EP3611387A2 - Roue à aubes d'une turbomachine - Google Patents

Roue à aubes d'une turbomachine Download PDF

Info

Publication number: EP3611387A2
Authority: EP; European Patent Office
Prior art keywords: blades; blade; blocks; angle; paddle wheel
Prior art date: 2018-08-14
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.): Granted

Application number

EP19190987.8A

Other languages

German (de)

English (en)

Other versions

EP3611387A3 (fr

EP3611387B1 (fr

Inventor

Sven SCHRAPE

Bernhard Mueck

Jens Nipkau

Thomas Giersch

Frank Heinichen

John Dodds

Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)

Rolls Royce Deutschland Ltd and Co KG

Rolls Royce PLC

Original Assignee

Rolls Royce Deutschland Ltd and Co KG

Rolls Royce PLC

Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)

2018-08-14

Filing date

2019-08-09

Publication date

2020-02-19

2019-08-09 Application filed by Rolls Royce Deutschland Ltd and Co KG, Rolls Royce PLC filed Critical Rolls Royce Deutschland Ltd and Co KG

2019-08-09 Priority to EP21195914.3A priority Critical patent/EP3940200B1/fr

2020-02-19 Publication of EP3611387A2 publication Critical patent/EP3611387A2/fr

2020-05-06 Publication of EP3611387A3 publication Critical patent/EP3611387A3/fr

2021-10-06 Application granted granted Critical

2021-10-06 Publication of EP3611387B1 publication Critical patent/EP3611387B1/fr

Status Active legal-status Critical Current

2039-08-09 Anticipated expiration legal-status Critical

Images

Classifications

- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/16—Form or construction for counteracting blade vibration
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
- F04D29/544—Blade shapes
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/125—Fluid guiding means, e.g. vanes related to the tip of a stator vane
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/24—Rotors for turbines
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/38—Arrangement of components angled, e.g. sweep angle
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/73—Shape asymmetric
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/90—Variable geometry
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
- F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
- F05D2270/101—Compressor surge or stall

Definitions

the invention relates to a paddle wheel of a turbomachine according to the preamble of claim 1 and a paddle wheel of a turbomachine according to the preamble of claim 11.
the invention is based on the object of providing a bucket wheel of a turbomachine and a bucket wheel arrangement in which the vibrations generated by a rotating separation are reduced.
the invention then considers a vane wheel of a turbomachine that has a plurality of vanes.
the blades are suitable and intended to extend radially in a flow path of the turbomachine and form a row of blades.
the blades form a blade entry angle and a blade exit angle.
the vane wheel forms N blocks of vanes with N 2 2, the vanes within a block each having the same vane entry angle and the same vane exit angle, and the vanes of at least two adjacent blocks having a different vane entry angle and / or have a different blade exit angle.
the number N is a natural number.
the solution according to the invention is based on the idea of avoiding or reducing the formation of a rotating detachment by introducing a changing aerodynamic load which acts on the blades.
the blade wheel under consideration can be a rotor with rotor blades or a stator with stator blades.
the invention also considers combinations of paddle wheels in individual aspects.
the phenomenon of rotating detachment is based on the fact that there is a stall in individual blade channels.
the flow material builds up in front of the detached blade channel and is pushed to the side (in the circumferential direction and counter to the rotor rotation).
the neighboring blade is flown against at a steeper flow angle and there is also a stall here.
the blocks of blades provided according to the invention the have different blade entry angles and / or blade exit angles, the blades in the individual blocks are flowed at at different angles or the flow leaves the blades of the individual blocks at different angles. It was found that this prevents the build-up of rotating cells or weakens such cells.
the paddle wheel can have an even or an odd number of blades.
an even number of blades it can be provided that two adjacent blocks of blades each have a different blade entry angle and / or a different blade exit angle, so that the change in angle is alternating.
an odd number of blades it can be provided that between two of the adjacent blocks there is no change in the blade entry angle and the blade exit angle in order to take account of the odd number of blocks, but between the other of the adjacent blocks.
the blocks of the impeller in one embodiment form a total of two different blade entry angles and / or blade exit angles, that is to say the alternating change in angle in each case relates to the same angle.
An embodiment of the invention provides that the blades of at least two adjoining blocks have a different blade entry angle and a different blade exit angle in that the blades of the blocks form a different staggering angle with the blades having an identical shape.
the blades of adjacent blocks thus have a different stagger angle.
the blades all have the same shape when viewed individually. They are only arranged in different blocks at a different stagger angle, it being provided, for example, that the blocks realize a total of two different stagger angles that alternate.
An alternative embodiment of the invention provides that the blades of at least two adjoining blocks have a different blade entry angle or a different blade exit angle in that the blades of the blocks have a different shape.
the different angles are thus not achieved via the staggering angle, but rather via the shape of the blades. If the blade wheel is a rotor, the blade entry angle is in particular at neighboring blocks are designed differently. If the blade wheel is a stator, the blade exit angle in particular is formed differently in the case of adjacent blocks.
the individual blocks have the same extension angle in the circumferential direction.
the individual blocks thus have the same size or the same number of blades, although it is provided that in the case of an odd number of blades, one block has one blade more than the other blocks.
At least two of the blocks have a different extension angle in the circumferential direction, the blocks with a different extension angle having a different number of blades.
An embodiment of this provides that all of the blocks have a different extension angle in the circumferential direction and accordingly a different number of blades.
a further embodiment provides that the blades of one block are open with respect to a nominal blade position and the blades of an adjacent block are closed with respect to the nominal blade position.
a nominal blade position is one that the blades of the blade council would assume without the invention.
the nominal blade position represents, as it were, an imaginary starting position of the blade position, from which the blades are closed or opened further depending on the block under consideration.
the blades of different blocks are opened or closed in one direction and in the other direction by the same amount of change, starting from the nominal blade position.
the change amount in one direction (for example "Open") does not necessarily have to correspond to the change amount in the other direction.
the blade entry angle and / or the blade exit angle between adjacent blocks does not change discretely, but continuously, for example in accordance with the shape of a sine curve.
the value ⁇ S, 0 corresponds to a nominal position from which the blades of a block are adjusted either in one direction or in the other direction by the change amount ⁇ S in order to implement the angle mentioned.
the blade entry angle and / or the blade exit angle can also be varied using the same formula.
⁇ i ⁇ 0 + - 1 i ⁇
⁇ i the blade entry angle or the blade exit angle
⁇ 0 and ⁇ ⁇ are constants and 1 i i N N.
the angle ⁇ S or the angle ⁇ ⁇ has, for example, a value which is in the range between 2 ° and 10 °.
the natural number N has a value that is between 2 and 10. It is true that a very high value of the number N means that the variations in the aerodynamic load are no longer perceived by the blades, so that a very high value of the number N is not effective.
patterns can be generated which do not have a common period over the circumference. This can effectively prevent or weaken the build-up of rotating cells.
the invention relates to a blade wheel arrangement for a compressor of a turbomachine, which comprises: a first blade wheel which is designed as an impeller, a second blade wheel which is arranged upstream of the first blade wheel and is designed as a stator wheel, and a third blade wheel which arranged downstream of the first impeller and is designed as a stator. It is provided that at least one of the blade wheels is designed as a blade wheel according to claim 1 and thus forms N blocks of blades with N ⁇ 2, the blades of a block each having the same blade entry angle and the same blade exit angle, and the blades of at least two adjoining one another Blocks have a different blade entry angle and / or a different blade exit angle.
An embodiment variant provides that the second impeller and the third impeller are designed as impeller according to claim 1, both impellers forming the same number of N blocks of blades with N ⁇ 2. According to this embodiment variant, the two stators of the considered sequence of stator-rotor-stator are thus designed in accordance with the present invention.
the rotor arranged between the two stators passes through flow blocks with different angles of incidence during one revolution.
changing aerodynamic and aeromechanical loads are exerted on the rotor. This prevents the development of rotating detachment cells, since their development takes a certain time over more than one revolution requires. Aerodynamic instability is created which changes the vibration response of the rotor and more strongly suppresses vibrations.
the size of the blocks and the variation of the blade entry angle and / or blade exit angle must be set such that the redistribution of flowing mass is sufficiently large to avoid or significantly suppress the development of a demolition pattern that is radially limited in its extent.
⁇ S2.0 and ⁇ S3.0 are constants and is 1 ⁇ i ⁇ N. Both paddle wheels have the same division into N blocks.
the values ⁇ S2.0 and ⁇ S3.0 each correspond to a nominal position, from which the blades of a block are adjusted either in one direction or in the other direction by the amount of change ⁇ S2 or ⁇ ⁇ S3 by the said angle realize.
Another embodiment of the invention provides that the first impeller, that is to say the rotor of the sequence of stator-rotor-stator considered, is designed as an impeller according to claim 1.
the size of the blocks and the variation of the blade entry angle and / or blade exit angle must in turn be set such that the redistribution of flowing mass is sufficiently large to avoid or significantly suppress the development of a demolition pattern that is radially limited in its extent.
the blade wheels are designed according to the present invention, or that only one of the stators is designed according to the present invention.
the said angles can be varied by varying the staggering angle or by varying the shape of the blades of the individual blocks.
a variation of the stagger angle on one blade wheel can also be combined with a variation of the shape of the blades on another blade wheel.
the second vane which is designed as a stator
the second vane is designed as an inlet stator.
Aircraft engine compressors are designed for a specific design speed. Especially in the partial load range, i.e. at speeds lower than the design speed there is a risk of local flow separation on the rotor blades of the compressor grille.
a stator with stator blades that may be adjustable in front of the first rotor of the compressor.
Such a stator is referred to as an inlet guide vane or a guide vane or as an IGV (IGV - Inlet Guide Vane).
IGV IGV - Inlet Guide Vane
the invention is in no way limited to the fact that the upstream row of blades is designed as an inlet guide wheel.
the upstream blade row can also be a normal stator of a compressor.
the invention can therefore be implemented both in front stages and in stages that are embedded in a compressor.
the second blade wheel has N blocks of blades, at least two of the blocks having a different blade exit angle.
the third blade wheel has N blocks of blades, at least two of the blocks having a different blade exit angle.
the blade outlet angle is thus varied according to this embodiment of the invention.
the blade entry angle is varied in the case of the first blade wheel designed as a rotor.
the first blade wheel has N blocks of blades, at least two of the blocks having a different blade entry angle.
downstream third impeller designed as a stator or the row of blades formed by it has only a change in the impeller inlet angle
upstream second impeller designed as stator has a change in the impeller exit angle. This serves to adapt the angle of incidence to the circumferential variation caused by the upstream impeller.
the blade entry angle is increased in the area of the upstream closed stator and the blade entry angle is reduced in the area of the upstream opened stator.
a further embodiment of the invention provides that a block or peripheral area of the second blade wheel, in which the blades of the block are more closed than a nominal blade position, is assigned a block or peripheral area of the third blade wheel, in which the blades of the block face each other a nominal blade position are more open.
the flow which has undergone a greater deflection in a block of the second, upstream paddle wheel, therefore experiences less deflection in the corresponding block of the third, downstream paddle wheel and vice versa.
Another aspect of the present invention considers a vane wheel with a plurality of guide vanes which extend in a flow path of the turbomachine, the guide vanes each being adjustable in their staggering angle are trained.
the guide vanes have first partial gaps for an outer flow path boundary and / or second partial gaps for an inner flow path boundary.
the radially inner flow path boundary is provided, for example, by a hub of the compressor and the outer flow path boundary by a compressor housing. It is pointed out that, due to the rotatability of the guide vanes, the partial gaps are necessarily formed adjacent to the flow path boundary and their existence only enables the staggering angle to be rotated or changed, since without such partial gaps, contact or collision with the flow path boundary occurs when the staggering angle changes would.
the gaps are referred to as partial gaps since they do not extend over the entire axial length of the guide vanes, but only over a partial length.
the paddle wheel forms N blocks of blades with N 2 2, the blades of a block each having partial gaps formed in the same manner and the blades of at least two adjacent blocks having differently shaped partial gaps.
This aspect of the invention is also based on the idea of avoiding or reducing the formation of a rotating separation by introducing a changing aerodynamic load which acts on the blades.
the flow in the individual blocks is varied by the blocks of blades provided according to the invention, which form different partial gaps for the flow path boundary.
the partial columns in the different blocks are designed differently.
the paddle wheel implements a total of two different configurations of the partial column, which implement the blocks of the paddle wheel alternately.
the blades of at least two adjoining blocks have partial gaps that have a different axial length.
a variation of the partial column in different blocks thus takes place over the axial length of the partial column.
Such a variation can be achieved, for example, by varying the diameter of turntables which form the guide vanes at their radially outer end and / or at their radially inner end and which enable their rotation.
the blades of at least two adjoining blocks have partial gaps that have a different radial height.
a variation of the partial column in different blocks thus takes place over the radial height of the partial column.
Such a variation can be achieved via the radial depth of recesses which are formed in the region of the front edge and / or in the region of the rear edge and thereby radially adjacent to the respective flow path boundary on the guide vanes.
a further embodiment provides that the blades of at least two adjoining blocks have partial gaps which have a different axial length and a different radial height, the variations of the partial gaps explained above are thus combined.
the partial gaps are formed by undercuts which form the guide vanes to the adjacent flow path boundary.
a gap volume of the partial gap is defined via the length and height of the partial column.
the partial gaps of the blades of adjacent blocks have a different gap volume.
the invention relates to a vane wheel arrangement for a compressor of a turbomachine, which comprises: a first vane wheel which is designed as an impeller, a second vane wheel which is arranged upstream of the first vane wheel and is designed as a stator wheel, and a third vane wheel which arranged downstream of the first impeller and is designed as a stator. It is provided that the second impeller and / or the third impeller are designed as an impeller according to claim 11.
An embodiment of the impeller arrangement provides that the second impeller and the third impeller are designed as impeller according to claim 11, both impellers forming the same number of N blocks of impellers with N ⁇ 2.
a further embodiment provides that the second impeller is designed as an inlet guide wheel, a block of the second impeller in which the gap volume of the partial gaps is larger is assigned a block of the third blade wheel in which the gap volume of the partial gaps is smaller, and vice versa ,
the flow which has experienced a greater disturbance in a block of the upstream inlet stator due to the larger partial gap, therefore experiences less interference in the corresponding block of the third, downstream paddle wheel due to the smaller partial gap and vice versa.
the designations "larger” and “smaller” each refer to the gap volume of the adjacent block of the paddle wheel under consideration.
the impeller arrangement is embedded in a compressor, the second impeller being designed as an embedded stator (and not as an inlet stator). It is provided that a block of the second paddle wheel, in which the gap volume of the partial gaps is smaller, is assigned a block of the third paddle wheel, in which the gap volume of the partial gaps is also smaller, and a block of the second paddle wheel, in which the gap volume of the Partial column is larger, a block of the third paddle wheel is assigned, in which the gap volume of the partial column is also larger.
the flow which has experienced a greater disturbance in a block of the upstream paddle wheel due to a larger partial gap thus also experiences a greater disturbance in the corresponding block of the third, downstream paddle wheel due to also larger partial gap than in the blocks with smaller partial gaps.
the designations “larger” and “smaller” each refer to the gap volume of the adjacent block of the paddle wheel under consideration.
the present invention insofar as it relates to an aircraft engine, is described with reference to a cylindrical coordinate system which has the coordinates x, r and ⁇ .
X indicates the axial direction, r the radial direction and ⁇ the angle in the circumferential direction.
the axial direction is identical to the machine axis of a gas turbine engine in which the impeller or the impeller arrangement is arranged. Starting from the x-axis, the radial direction points radially outwards.
Terms such as “in front”, “behind”, “front” and “rear” refer to the axial direction or the direction of flow in the engine in which the planetary gear is arranged.
Terms such as “outer” or “inner” refer to the radial direction.
Such a gas turbine engine may include an engine core that includes a turbine, a combustion chamber, a compressor, and a core shaft connecting the turbine to the compressor.
Such a gas turbine engine may include a fan (with fan blades) positioned upstream of the engine core.
the gas turbine engine may include a transmission that receives an input from the core shaft and drives the fan to drive the fan at a lower speed than the core shaft.
the input for the transmission can take place directly from the core shaft or indirectly from the core shaft, for example via a spur shaft and / or a spur gear.
the core shaft can with the turbine and be rigidly connected to the compressor so that the turbine and the compressor rotate at the same speed (with the fan rotating at a lower speed).
the gas turbine engine described and / or claimed herein can have any suitable general architecture.
the gas turbine engine may have any desired number of shafts connecting turbines and compressors, for example one, two or three shafts.
the turbine connected to the core shaft may be a first turbine
the compressor connected to the core shaft may be a first compressor
the core shaft may be a first core shaft.
the engine core may further include a second turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor.
the second turbine, the second compressor, and the second core shaft may be arranged to rotate at a higher speed than the first core shaft.
the second compressor may be positioned axially downstream of the first compressor.
the second compressor can be arranged to receive flow from the first compressor (for example, to receive directly, for example via a generally annular channel).
the transmission may be arranged to be driven by the core shaft configured to rotate (e.g., in use) at the lowest speed (e.g., the first core shaft in the example above).
the transmission may be arranged to be driven only by the core shaft configured to rotate at the lowest speed (for example, in use) (for example, only the first core shaft and not the second core shaft in the example above) become.
the transmission may be arranged to be driven by one or more shafts, for example the first and / or the second shaft in the example above.
a combustion chamber may be provided axially downstream of the blower and the compressor (s).
the combustion chamber can be located directly downstream of the second compressor (for example at its outlet) if a second compressor is provided.
the flow at the outlet of the compressor be fed to the inlet of the second turbine if a second turbine is provided.
the combustion chamber can be provided upstream of the turbine (s).
each compressor for example, the first compressor and the second compressor as described above
Each stage can include a series of rotor blades and a series of stator blades, which can be variable stator blades (in that their angle of attack can be variable).
the row of rotor blades and the row of stator blades can be axially offset from one another.
the or each turbine can comprise any number of stages, for example several stages.
Each stage can include a series of rotor blades and a series of stator blades.
the row of rotor blades and the row of stator blades can be axially offset from one another.
Each fan blade may be defined with a radial span that extends from a foot (or hub) at a radially inner gas-swept location or at a 0% span position to a tip at a 100% span position.
the ratio of the radius of the fan blade at the hub to the radius of the fan blade at the tip may be less than (or on the order of): 0.4, 0.39, 0.38, 0.37, 0.36, 0, 35, 0.34, 0.33, 0.32, 0.31, 0.3, 0.29, 0.28, 0.27, 0.26 or 0.25.
the ratio of the radius of the fan blade at the hub to the radius of the fan blade at the tip can be in an inclusive range limited by two of the values in the previous sentence (i.e. the values can form upper or lower limits).
the hub-to-tip ratio can be commonly referred to as the hub-to-tip ratio.
the radius at the hub and the radius at the tip can both be measured at the front edge portion (or the axially most forward edge) of the blade.
the hub-to-tip ratio refers to the portion of the fan blade over which gas flows, i.e. H. the section that is radially outside of any platform.
the radius of the fan can be measured between the center line of the engine and the tip of the fan blade at its front edge.
the diameter of the Blower (which can simply be twice the radius of the blower) can be larger than (or on the order of): 250 cm (about 100 inches), 260 cm, 270 cm (about 105 inches), 280 cm (about 110 inches) , 290 cm (about 115 inches), 300 cm (about 120 inches), 310 cm, 320 cm (about 125 inches), 330 cm (about 130 inches), 340 cm (about 135 inches), 350 cm, 360 cm ( about 140 inches), 370 cm (about 145 inches), 380 cm (about 150 inches) or 390 cm (about 155 inches).
the fan diameter can be in an inclusive range limited by two of the values in the previous sentence (ie the values can be upper or lower limits).
the speed of the fan can vary in use. In general, the speed is lower for fans with a larger diameter. As a non-limiting example only, the fan speed may be less than 2500 rpm, for example less than 2300 rpm, under constant speed conditions.
the speed of the fan under constant speed conditions for an engine with a fan diameter in the range from 320 cm to 380 cm can be in the range from 1200 rpm to 2000 rpm, for example in the range from 1300 rpm. min to 1800 rpm, for example in the range from 1400 rpm to 1600 rpm.
a blower tip load can be defined as dH / U tip 2 , where dH is the enthalpy rise (e.g. the average 1-D enthalpy rise) across the blower and U tip is the (translation) speed of the blower tip, e.g. at the front edge of the tip , (which can be defined as the blower tip radius at the front edge multiplied by the angular velocity).
the blower peak load under constant speed conditions can be more than (or on the order of): 0.3, 0.31, 0.32, 0.33, 0.34, 0.35, 0.36, 0.37, 0.38 , 0.39 or 0.4 are (lie) (all units in this section being Jkg -1 K -1 / (ms -1 ) 2 ).
the blower peak load can be in an inclusive range delimited by two of the values in the previous sentence (ie the values can be upper or lower bounds).
Gas turbine engines in accordance with the present disclosure may have any desired bypass ratio, the bypass ratio being defined as the ratio of the mass flow rate of flow through the bypass channel to the mass flow rate of flow through the core at constant speed conditions.
the bypass ratio can be more than (on the order of): 10, 10.5, 11, 11.5, 12, 12.5, 13, 13.5, 14, 14.5, 15, 15.5 , 16, 16.5 or 17 are (lying).
the bypass ratio can be in an inclusive range limited by two of the values in the previous sentence (i.e., the values can be upper or lower limits).
the bypass channel can be essentially ring-shaped.
the bypass channel can be located radially outside the engine core.
the radially outer surface of the bypass duct can be defined by an engine nacelle and / or a blower housing.
the total pressure ratio of a gas turbine engine described and / or claimed herein can be defined as the ratio of the back pressure upstream of the fan to the back pressure at the output of the supercharger (prior to entering the combustion chamber).
the total pressure ratio of a gas turbine engine described and / or claimed herein at constant speed may be more than (or on the order of): 35, 40, 45, 50, 55, 60, 65, 70, 75 (lie).
the total pressure ratio can be in an inclusive range limited by two of the values in the previous sentence (i.e. the values can be upper or lower limits).
the specific thrust of an engine can be defined as the net thrust of the engine divided by the total mass flow through the engine. Under constant speed conditions, the specific thrust of an engine described and / or claimed herein may be less than (or on the order of): 110 Nkg -1 s, 105 Nkg -1 s, 100 Nkg -1 s, 95 Nkg -1 s, 90 Nkg -1 s, 85 Nkg -1 s or 80 Nkg -1 s.
the specific thrust can be in an inclusive range limited by two of the values in the previous sentence (ie the values can be upper or lower limits). Such Engines can be particularly efficient compared to conventional gas turbine engines.
a gas turbine engine described and / or claimed herein can have any desired maximum thrust.
a gas turbine described and / or claimed herein can produce a maximum thrust of at least (or on the order of): 160kN, 170kN, 180kN, 190kN, 200kN, 250kN, 300kN, 350kN, 400kN , 450kN, 500kN or 550kN.
the maximum thrust can be in an inclusive range limited by two of the values in the previous sentence (i.e. the values can be upper or lower limits).
the thrust referred to above can be the maximum net thrust under standard atmospheric conditions at sea level plus 15 degrees C (ambient pressure 101.3 kPa, temperature 30 degrees C) for static engines.
the temperature of the flow at the inlet of the high pressure turbine can be particularly high.
This temperature which can be referred to as TET
TET can be measured at the exit to the combustion chamber, for example immediately upstream of the first turbine blade, which in turn can be referred to as a nozzle guide blade.
the TET can be at least (or in the order of magnitude): 1400K, 1450K, 1500K, 1550K, 1600K or 1650K.
the constant velocity TET can be in an inclusive range limited by two of the values in the previous sentence (i.e., the values can be upper or lower limits).
the maximum TET in use of the engine can be at least (or on the order of): 1700K, 1750K, 1800K, 1850K, 1900K, 1950K or 2000K.
the maximum TET can be in an inclusive range limited by two of the values in the previous sentence (i.e. the values can be upper or lower limits).
the maximum TET can occur, for example, in a condition of high thrust, for example an MTO condition (MTO - maximum take-off thrust - maximum start thrust).
a fan blade and / or a blade portion of a fan blade described and / or claimed herein can be made from any suitable material or combination of materials.
at least part of the fan blade and / or the blade can be made at least partly of a composite, for example a metal matrix composite and / or a Organic matrix composite such as B. carbon fiber.
at least a portion of the fan blade and / or the blade may be at least partially made of a metal, such as. B. a titanium-based metal or an aluminum-based material (such as an aluminum-lithium alloy) or a steel-based material.
the fan blade may include at least two areas made using different materials.
the fan blade may have a front protective rim that is made using a material that is more resistant to impact (e.g., birds, ice, or other material) than the rest of the blade.
a leading edge can be produced, for example, using titanium or a titanium-based alloy.
the fan blade may include a carbon fiber or aluminum based body (such as an aluminum-lithium alloy) with a titanium front edge.
a fan described and / or claimed herein may include a central portion from which the fan blades may extend, for example in a radial direction.
the fan blades can be attached to the central section in any desired manner.
each fan blade can include a fixation device that can engage a corresponding slot in the hub (or disc).
a fixing device in the form of a dovetail, which can be inserted into and / or brought into engagement with a corresponding slot in the hub / disc for fixing the fan blade, can be present only as an example.
the fan blades can be integrally formed with a central portion. Such an arrangement can be referred to as a blisk or a bling. Any suitable method can be used to make such a blisk or bling.
at least some of the fan blades can be machined out of a block and / or at least some of the fan blades can be welded, e.g. B. linear friction welding, attached to the hub / disc.
VAN Very Area Nozzle - nozzle with a variable cross-section
Such a variable cross section nozzle may allow the output cross section of the bypass channel to be varied in use.
the general Principles of the present disclosure may apply to engines with or without a VAN.
blower of a gas turbine which is described and / or claimed here, can have any desired number of blower blades, for example 16, 18, 20 or 22 blower blades.
constant speed conditions may mean constant speed conditions of an aircraft to which the gas turbine engine is attached.
Such constant speed conditions can conventionally be defined as the conditions during the middle part of the flight, for example the conditions to which the aircraft and / or the engine are exposed between (in terms of time and / or distance) the end of the climb and the start of the descent. become.
the forward speed at the constant speed condition at any point may range from Mach 0.7 to 0.9, for example 0.75 to 0.85, for example 0.76 to 0.84, for example 0.77 to 0 , 83, for example 0.78 to 0.82, for example 0.79 to 0.81, for example in the order of Mach 0.8, in the order of Mach 0.85 or in the range of 0.8 to 0, 85 lie. Any speed within these ranges can be the constant travel condition. For some aircraft, constant speed conditions may be outside of these ranges, for example below Mach 0.7 or above Mach 0.9.
the constant speed conditions may be standard atmospheric conditions at an altitude that is in the range of 10,000 m to 15,000 m, for example in the range of 10,000 m to 12,000 m, for example in the range of 10,400 m to 11,600 m (approximately 38,000 feet), for example in Range from 10,500 m to 11,500 m, for example in the range from 10,600 m to 11,400 m, for example in the range from 10,700 m (approximately 35,000 feet) to 11,300 m, for example in the range from 10,800 m to 11,200 m, for example in the range from 10,900 m to 11,100 m, for example in the order of 11,000 m, correspond.
the constant speed conditions can correspond to standard atmospheric conditions at any given altitude in these areas.
the constant speed conditions may correspond to: a forward Mach number of 0.8; a pressure of 23,000 Pa and a temperature of -55 degrees C.
constant speed or “constant speed conditions” can mean the aerodynamic design point.
Such an aerodynamic design point can correspond to the conditions (including, for example, the Mach number, ambient conditions and thrust requirement) for which the blower operation is designed. This can mean, for example, the conditions in which the blower (or the gas turbine engine) has the optimum efficiency by design.
a gas turbine engine described and / or claimed herein can be operated at the constant speed conditions defined elsewhere herein.
Such constant speed conditions can be determined from the constant speed conditions (e.g., mid-flight conditions) of an aircraft to which at least one (e.g., 2 or 4) gas turbine engine may be attached to provide thrust.
Figure 1 represents a gas turbine engine 10 with a main axis of rotation 9.
the engine 10 comprises an air inlet 12 and a thrust blower or fan 23, which generates two air streams: a core air stream A and a bypass air stream B.
the gas turbine engine 10 comprises a core 11, which is the core air stream A. receives.
the engine core 11 comprises, in axial flow order, a low-pressure compressor 14, a high-pressure compressor 15, a combustion device 16, a high-pressure turbine 17, a low-pressure turbine 19 and a core thrust nozzle 20.
An engine nacelle 21 surrounds the gas turbine engine 10 and defines a bypass duct 22 and a bypass thrust air jet 18 flows through the bypass duct 22.
the fan 23 is attached to the low-pressure turbine 19 via a shaft 26 and an epicycloid gear 30 and is driven by the latter.
the core air flow A is accelerated and compressed by the low pressure compressor 14 and passed into the high pressure compressor 15, where further compression takes place.
the compressed air discharged from the high pressure compressor 15 is conducted into the combustion device 16, where it is mixed with fuel and the mixture is burned.
the resulting hot combustion products then propagate through and drive the high pressure and low pressure turbines 17, 19 before being expelled through the nozzle 20 to provide some thrust.
the high-pressure turbine 17 drives the high-pressure compressor 15 through a suitable connecting shaft 27.
the blower 23 generally provides most of the thrust.
the epicycloid gear 30 is a reduction gear.
FIG Figure 2 An exemplary arrangement for a gear blower gas turbine engine 10 is shown in FIG Figure 2 shown.
the low pressure turbine 19 (see Figure 1 ) drives the shaft 26, which is coupled to a sun gear 28 of the epicycloid gear arrangement 30.
a plurality of planet gears 32 which are coupled to one another by a planet carrier 34, are located radially on the outside of the sun gear 28 and mesh with it.
the planet carrier 34 limits the planet gears 32 to orbit synchronously around the sun gear 28 while allowing each planet gear 32 to rotate about its own axis.
the planet carrier 34 is coupled to the blower 23 via linkages 36 to drive its rotation about the engine axis 9.
An outer gear or ring gear 38 which is coupled to a stationary support structure 24 via linkages 40, is located radially outside of the planet gears 32 and meshes therewith.
low pressure turbine and “low pressure compressor” as used herein can be understood to mean the lowest pressure turbine stage and the lowest pressure compressor stage (ie, they are not the blower 23) and / or the turbine and compressor stage connected by the lowest speed connection shaft 26 in the engine (ie not including the transmission output shaft that drives the blower 23).
the "low pressure turbine” and the “low pressure compressor” referred to herein may alternatively be known as the “medium pressure turbine” and “medium pressure compressor”.
the blower 23 can be referred to as a first compression stage or compression stage with the lowest pressure.
the epicycloid gear 30 is in Figure 3 shown in more detail by way of example.
the sun gear 28, the planet gears 32 and the ring gear 38 each include teeth around their periphery for meshing with the other gears. However, for the sake of clarity, only exemplary sections of the teeth are shown in FIG Figure 3 shown.
four planet gears 32 are shown, it is obvious to a person skilled in the art that more or fewer planet gears 32 can be provided within the scope of the claimed invention.
Practical applications of an epicycloid gear 30 generally include at least three planet gears 32.
Epicycloid gear 30 shown as an example is a planetary gear in which the planet carrier 34 is coupled to an output shaft via linkages 36, the ring gear 38 being fixed.
the epicycloid gear 30 may be a star configuration with the planet carrier 34 held in place, allowing the ring gear (or outer gear) 38 to rotate. With such an arrangement, the blower 23 is driven by the ring gear 38.
the transmission 30 may be a differential transmission that allows both the ring gear 38 and the planet carrier 34 to rotate.
the present disclosure extends to a gas turbine engine with any arrangement of the transmission types (for example star-shaped or planet-like), support structures, input and output shaft arrangements and bearing positions.
the transmission types for example star-shaped or planet-like
support structures for example star-shaped or planet-like
input and output shaft arrangements and bearing positions for example star-shaped or planet-like
the transmission can drive secondary and / or alternative components (e.g. the medium pressure compressor and / or a secondary compressor).
secondary and / or alternative components e.g. the medium pressure compressor and / or a secondary compressor.
gas turbine engines to which the present disclosure may apply may have alternative configurations.
such engines can have an alternative number of compressors and / or turbines and / or have an alternative number of connection shafts.
Figure 1 Gas turbine engine shown a split stream nozzle 20, 22, which means that the flow through the bypass passage 22 has its own nozzle, which is separate from the engine core nozzle 20 and radially outward therefrom.
this is not limitative and any aspect of the present disclosure may apply to engines in which the flow through the bypass passage 22 and the flow through the core 11 are in front of (or upstream) a single nozzle, which may be referred to as a mixed flow nozzle, can be mixed or combined.
One or both nozzles can have a fixed or variable range.
the example described relates to a turbo blower engine
the disclosure may be applicable to any type of gas turbine engine, such as a. B. with an open rotor (in which the blower stage is not surrounded by an engine nacelle) or a turboprop engine.
the gas turbine engine 10 may not include a transmission 30.
the geometry of the gas turbine engine 10 and components thereof is defined by a conventional axis system that has an axial direction (which is aligned with the axis of rotation 9), a radial direction (in the bottom-up direction in FIG Figure 1 ) and a circumferential direction (perpendicular to the view in Figure 1 ) includes.
the axial, the radial and the circumferential direction are perpendicular to each other.
the formation of the impellers in the compressor is important.
the invention can basically be used in a low pressure compressor, a medium pressure compressor (if present) and / or a high pressure compressor.
the compressor grille is shown in the usual representation in the meridian section and unrolled. It comprises a plurality of blades S, each of which has a front edge S VK and a rear edge S HK .
the front edges S VK lie on an imaginary line L 1
the rear edges S HK lie on an imaginary line L 2 .
Lines L 1 and L 2 run parallel.
the blades S furthermore each comprise a suction side SS and a pressure side DS. Your maximum profile thickness is indicated with d.
the compressor grid has a grid pitch t and a chord s with a chord length S k .
the chord s is the connecting line between the The leading edge S VK and the trailing edge S HK of the profile.
the blade stagger angle (hereinafter stagger angle) ⁇ s is formed between the chord s and the perpendicular on the line L 1 (the perpendicular at least approximately corresponding to the direction defined by the machine axis).
the staggering angle ⁇ s indicates the inclination of the blades S.
the blades S have a skeleton line SL, which is also referred to as the profile center line. This is defined by the connecting line of the circle center points inscribed in the profile.
the tangent to the skeleton line SL at the front edge is designated T 1 .
the tangent to the skeletal guideline SL at the rear edge is designated T2.
the angle at which the two tangents T 1 , T2 intersect is the blade curvature angle A.
the inflow direction with which gas flows onto the grille is marked with Z and the outflow direction with which gas flows away from the grille is marked with D.
the angle of incidence ⁇ 1 is defined as the angle between the tangents T 1 and the inflow direction Z.
the deviation angle ⁇ 2 is defined as the angle between the tangents T2 and the outflow direction A.
the blade entry angle ⁇ 1 and the blade exit angle ⁇ 2 are of particular importance.
the blade exit angle ⁇ 1 is defined as the angle between the tangent T 1 to the skeleton line SL and the perpendicular on the line L 1 .
the blade exit angle ⁇ 2 is defined as the angle between the tangent T2 to the skeleton line SL and the perpendicular on the line L 2 .
the blade entry angle ⁇ 1 is also referred to as the blade entry angle or the inflow metal angle and the blade exit angle ⁇ 2 is also referred to as the blade exit angle or the outflow metal angle.
the blade entry angle ⁇ 1 and the blade exit angle ⁇ 2 both change if the staggering angle ⁇ s is changed with the blades having the same shape, since in such a case a change in the staggering angle ⁇ s due to the inclination adjustment of the blades connected with this the orientation of the tangents T 1 , T2 changed.
the blade entry angle ⁇ 1 and / or the blade exit angle ⁇ 2 can also be changed without changing the staggering angle ⁇ s . It can also be provided that only the blade entry angle ⁇ 1 or the blade exit angle ⁇ 2 is changed by appropriate shaping of the blades S, this also leading to a change in the staggering angle ⁇ s .
the Figure 5 shows a blade wheel arrangement for a compressor, which has a first blade wheel 6, which is designed as an impeller.
a second impeller 5 is arranged upstream of the impeller 6 and is designed as a stator.
a third blade wheel 7 is arranged downstream of the impeller 6 and is designed as a further stator wheel.
the upstream stator 5 can be designed as an input stator (IGV). However, this is not necessarily the case. It can also be a normal compressor stator of a stage embedded in the compressor.
a flow path 8 of the compressor or the core engine extends through the impeller arrangement.
Each of these blade wheels 5, 6, 7 comprises a plurality of blades that extend radially in the flow path 8 of the turbomachine. It is provided that the blades on at least one of the blade wheels 5, 6, 7 are divided into blocks, for which the blades within a block each have the same blade entry angle and the same blade exit angle. In contrast, the blades of at least two adjacent blocks have a different blade entry angle and / or a different blade exit angle.
the Figure 6 shows in a cross section transverse to the machine axis showing the polar coordinates r, ⁇ a paddle wheel, which is one of the paddle wheels 5, 6, 7 of the Figure 5 can act.
the individual blades are not shown separately.
the paddle wheel is divided into two blocks B1, B2. Each of the blocks extends in the circumferential direction ⁇ over an extension angle ⁇ of 180 °.
the blades of the blocks B1, B2 have a different blade entry angle and / or a different blade exit angle.
the Figure 6 additionally shows an alternative embodiment in which the individual blocks B1, B2 have a different extension angle in the circumferential direction exhibit.
the one block B1 has an extension angle ⁇ 1 of less than 180 ° and the block B2 has an extension angle which is correspondingly greater than 180 °.
the paddle wheel is divided into a larger number of blocks, the individual blocks each having a different extension angle and, accordingly, a different number of blades.
FIG. 7 initially shows a nominal position of the blades, all blades having the same blade entry angle and the same blade exit angle.
the blade wheel arrangement shown here comprises a rotor or an impeller 6 which has a plurality of blades 60 which rotate in a direction F.
the blades 60 of the impeller 6 form a row of blades.
the Figure 8 shows a first embodiment of a different vane wheel arrangement.
the stator 5 is considered first.
This has N blocks of blades, blades of two blocks, namely the blocks B j and B k, being shown.
the individual blocks comprise in the representation of the Figure 8 two shovels each. This is only to be understood as an example.
the Figure 8 shows both the blades 50 in the nominal position corresponding to the Figure 7 as well as the blades in a changed position.
the blades in the changed position are identified in block B j with 51 and in block B k with 52. It is the case that the blades 51, 52 of the two blocks B j and B k have a different stagger angle.
⁇ S2.0 is a constant that defines the nominal stagger angle according to the Figure 7 indicates. The following applies to i: 1 ⁇ i ⁇ N. From the nominal position, the stagger angle is adjusted in one direction or in the other direction by the change amount ⁇ S2 . With the blades of adjacent blocks B j and B k , the stagger angle is changed with a different sign. There is a change in the stagger angle between the blades 50 and the blades 51 of the block B j by the amount of change - ⁇ S2 , as in FIG Figure 5 is indicated. Between the blades 50 and the blades 52 of the block B k there is a change in the stagger angle by the change amount + ⁇ S2 . The graduation angle is like in relation to the Figure 4 explains defined.
the change in the stagger angle in the individual blocks is accompanied by the fact that the stator blades are more closed than in the nominal position in block B j and more open in block B k .
the Figure 8 shows both blades 70 in the nominal position corresponding to FIG Figure 7 as well as the blades in a modified position.
the blades in the modified position are identified in block B j with 71 and in block B k with 72. It is the case that the blades 71, 72 of the two blocks B j and B k have a different stagger angle.
⁇ S3.0 is a constant that defines the nominal stagger angle according to the Figure 7 As.
the explanations for the stator 5 apply in a corresponding manner.
There is a change in the stagger angle between the blades 70 and the blades 71 of the block B j by the amount of change + ⁇ S3 , as in FIG Figure 5 is indicated.
the change in sign in the individual blocks of the stator 7 is in the opposite direction to that of the blocks of the stator 5. If the stator blades 51 are more closed in block B j of the stator 5, the stator blades 71 are stronger in block B j of the stator 7 open. It also applies that if the stator blades 52 are more open in the block B k of the stator 5, the stator blades 71 in the block B k of the stator 7 are more closed.
the change amount ⁇ S3 can be equal to the change amount ⁇ S2 . However, this is not necessarily the case.
the blades of the impeller 6 are also divided into groups with different staggering angles. However, this is not necessarily the case. In exemplary embodiments of the invention, only the blades of the stator 5 and / or the blades of the stator 7 are divided into groups with different staggering angles. In further exemplary embodiments it can be provided that only the blades of the impeller 6 are divided into groups with different staggering angles.
the Figure 8 shows both the blades 60 in the nominal position corresponding to the Figure 7 as well as the blades in a modified position.
the impeller 6 is divided into the same number N of blocks, each with a different staggering angle than the guide wheels 5, 7.
the blades in the modified position are identified in block B j with 61 and in block B k with 62. It is the case that the blades 61, 62 of the two blocks B j and B k have a different stagger angle.
⁇ S1.0 is a constant that defines the nominal stagger angle according to the Figure 7 As.
the explanations for the stator 5 apply in a corresponding manner.
There is a change in the stagger angle between the blades 60 and the blades 61 of the block B j by the amount of change + ⁇ S1 , as in FIG Figure 5 is indicated.
the Figure 9 shows a second embodiment of a to the arrangement of Figure 7 deviating impeller arrangement.
the fundamental difference to the embodiment of Figure 8 is that in the embodiment of the Figure 9 not the stagger angle (and thus the blade entry angle and the blade exit angle in the case of identical shape of the individual blades) is changed, but only the blade entry angle or the blade exit angle is changed while providing a different shape of the blades of the different blocks.
the stator 5 is considered first. This has N blocks of blades, blades of two blocks, namely the blocks B j and B k, being shown.
the comments on the size and number of blocks with regard to the Figure 8 apply accordingly to the Figure 9 ,
the Figure 9 shows both the blades 50 in the nominal position corresponding to the Figure 7 as well as the blades in a changed position.
the blades with modified shapes are identified in block B j with 53 and in block B k with 54. It is the case that the blades 53, 54 of the two blocks B j and B k have a different blade inlet angle with an identical blade inlet angle.
⁇ 2 S2.0 is a constant, which is the nominal blade outlet angle according to the Figure 7 indicates.
i applies: 1 ⁇ i ⁇ N.
the blade exit angle is changed with a different sign.
the blade exit angle is like in relation to the Figure 4 explains defined.
the change in the blade outlet angle in the individual blocks is accompanied by the fact that the stator blades are more closed in block B j and more open in block B k .
the Figure 9 shows both blades 70 in the nominal position corresponding to FIG Figure 7 as well as the blades in a modified position.
the blades with a modified shape are identified in block B j with 73 and in block B k with 74. It is the case that the blades 73, 74 of the two blocks B j and B k have a different blade outlet angle with an identical blade inlet angle.
⁇ 2, S3.0 is a constant, which is the nominal blade outlet angle according to the Figure 7 indicates.
the blade exit angle is adjusted in one direction or in the other direction by the change amount ⁇ 2, S3 .
the blade exit angle is changed with a different sign.
the change amount - ⁇ 2, S3 there is a change in the blade exit angle by the change amount - ⁇ 2, S3 .
stator blades 51 are more closed in block B j of the stator 5
stator blades 71 are stronger in block B j of the stator 7 open. It also applies that if the stator blades 52 are more open in the block B k of the stator 5, the stator blades 71 in the block B k of the stator 7 are more closed.
the blades of the impeller 6 are also divided into groups with different blade entry angles, although this is not necessarily the case. It can also be provided in one embodiment variant that only the blades of the impeller 6 are divided into groups with different blade entry angles.
the Figure 9 shows both the blades 60 in the nominal position corresponding to the Figure 7 as well as the blades with modified shape.
the impeller 6 is divided into the same number N of blocks as the other paddle wheels 5, 7.
the blades in the modified shape are identified in block B j with 61 and in block B k with 62. It is the case that the blades 61, 62 of the two blocks B j and B k have a different blade inlet angle with an identical blade outlet angle.
⁇ 1, S1.0 is a constant that defines the nominal blade entry angle according to the Figure 7 indicates.
i 1 ⁇ i ⁇ N.
the blade exit angle is adjusted in one direction or in the other direction by the change amount ⁇ 1, S1 .
the blade entry angle is changed with a different sign.
the change amount - ⁇ 1, S1 there is a change in the blade exit angle by the change amount - ⁇ 1, S1 .
FIG. 11-14 A further exemplary embodiment of the invention is described, in which the blades of a paddle wheel are also divided into a plurality of blocks, the blades being designed identically within a block are.
the property in which the individual blocks differ is different than in the exemplary embodiments in FIG Figures 4-9 not the blade entry angle and / or the blade exit angle, but lies in the design of partial gaps that form the blades for the respectively adjacent flow path boundary.
the explanations for the Figures 4-9 accordingly.
the Figure 11 shows a sectional view of a structural assembly that defines a flow path 8 and comprises a stator 5, a rotor 6 of a compressor stage of a compressor and flow path boundaries.
the stator 5 is designed as an inlet stator, although this is not necessarily the case.
the flow path 8 conducts the core air flow A according to the Figure 1 through the core engine.
the flow path 8 is delimited radially on the inside by a hub 95, which forms an inner flow path boundary 950.
the flow path 8 is delimited radially on the outside by a compressor housing 4 which forms a radially outer flow path boundary 410.
the flow path 8 is designed as an annular space.
the inlet guide wheel 5 has stator blades or guide blades 55 which are adjustable in a staggered angle and which are arranged distributed in the circumferential direction in the flow path 8.
the guide vanes 55 each have a front edge 551 and a rear edge 552.
the swirl in the flow is increased by the inlet guide wheel 5, and the subsequent rotor 6 is thus striven for in a more effective manner.
the rotor 6 comprises a series of rotor blades or rotor blades 60, which extend radially in the flow path 8.
the guide vanes 55 are rotatably mounted to adjust the stagger angle. For this purpose, they are each connected to a spindle 25 in a rotationally fixed manner or formed integrally with one.
the spindle 25 has an axis of rotation which is equal to the axis of rotation of the guide vane 55.
the spindle 25 is accessible and adjustable from outside the flow path 8.
the guide vane 55 is connected at its radially outer end to an outer circular platform 75 which forms a turntable and is connected to a radially outer spindle section 251 of the spindle 25.
the platform 75 and the spindle section 251 are mounted in a housing cover band 420, which is part of the compressor housing 4.
the The guide vane 55 is connected at its radially inner end to an inner circular platform 78, which forms a further turntable and is connected to a radially inner spindle section 252 of the spindle 25.
the platform 78 and the spindle section 252 are supported in an inner shroud 910 which locally forms the inner flow path boundary 950.
the guide vanes 55 In order to enable the guide vanes 55 to rotate or the stagger angle to be adjustable, it is necessary for the guide vanes 55 to form recesses 553, 554 in the region of their rear edge 552 radially adjacent to the outer flow path boundary 410 and radially adjacent to the inner flow path boundary 950 that the guide vanes 55 each form a partial gap 81 for the radially outer flow path boundary 410 and a partial gap 82 for the radially inner flow path boundary 950 in their axially rearward region. This prevents that when the guide vane 55 is adjusted by rotation about the axis of rotation, it collides with the outer flow path boundary 410 and / or with the inner flow path boundary 950.
the gaps 81, 82 are referred to as partial gaps since they do not extend over the entire axial length of the guide vanes 55.
the guide vanes 55 are formed at their radially inner end without a shroud, for which case they end freely floating with the formation of a continuous gap radially spaced from the inner flow path boundary 95.
partial gaps are formed in the region of the front edge 51 or both in the region of the front edge 51 and in the region of the rear edge 52.
the Figure 12 shows the arrangement of guide vane 55, outer and inner platforms 75, 78 and spindle 25 of the Figure 11 in an enlarged view.
the undercuts 553, 554 create the partial gaps 81, 82 for the outer or inner flow path boundary.
the partial gaps 81, 82 have a gap volume which is defined by the axial length and the radial height of the partial gaps 81, 82 or the undercuts 553, 554 forming them.
the radial height r of the partial gap and / or the axial length x of the partial gap can be varied to vary the partial gap 81 and / or the partial gap 82 in different blocks which form the guide vanes 55 of the guide wheel 5.
the first variation V1 is carried out at the upper partial gap 81, which can alternatively or simultaneously take place at the lower partial gap 82.
the radial height of the partial gap 81 is increased by making the undercut 553 ′ lower.
the second variation V2 is carried out at the lower partial gap 82, which can alternatively or simultaneously also take place at the upper partial gap 81.
the axial length of the partial gap 81 is increased in that the diameter of the lower platform 78 is reduced and at the same time the undercut 554 has a greater axial length.
the variations shown can also be combined, i. H. the upper partial gap 81 and / or the lower partial gap 82 are varied by a changed axial length and a changed radial height.
FIG. 13 Two exemplary embodiments are explained below in which the paddle wheels form blocks with differently configured partial gaps.
the basic arrangement corresponds to that of Figure 5 , wherein a blade wheel arrangement for a compressor has a rotor 6, a variable stator 5 arranged upstream of the rotor 6 and a variable stator 7 arranged downstream of the rotor 6.
the upstream stator 5 is an inlet stator.
FIG 14 a sequence of stator 5, rotor 6 and stator 7 embedded in a compressor is shown.
the inlet guide wheel 5 is first considered.
This has N blocks of blades, blades of two blocks, namely the blocks B j and B k, being shown.
the individual blocks comprise in the representation of the Figure 13 two blades 56, 57 each. This is only to be understood as an example.
the blocks B j and B k differ in the partial gaps which the blades 56, 57 form in relation to the adjacent flow path boundary.
the partial gaps 811 of the blades 56 of the block B j of the inlet guide wheel 5 have a larger axial one Extension to as the partial column 812 of the blades 57 of the block B k .
the gap area covered by the partial column 811 is accordingly larger than the gap area covered by the partial column 812.
modifications are also implemented in the sub-columns of the stator 7. This is subdivided into the same number N of blocks B j and B k , each with differently designed partial columns for the outer flow path boundary and / or for the inner flow path boundary. Alternatively, modifications in the sub-columns are only realized for the stator 7.
the partial gaps 813 of the blades 76 of the block B j of the stator 7 have a smaller axial extent than the partial gaps 814 of the blades 77 of the block B k .
the gap area covered by the partial column 813 is accordingly smaller than the gap area covered by the partial column 814.
the assignment of the partial columns between the blocks of the inlet guide wheel 5 and the blocks of the stator 7 is offset, ie blocks with larger partial columns 811 of the inlet guide wheel 5 are assigned blocks 813 with smaller partial columns 813 of the stator 7 and vice versa.
sub-column 811, 812, 813, 814 also has a radial variation, as shown schematically in FIG Figure 12 shown, can have. In the sectional view of the Figures 13 and 14 such a radial variation is not discernible.
a further variation can consist in that the partial gaps are not realized in the area of the rear edge of the blades, but in the area of the front edge of the blades, or both in the area of the rear edge and in the area of the front edge of the blades.
the Figure 14 shows in the blade profile a blade wheel arrangement which comprises two variable stators 5, 7 embedded in a compressor and a rotor 6 arranged in between.
the inlet guide wheel 5 has N blocks of blades, blades of two blocks, namely the blocks B j and B k, being shown.
the individual blocks comprise in the representation of the Figure 14 Two blades 58, 59 each. With regard to the size of the individual blocks B j and B k , the explanations for Figure 13 in a corresponding manner.
the blocks B j and B k differ in the partial gaps which the blades 58, 59 form in relation to the adjacent flow path boundary.
the partial gaps 815 of the blades 58 of the block B j of the stator 5 have a smaller axial extension than the partial gaps 816 of the blades 59 of the adjacent block B k .
the gap area covered by the partial column 815 is accordingly smaller than the gap area covered by the partial column 816.
modifications are also implemented in the partial columns in the stator 7. This is subdivided into the same number N of blocks B j and B k , each with differently designed partial columns for the outer flow path boundary and / or for the inner flow path boundary. Alternatively, modifications in the partial columns are only realized in the stator 7.
the stator 7 is in the same way as the stator 7 Figure 13 educated.
the partial gaps 813 of the blades 76 of the block B j of the stator 7 have a smaller axial extent than the partial gaps 814 of the blades 77 of the block B k .
the gap area covered by the partial column 813 is accordingly smaller than the gap area covered by the partial column 814.
the assignment of the partial columns between the blocks of the inlet guide wheel 5 and the blocks of the stator 7 is such that blocks with smaller partial columns 815 of the stator 5 are assigned blocks 813 with smaller partial columns 813 of the stator 7 and blocks with larger partial columns 816 of the stator 5 blocks associated with larger sub-columns 814 of the stator 7.
the Figure 10 shows schematically the advantages achieved by the present invention.
the aerodynamic damping as a function of the knot diameter is specified.
the blade rows form cyclic overall vibration forms, which are characterized by node lines.
the maximum number of knot lines is equal to half of the blades for an even number of blades and minus one for half of the blades for an odd number of blades.
the deflection in a node line is zero.
the knot diameter is determined by the knot pattern.
bar X1 shows vibration excitations without implementation of the invention and bar X2 vibration excitations with implementation of the invention.
Another knot pattern has been created by the invention, in which the aerodynamic damping is increased, so that the build-up of a rotating tear is effectively prevented.
the individual blocks implement more than two different blade entry angles and / or blade exit angles, that is to say, for example, a total of 6 blocks are provided, two of which have a first blade entry angle and / or blade exit angle, and two more have a second blade entry angle and / or blade exit angle have, and two more have a third blade entry angle and / or blade exit angle.
the blade entry angle and / or blade exit angle between adjacent blocks does not change discretely, but continuously, for example in accordance with the shape of a sine curve.
any of the described features can be used separately or in combination with any other features, provided that they are not mutually exclusive.
the disclosure extends to, and encompasses, all combinations and sub-combinations of one or more features described herein. If areas are defined, they include all values within these areas as well as all sub-areas that fall within one area.

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Engineering & Computer Science (AREA)
Mechanical Engineering (AREA)
General Engineering & Computer Science (AREA)
Physics & Mathematics (AREA)
Fluid Mechanics (AREA)
Geometry (AREA)
Structures Of Non-Positive Displacement Pumps (AREA)

EP19190987.8A 2018-08-14 2019-08-09 Roue à aubes d'une turbomachine Active EP3611387B1 (fr)

Priority Applications (1)

Application Number	Priority Date	Filing Date	Title
EP21195914.3A EP3940200B1 (fr)	2018-08-14	2019-08-09	Roue à aubes d'une turbomachine

Applications Claiming Priority (1)

Application Number	Priority Date	Filing Date	Title
DE102018119704.7A DE102018119704A1 (de)	2018-08-14	2018-08-14	Schaufelrad einer Strömungsmaschine

Related Child Applications (1)

Application Number	Title	Priority Date	Filing Date
EP21195914.3A Division EP3940200B1 (fr)	2018-08-14	2019-08-09	Roue à aubes d'une turbomachine

Publications (3)

Publication Number	Publication Date
EP3611387A2 true EP3611387A2 (fr)	2020-02-19
EP3611387A3 EP3611387A3 (fr)	2020-05-06
EP3611387B1 EP3611387B1 (fr)	2021-10-06

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EP19190987.8A Active EP3611387B1 (fr)	2018-08-14	2019-08-09	Roue à aubes d'une turbomachine
EP21195914.3A Active EP3940200B1 (fr)	2018-08-14	2019-08-09	Roue à aubes d'une turbomachine

Family Applications After (1)

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EP21195914.3A Active EP3940200B1 (fr)	2018-08-14	2019-08-09	Roue à aubes d'une turbomachine

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US (2)	US11105207B2 (fr)
EP (2)	EP3611387B1 (fr)
DE (1)	DE102018119704A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
CN113685363A (zh) *	2020-05-18	2021-11-23	中国航发商用航空发动机有限责任公司	多级轴流压气机叶片设计方法
FR3144634A1 (fr) *	2023-01-04	2024-07-05	Safran Aircraft Engines	aubage amélioré pour compresseur de turbomachine.

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
FR3094746B1 (fr) *	2019-04-03	2021-03-05	Safran Aircraft Engines	Aube de stator a calage variable pour une turbomachine d’aeronef
JP7363328B2 (ja) *	2019-10-09	2023-10-18	ニデック株式会社	インペラおよび軸流ファン
IT202000004585A1 (it) *	2020-03-04	2021-09-04	Nuovo Pignone Tecnologie Srl	Turbina e pala perfezionate per la protezione della radice dai gas caldi del percorso del flusso.
US12091178B2 (en)	2022-05-30	2024-09-17	Pratt & Whitney Canada Corp.	Aircraft engine with stator having varying geometry
US11939886B2 (en)	2022-05-30	2024-03-26	Pratt & Whitney Canada Corp.	Aircraft engine having stator vanes made of different materials
US12017782B2 (en)	2022-05-30	2024-06-25	Pratt & Whitney Canada Corp.	Aircraft engine with stator having varying pitch
US12078189B2 (en)	2022-08-09	2024-09-03	Pratt & Whitney Canada Corp.	Variable vane airfoil with recess to accommodate protuberance

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE1503520A1 (de) *	1965-09-22	1970-02-26	Daimler Benz Ag	Schaufelrad von Axial- oder Radialverdichtern
US6379112B1 (en) *	2000-11-04	2002-04-30	United Technologies Corporation	Quadrant rotor mistuning for decreasing vibration
FR2824597B1 (fr) *	2001-05-11	2004-04-02	Snecma Moteurs	Reduction de vibrations dans une structure comprenant un rotor et des sources de perturbation fixes
US8613596B2 (en) *	2009-12-28	2013-12-24	Rolls-Royce Corporation	Vane assembly having a vane end seal
EP2623793B1 (fr) *	2012-02-02	2016-08-10	MTU Aero Engines GmbH	Turbomachine avec grille d'aubes
JP2013177816A (ja) *	2012-02-28	2013-09-09	Hitachi Ltd	軸流ターボ機械
US20140286758A1 (en) *	2013-03-19	2014-09-25	Abb Turbo Systems Ag	Nozzle ring with non-uniformly distributed airfoils and uniform throat area
DE102013224081B4 (de) *	2013-11-26	2015-11-05	Man Diesel & Turbo Se	Verdichter
DE102014203605A1 (de) *	2014-02-27	2015-08-27	Rolls-Royce Deutschland Ltd & Co Kg	Schaufelreihengruppe
US9631504B2 (en) *	2014-04-02	2017-04-25	Solar Turbines Incorporated	Variable guide vane extended variable fillet
DE102016212767A1 (de) *	2016-07-13	2018-01-18	MTU Aero Engines AG	Verstellbares Turbomaschinen-Schaufelgitter
US10526905B2 (en) *	2017-03-29	2020-01-07	United Technologies Corporation	Asymmetric vane assembly
GB201719538D0 (en) *	2017-11-24	2018-01-10	Rolls Royce Plc	Gas turbine engine
US10436035B1 (en) *	2018-07-03	2019-10-08	Rolls-Royce Plc	Fan design
DE102018117884A1 (de) *	2018-07-24	2020-01-30	Rolls-Royce Deutschland Ltd & Co Kg	Strukturbaugruppe für einen Verdichter einer Strömungsmaschine

2018
- 2018-08-14 DE DE102018119704.7A patent/DE102018119704A1/de not_active Withdrawn
2019
- 2019-08-09 EP EP19190987.8A patent/EP3611387B1/fr active Active
- 2019-08-09 EP EP21195914.3A patent/EP3940200B1/fr active Active
- 2019-08-13 US US16/539,688 patent/US11105207B2/en active Active
2021
- 2021-07-15 US US17/376,632 patent/US11391169B2/en active Active

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
CN113685363A (zh) *	2020-05-18	2021-11-23	中国航发商用航空发动机有限责任公司	多级轴流压气机叶片设计方法
FR3144634A1 (fr) *	2023-01-04	2024-07-05	Safran Aircraft Engines	aubage amélioré pour compresseur de turbomachine.

Also Published As

Publication number	Publication date
EP3940200A1 (fr)	2022-01-19
US11105207B2 (en)	2021-08-31
US20200056486A1 (en)	2020-02-20
DE102018119704A1 (de)	2020-02-20
EP3611387A3 (fr)	2020-05-06
US11391169B2 (en)	2022-07-19
EP3611387B1 (fr)	2021-10-06
EP3940200B1 (fr)	2024-03-13
US20210340875A1 (en)	2021-11-04

Publication	Publication Date	Title
EP3611387B1 (fr)	2021-10-06	Roue à aubes d'une turbomachine
EP3591237B1 (fr)	2021-05-19	Module structural pour un compresseur d'une turbomachine
DE69515624T2 (de)	2000-09-07	Compressorgehäuse mit Rezirkulationskanälen
EP3715586B1 (fr)	2023-05-03	Pale d'aube de rotor d'une turbomachine
DE102018133388A1 (de)	2020-06-25	Planetengetriebe und Verfahren zur Montage eines Planetengetriebes
DE102019117038A1 (de)	2020-12-31	Getriebe und Gasturbinentriebwerk
EP3599349A1 (fr)	2020-01-29	Module structural avec aubes à calage variable inclinées pour un compresseur d'une turbomachine
DE102019110834A1 (de)	2020-10-29	Zapfluftentnahmevorrichtung für ein Gasturbinentriebwerk
EP3428393A1 (fr)	2019-01-16	Roue aubagée d'une turbomachine
EP3543481B1 (fr)	2020-10-28	Turbomoteur à gaz et procédé d'introduction de l'huile dans un agencement de transmission
EP4477839A2 (fr)	2024-12-18	Procédé de détermination de la forme d'une aube désaccordée d'une roue porteuse d'une turbomachine
WO2021019030A1 (fr)	2021-02-04	Roue dentée
WO2020200892A1 (fr)	2020-10-08	Dispositif de fixation de plaques d'étanchéité entre les éléments structuraux d'un turbomoteur à gaz
DE102019116974A1 (de)	2020-12-24	Getriebe und Gasturbinentriebwerk
DE102019106633A1 (de)	2019-09-26	Getriebe und Gasturbinentriebwerk
EP4034756B1 (fr)	2024-04-24	Turbine à gaz d'aéronef comprenant une transmission
DE102018119463B4 (de)	2023-12-28	Labyrinthdichtungssystem und Gasturbinentriebwerk mit einem Labyrinthdichtungssystem
WO2021008901A1 (fr)	2021-01-21	Accouplement d'arbres pourvu d'une denture emboîtable
DE102018130298A1 (de)	2020-06-04	Baugruppe mit einem Ausgangsleitrad für ein Turbofantriebwerk und Turbofantriebwerk mit einer solchen Baugruppe
DE102019106999A1 (de)	2020-09-24	Stirnradgetriebe und Planetengetriebe mit einem derartigen Stirnradgetriebe
DE102020122418A1 (de)	2021-12-23	Planetengetriebe
DE102020113053A1 (de)	2020-11-26	Gasturbinentriebwerk
DE102020116785B4 (de)	2025-01-23	Strukturbaugruppe für ein Gasturbinentriebwerk
DE102018108753A1 (de)	2019-10-17	Verfahren zur Herstellung einer Verzahnung und Verzahnung
WO2022101029A1 (fr)	2022-05-19	Roue à aubes directrices d'une turbomachine

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EP3611387A2 - Roue à aubes d'une turbomachine - Google Patents

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