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EP2746538B1 - Befestigungsplatte einer Statorschaufel eines Turbotriebwerks mit internen Ausparungen - Google Patents

Befestigungsplatte einer Statorschaufel eines Turbotriebwerks mit internen Ausparungen Download PDF

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Publication number
EP2746538B1
EP2746538B1 EP12199336.4A EP12199336A EP2746538B1 EP 2746538 B1 EP2746538 B1 EP 2746538B1 EP 12199336 A EP12199336 A EP 12199336A EP 2746538 B1 EP2746538 B1 EP 2746538B1
Authority
EP
European Patent Office
Prior art keywords
rectifier
blade
accordance
blades
tongue
Prior art date
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.)
Active
Application number
EP12199336.4A
Other languages
English (en)
French (fr)
Other versions
EP2746538A1 (de
Inventor
Christophe Remy
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.)
Safran Aero Boosters SA
Original Assignee
Techspace Aero SA
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.)
Filing date
Publication date
Application filed by Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP12199336.4A priority Critical patent/EP2746538B1/de
Priority to CA2836434A priority patent/CA2836434A1/en
Priority to RU2013156800A priority patent/RU2671260C2/ru
Priority to US14/136,070 priority patent/US9771815B2/en
Priority to CN201310757394.0A priority patent/CN103899579B/zh
Publication of EP2746538A1 publication Critical patent/EP2746538A1/de
Application granted granted Critical
Publication of EP2746538B1 publication Critical patent/EP2746538B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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

Definitions

  • the invention relates to an axial turbomachine compressor stator. More particularly, the invention relates to an axial turbomachine compressor stator blade retainer retainer. The invention also relates to an axial turbomachine.
  • an axial turbomachine In order to guide an annular flow, an axial turbomachine is provided with coaxial ferrules delimiting the inside and the outside of the flow.
  • the inner ferrules In a rectifier, the inner ferrules are essentially connected to the inner ends of the stator vanes. They form cylindrical walls having openings in which are introduced the ends of the stator blades for anchoring.
  • the rectifiers have on the one hand layers of abradable material applied at the inner rings, and wipers on the rotor on the other hand.
  • the rotor moves and deforms so that the radial ends of the wipers touch the associated abradable layers. They hollow out annular furrows, which thus materialize labyrinthine joints.
  • the inner ends of the blades extend into and anchored in the layers of abradable material. They have openings in the layers of abradable material in which retention pieces are placed.
  • the document EP 2 072 760 A1 discloses a turbojet axial compressor rectifier.
  • the rectifier comprises a plurality of blades bonded to an outer shell and an inner shell.
  • the outer shell has openings traversed by blade loops, said loops surrounding blade openings receiving curved plates spring effect to connect the outer ring blades.
  • the bent plates have notches for holding in position each bent plate.
  • such curved plates are difficult to introduce into the blade openings, and penalize the radial compactness of the rectifier.
  • the document EP 1 213 483 B1 discloses a rectifier stage whose blade ends are connected two by two by retention and stiffening parts. They have V-shapes and are inserted into openings formed in the ends of the blades. When inserted, the branches of the V are folded so that their ends can enter the openings.
  • this mounting method requires that the mounting piece has a significant length along the axis of the rectifier. This configuration may become incompatible with some internal rectifier shrouds that are narrow.
  • the mounting of such a retention piece requires great attention to manually position each end of the branches of the V in the corresponding openings. After mounting, the tip of the V may protrude from the layer of abradable material in which it is supposed to remain embedded.
  • the document EP 1 626 163 A2 presents a blade retention clip to a ferrule of a rotating machine.
  • the clip is inserted into an opening formed at the end of a blade and is embedded in a layer of abradable material applied inside the shell.
  • the clip forms a rectangular plate with an L-shaped deformable side member.
  • the free end of the latter has a hook cooperating with a narrow band of blade material.
  • This narrow band of material engages the opposite side of the hook in a notch formed in the body of the clip.
  • This clip can effectively fix a blade to a shell.
  • it necessarily requires an elastic material for its realization.
  • it has a large axial space to be able to deform and be mounted on blades with a pronounced pitch angle.
  • This type of clip also requires a high accuracy of assembly to present it in the right axis, so that a hook engages properly.
  • the engagement movement of the hook must be gentle so as not to degrade the elastic element because of its fineness.
  • the combination of notch and hook at the end of the side element deformable does not allow to firmly lock the clip in a given orientation.
  • the clip can rotate and protrude from the layer of abradable material, especially when its covering thickness is reduced.
  • a blade retaining plate which comprises a folding finger.
  • This plate is intended to be inserted into the orifices of two neighboring blades, the finger extending between them. To ensure maintenance, this finger is folded towards the plate, against one of the blades. This operation requires a certain thoroughness to carefully bend the finger. This one is particularly fine, which weakens it. Also, this finger is arranged towards the outside. The position of its end is not controlled, it can emerge from a layer of annular abradable material. As it comes out, it can come into contact with the wipers of the rotor.
  • the invention aims to solve at least one of the problems raised by the prior art.
  • the invention also aims to propose another mode of locking a blade retaining piece in openings.
  • the invention also aims to improve the stability of a blade retainer.
  • Another object of the invention is to simplify the operation of mounting a blade retaining piece inside an aperture formed at the end of a blade.
  • the invention also aims to reduce the size of a blade retainer.
  • the invention relates to an axial turbomachine rectifier comprising: an inner ring with an annular row of openings; an annular row of blades, said blades extending substantially radially through said openings, respectively, and each having an opening on the inner side of the shell; at least one blade retainer insert inserted in at least one of the openings, with means for locking said insert in the perforation (s); remarkable that the locking means comprise at least one tongue with an end forming a bearing surface in contact with a portion of the blade or one of the blades, located radially to the right of the corresponding aperture.
  • the rectifier comprises a layer of abradable material applied inside the inner shell which envelops the retaining plate or plates.
  • the retaining plate is predominantly made of a metallic material such as a steel alloy, an aluminum alloy, or a titanium alloy.
  • the elongation of the retaining plate is between 10 mm and 150 mm, preferably between 30 mm and 100 mm, more preferably between 40 mm and 70 mm.
  • the width of the retaining plate in its transverse direction is between 5 mm and 40 mm, preferably between 10 mm and 30 mm, more preferably between 15 mm and 20 mm.
  • the bearing surface can be curved so as to match a blade surface which can be concave or convex.
  • the or at least one bearing surface forms a bearing line.
  • the portion of the blade or one of the blades, in contact with the bearing surface of the or one of the tongues is located between the aperture and the inner shell.
  • the bearing surface extends along the blade substantially parallel to the average plane of the wafer.
  • the tongue or tabs are able to deform substantially along a major axial deformation axis.
  • the tongue or tabs are elastically deformable so as to take its or their support position after inserting the wafer in the or openings.
  • the tongue or tabs are plastically deformable so as to allow it or their establishment from a position substantially in the extent of the or platelets.
  • the tongue or tabs are integral with the wafer and cut into said wafer, the cutout being preferentially in the general shape of U.
  • the edges of the tongue or tongues are inscribed in the contour of the retaining plate, said edges preferably being at a distance from said contour.
  • the or at least one of the plates passes through the openings of at least two consecutive blades, and preferably comprises two tongues arranged in opposite directions.
  • the two tabs cooperate, each and respectively, with the face of each of the two blades which is vis-à-vis the other of the two blades.
  • the two tabs cooperate, each and respectively, with the face of each of the two blades which is opposite to the other of the two blades.
  • the rectifier comprises at least two tongues arranged in opposite directions, said two tongues cooperating, each and respectively, with each of the two faces of the blade or one of the blades.
  • the wafer has an end configured to abut against a face of the blade or one of the blades, the tongue being in contact with the opposite face of said blade or with the corresponding face of another of the blades.
  • the bearing surface of the tongue or tongues contacts the corresponding blade via an elastomeric material applied to said blade at the corresponding opening in the ferrule, said elastomer providing a fastening function said blade to the ferrule and / or a sealing function between said blade and the ferrule.
  • the invention also relates to a turbomachine comprising a rectifier, remarkable in that the rectifier is in accordance with the invention.
  • the invention provides a blade retainer whose stability is improved. Its positioning accuracy is too.
  • the locking means allow through the support surface to provide a blocking function and also orientation, which simplifies the retaining piece.
  • the stability of the retainer is also improved when in contact with only one blade.
  • the editing operation is simplified.
  • the locking operation of the retaining piece is assisted by the abutment surface against which abut the locking means. Their gathered shape helps strengthen them, and reduce the size of the openings.
  • the retaining piece is suitable for small rectifiers, as its adaptation will not weaken the locking means.
  • the invention makes it possible to dispense with fastening means such as hooks that require a certain minutia to be able to engage on a blade.
  • fastening means such as hooks that require a certain minutia to be able to engage on a blade.
  • the manual assembly of the retention room will be simple, regardless of the size of the blade.
  • inner and outer refer to a positioning relative to the axis of rotation of an axial turbomachine.
  • the figure 1 schematizes an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6.
  • Reducing means can increase the speed of rotation transmitted to the compressors.
  • the different turbine stages can each be connected to the compressor stages via concentric shafts.
  • the latter comprise several rows of rotor blades associated with rows of stator vanes. The rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 10.
  • a commonly designated fan inlet fan 16 is coupled to the rotor 12 and generates a flow of air which is divided into a primary flow 18 passing through the various levels mentioned above of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the turbine outlet.
  • the primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine.
  • the casing has cylindrical walls or ferrules which can be internal and external.
  • the figure 2 is a sectional view of a low-pressure compressor 4 of an axial turbomachine 2 such as that of the figure 1 . There can be observed a portion of the fan 16 and the separation nozzle 22 of the primary flow 18 and the secondary flow 20.
  • the rotor 12 comprises several rows of rotor blades 24, for example three.
  • the low pressure compressor 4 comprises several rectifiers, for example four, each containing a row of stator vanes 26 and an inner ferrule 28 fixed to the vanes.
  • the rectifiers are associated with the fan 16 or a row of rotor vanes to straighten the air flow, so as to convert the speed of the flow into pressure.
  • the stator vanes 26 extend substantially radially from an outer casing, and can be attached thereto by means of an axis. They are regularly spaced from each other, and have the same angular orientation in the flow. Advantageously, these vanes are identical. Optionally, the spacing between the blades may vary locally as well as their angular orientation. Some blades may be different from the rest of the blades in the row.
  • Each inner shell 28 has a U-shaped section whose hollow receives a layer of abradable material 30.
  • the ends of the blades are engaged. They present crossing openings.
  • the openings are partially filled with abradable material 30. They can be substantially aligned in an annular manner, or form several annular sets of axially offset openings. A radial offset may be provided for one of the games.
  • the figure 3 is a sectional view of the rectifier according to a first embodiment along the axis 3-3 drawn on the figure 2 .
  • the rectifier may be a low pressure compressor upstream rectifier.
  • the rectifier comprises at least one retaining piece 36 of vanes.
  • each blade is connected to a retaining piece.
  • the retaining piece 36 has a wafer shape, preferably flat.
  • the retaining piece 36 is a plate.
  • the retaining piece 36 comprises a body. Its thickness is generally constant. It has a main elongation and a transverse direction that is perpendicular to its main elongation. It has a general shape of parallelogram, preferably of rectangle. It has a main surface.
  • the retaining piece 36 is introduced into at least one blade aperture 34, preferably at least two openings.
  • the number of retaining pieces 36 may be equal to that of the stator vanes 26 of the stator, or may be less than or equal to half the number of stator vanes 26.
  • the retaining piece 36 is arranged so that its main surface is substantially perpendicular to the radial direction of the rectifier. Its main elongation is arranged perpendicular to the surface of the end of the blade 32. In this way, it optimizes the retention and anchoring of the blades according to their heights.
  • the retaining piece 36 is slid into one or more openings 34 before the application phase of the layer of abradable material 30. To remain in position during this phase, it comprises locking means in the form of tongue 38.
  • the tabs 38 are inclined so as to bear against at least one blade, while facilitating their introduction, their adjustment.
  • the tongues 38 each comprise an elongate bearing surface 40 which cooperates with a respective stator blade 26.
  • the tongues 38 extend radially, preferably in the direction of the inner ferrule 28.
  • the or at least one of the bearing surfaces are at a distance from the body of the wafer.
  • the tongues 38 can be bent. Elbows can be made along their length to make them more flexible. Thus, the positions of the bearing surfaces 40 can be adjusted more easily.
  • the use of an elongated surface for the support surface provides more stability than points of contact.
  • the elongation of the bearing surface or surfaces 40 is generally axial, this direction corresponding to the axis in which the retaining piece 36 is likely to pivot when it is placed only in an aperture. In a configuration where the abradable layer has a riser at a height of a retaining piece 36, it will not run over and beyond the abradable layer.
  • the locking means therefore make it possible to reduce the mobility of the retaining piece 36 in its aperture (s) 34. They also make it possible to block it. They can be configured to block the retaining piece 36 in translation along at least one direction, preferably in three orthogonal directions. They can be configured to lock the retaining piece 36 in rotation along at least one axis, preferably along three orthogonal axes.
  • the body of the retaining piece 36 can bear against the contour of at least one aperture 34 of a blade, which contributes to the positioning, and possibly the locking of the retaining piece 36.
  • the width of the piece of Retention 36 can be substantially adjusted to the width of the openings 34.
  • the height of the retaining piece 36 measured at its locking means 38 is greater than that of the height of the openings 34.
  • the thickness of the body of the room Retention 36 may be substantially less than the height of the openings 34.
  • the locking means 38 may cooperate with the same stator blade 26, or with at least two stator blades 26 adjacent.
  • the rectifier may comprise an elastomeric material 42 disposed to the interface between a blade 26 and its opening of the inner shell 28.
  • the elastomeric material is disposed at each interface between the blades and their respective openings.
  • This elastomeric material 42 provides positioning and sealing functions. It can be made of silicone material. It forms a bead extending inwards.
  • this bead forms chamfers around the stator vane 26. The chamfers are configured so that the bearing surfaces 40 come into contact with them when the tongues 38 are deployed. The surface of one of the chamfers is incident to the arc that can sweep a bearing surface 40 during the operation of the tongue 38 associated.
  • the retaining piece 36 is produced or supplied having its locking means 38 substantially housed in the thickness of its body. They are folded. During assembly of the retaining piece 36, it is introduced into an aperture 34, then its locking means 38 are deformed plastically by an operator until coming into contact with the blade. They are then deployed. The tongue or tabs are folded. This mounting operation is simple to perform because the operator performs a deformation movement by pressing radially on the locking means 38. They are easily accessible from the outside. This operation requires little precision, and little attention to detail. The positioning and locking of the retaining piece 36 are quickly performed.
  • the retaining piece is produced or supplied with its blocking means deployed. They protrude from the body of the retainer. During assembly, the retaining piece is introduced into at least one aperture, and its locking means deform elastically. Once the retaining piece 36 occupies its final place, the locking means 38 cooperate with the blade and position the retaining piece 36 while allowing to maintain the orientation along at least one axis of rotation.
  • the locking means 38 may comprise first locking means and second locking means each having a bearing surface 40.
  • the bearing surfaces 40 are oriented in directions different, preferentially opposed.
  • the bearing surfaces 40 of the first and second locking means each cooperate with a different blade.
  • the figure 4 represents a plan view of the blade retainer 36 according to the first embodiment of the invention.
  • the locking means 38 are cut in the body of the retaining piece 36. Their contours may correspond locally to the contour of the retaining piece 36, or may be distant from the contours of the retaining piece 36.
  • the cutout 44 of the locking means 38 can be substantially an "L” or a "U”.
  • the locking means 38 may comprise two tabs 38, preferably rectangular. They each have a main direction. Each tongue has two opposite sides, one being connected to the body, the other comprising the bearing surface 40. The latter has a length greater than 3.00 mm, preferably greater than 5.00 mm, more preferably greater than 12.00 mm. The length of the bearing surface represents more than 10% of the elongation of the retaining piece 36, preferably more than 20%, more preferably more than 30%. These proportions improve the stability of the retaining piece 36 with respect to the blade or blades to which it is positioned, in particular because of the mechanical clearances.
  • This form of retaining piece 36 is particularly suitable for anchoring for two neighboring blades. It can also serve as anchor for at least a third dawn neighbor. For this, simply lengthen it accordingly.
  • the figure 5 represents a plan view of a blade retaining piece according to a second embodiment of the invention. This figure 5 resumes the numbering of the preceding figures for identical or similar elements, the numbering however being incremented by 100.
  • the retaining piece 136 has a general shape of rectangle. Its first and second locking means 138 extend towards each other following the extension of the retaining piece 136. They are in elevation on the same side of the body of the retaining piece 136.
  • the means locking members comprise two tabs 138 whose cutouts 144 are distant, or joined so as to achieve a manufacturing economy.
  • This retaining piece 136 is adapted to be mounted on the same blade, its blocking means 138 manage to ensure blocking and stability with a single blade. By lengthening it, this retaining piece 136 can also ensure the anchoring of other neighboring blades.
  • the figure 6 is a plan view of a blade retainer according to a third embodiment of the invention. This figure 6 resumes the numbering of the preceding figures for identical or similar elements, the numbering however being incremented by 200. Specific numbers are created for the new elements.
  • the retaining piece 236 has an end 246 configured to abut against the stator vane, and ensure a locking in combination with a tongue 238.
  • the end may have stops such as lateral shoulders. These latter each comprise a discontinuous bearing surface 240.
  • the bearing surfaces 240 of the tongue 238 and the shoulders are arranged at different heights relative to the body of the retaining piece 236. The locking in a given orientation is more stable.
  • the shoulder and the tongue 238 are robust, they are not likely to be damaged during assembly.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (15)

  1. Gleichrichter einer axialen Turbomaschine (2), bestehend aus:
    - einem inneren Mantel (28) mit einer ringförmigen Reihe von Öffnungen;
    - einer ringförmigen Reihe von Leitschaufeln (26), die sich im Wesentlichen jeweils radial durch die genannten Öffnungen hindurch erstrecken und jeweils einen Durchbruch (34) auf der Innenseite des Mantels aufweisen;
    - mindestens einer Befestigungsplatte (36; 136; 226) für Leitschaufeln, die in mindestens einen der Durchbrüche (34) eingefügt ist, mit Mitteln für die Befestigung der genannten Platte in dem Durchbruch oder den Durchbrüchen;
    dadurch gekennzeichnet, dass
    die Befestigungsmittel mindestens eine Feder (38; 138; 238) beinhalten, deren eines Ende eine Auflagefläche (40; 140; 240) bildet, die mit einem Abschnitt der Leitschaufel (26) oder einer der Leitschaufeln (26), die sich radial von dem entsprechenden Durchbruch aus erstrecken, in Kontakt steht.
  2. Gleichrichter nach Anspruch 1, dadurch gekennzeichnet, dass der Abschnitt der Leitschaufel (26) oder einer der Leitschaufeln (26), die mit der Auflagefläche (40; 140; 240) der Feder oder einer der Federn (38; 138; 238) in Kontakt stehen, zwischen dem Durchbruch (34) und dem inneren Mantel (28) angeordnet ist.
  3. Gleichrichter nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, dass sich die Auflagefläche (40; 140; 240) im Wesentlichen parallel zur durchschnittlichen Ebene der Befestigungsplatte (36; 136; 236) entlang der Leitschaufel erstreckt.
  4. Gleichrichter nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Federn (38; 138; 238) in der Lage sind, sich im Wesentlichen entlang einer überwiegend axialen Verformungsachse zu verformen.
  5. Gleichrichter nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die Feder(n) (38; 138; 238) in der Weise elastisch verformbar ist/sind, dass sie nach dem Einführen der Platte (36; 136; 236) in der Lage ist/sind, ihre Auflageposition in dem Durchbruch oder in den Durchbrüchen einzunehmen.
  6. Gleichrichter nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die Feder(n) (38; 138; 238) in der Weise elastisch verformbar ist/sind, dass sie ihre Einsetzung anhand einer Position ermöglicht/ermöglichen, die sich im Wesentlichen in der Ausdehnung der Platte (36; 136; 236) befindet.
  7. Gleichrichter nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die Feder(n) (38; 138; 238) aus dem gleichen Material besteht/bestehen, wie die Platte (36; 136; 236) und aus der genannten Platte ausgeschnitten ist/sind, wobei der Ausschnitt vorzugweise die allgemeine Form eines "U" besitzt.
  8. Gleichrichter nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass die Ränder der Feder(n) (38; 138; 238) der Kontur der Platte (36; 136; 236) folgen, wobei die genannten Ränder vorzugsweise einen Abstand zu der genannten Kontur aufweisen.
  9. Gleichrichter nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass die Platte oder mindestens eine der Platten (36; 136; 236) die Durchbrüche (34) von mindestens zwei aufeinanderfolgenden Leitschaufeln (26) durchquert und vorzugsweise zwei Federn (38; 138) beinhaltet, die in entgegengesetzten Richtungen angeordnet sind.
  10. Gleichrichter nach Anspruch 9, dadurch gekennzeichnet, dass die beiden Federn (38) jeweils mit der Fläche jeder der beiden Leitschaufeln (26) zusammenwirken, die der anderen der beiden Leitschaufeln (26) gegenüberliegt (vis à vis).
  11. Gleichrichter nach Anspruch 9, dadurch gekennzeichnet, dass die beiden Federn (38) jeweils mit der Fläche jeder der beiden Leitschaufeln (26) zusammenwirken, die der anderen der beiden Leitschaufeln (26) gegenüberliegt (opposée).
  12. Gleichrichter nach einem der Ansprüche 1 bis 11, dadurch gekennzeichnet, dass er mindestens zwei Federn (13) beinhaltet, die in entgegengesetzten Richtungen angeordnet sind, wobei die beiden Federn jeweils mit jeder der beiden Seiten der Leitschaufel (26) oder einer der Leitschaufeln (26) zusammenwirken
  13. Gleichrichter nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass die Platte (236) ein Ende (246) aufweist, das so konfiguriert ist, dass es an einer Seite der Leitschaufel (26) oder einer der Leitschaufeln (26) anliegt, wobei die Feder (238) mit der gegenüberliegenden Seite der genannten Leitschaufel (26) oder mit der entsprechenden Seite einer anderen der Leitschaufeln in Kontakt steht.
  14. Gleichrichter nach einem der Ansprüche 1 bis 13, dadurch gekennzeichnet, dass die Auflagefläche der Feder(n) (38; 138; 238) die entsprechende Leitschaufel (26) anhand eines Elastomers (42) kontaktiert, das auf die genannte Leitschaufel im Bereich der entsprechenden Öffnung im Mantel (28) aufgetragen wird, wobei das genannte Elastomer (42) eine Befestigungsfunktion für die genannte Leitschaufel (26) am Mantel (28) und/oder eine Dichtungsfunktion zwischen der genannten Leitschaufel (26) und dem Mantel (28) übernimmt.
  15. Turbomaschine (2) mit einem Gleichrichter, dadurch gekennzeichnet, dass der Gleichrichter einem der Ansprüche 1 bis 14 entspricht.
EP12199336.4A 2012-12-24 2012-12-24 Befestigungsplatte einer Statorschaufel eines Turbotriebwerks mit internen Ausparungen Active EP2746538B1 (de)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP12199336.4A EP2746538B1 (de) 2012-12-24 2012-12-24 Befestigungsplatte einer Statorschaufel eines Turbotriebwerks mit internen Ausparungen
CA2836434A CA2836434A1 (en) 2012-12-24 2013-12-16 Blade-retaining plate with internal cut-outs for a turbomachine stator
RU2013156800A RU2671260C2 (ru) 2012-12-24 2013-12-20 Пластинчатый фиксатор крепления лопаток, содержащий внутренние вырезы, для статора турбомашины
US14/136,070 US9771815B2 (en) 2012-12-24 2013-12-20 Blade-retaining plate with internal cut-outs for a turbomachine stator
CN201310757394.0A CN103899579B (zh) 2012-12-24 2013-12-24 具有内部切口的用于涡轮机定子的叶片保持板

Applications Claiming Priority (1)

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EP12199336.4A EP2746538B1 (de) 2012-12-24 2012-12-24 Befestigungsplatte einer Statorschaufel eines Turbotriebwerks mit internen Ausparungen

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EP2746538A1 EP2746538A1 (de) 2014-06-25
EP2746538B1 true EP2746538B1 (de) 2016-05-18

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US (1) US9771815B2 (de)
EP (1) EP2746538B1 (de)
CN (1) CN103899579B (de)
CA (1) CA2836434A1 (de)
RU (1) RU2671260C2 (de)

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BE1022513B1 (fr) * 2014-11-18 2016-05-19 Techspace Aero S.A. Virole interne de compresseur de turbomachine axiale
BE1023367B1 (fr) * 2015-08-19 2017-02-20 Safran Aero Boosters S.A. Fixation de virole interne de compresseur de turbomachine axiale
US10767503B2 (en) * 2017-06-09 2020-09-08 Raytheon Technologies Corporation Stator assembly with retention clip for gas turbine engine
US20190078469A1 (en) * 2017-09-11 2019-03-14 United Technologies Corporation Fan exit stator assembly retention system
US11852038B2 (en) 2019-11-07 2023-12-26 Rtx Corporation Stator retention of gas turbine engine

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Also Published As

Publication number Publication date
RU2671260C2 (ru) 2018-10-30
CA2836434A1 (en) 2014-06-24
CN103899579A (zh) 2014-07-02
RU2013156800A (ru) 2015-06-27
EP2746538A1 (de) 2014-06-25
US20140178193A1 (en) 2014-06-26
CN103899579B (zh) 2018-03-27
US9771815B2 (en) 2017-09-26

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