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EP2617945B1 - Rotor pour une turbomachine et procédé de fabrication - Google Patents

Rotor pour une turbomachine et procédé de fabrication Download PDF

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Publication number
EP2617945B1
EP2617945B1 EP12152073.8A EP12152073A EP2617945B1 EP 2617945 B1 EP2617945 B1 EP 2617945B1 EP 12152073 A EP12152073 A EP 12152073A EP 2617945 B1 EP2617945 B1 EP 2617945B1
Authority
EP
European Patent Office
Prior art keywords
rotor blades
blade
rotor
group
blades
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.)
Not-in-force
Application number
EP12152073.8A
Other languages
German (de)
English (en)
Other versions
EP2617945A1 (fr
Inventor
Martin Pernleitner
Marcus Dr. Wöhler
Rudolf Stanka
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to ES12152073.8T priority Critical patent/ES2668268T3/es
Priority to EP12152073.8A priority patent/EP2617945B1/fr
Priority to US13/746,650 priority patent/US9657581B2/en
Publication of EP2617945A1 publication Critical patent/EP2617945A1/fr
Application granted granted Critical
Publication of EP2617945B1 publication Critical patent/EP2617945B1/fr
Not-in-force 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • 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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F05D2240/80—Platforms for stationary or moving 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making

Definitions

  • the invention relates to a rotor for a turbomachine, in particular for an aircraft engine.
  • the invention further relates to a method for producing a blade ring of a rotor for a turbomachine and an aircraft engine.
  • Rotors for turbomachines are known in a variety of configurations.
  • a generic rotor comprises a blade ring which has a plurality of rotor blades with blade platforms resting flush against each other.
  • the blade platforms are each arranged in the radial direction between the blade and the blade root of the individual rotor blades and form an inner boundary of the flow path through the turbomachine when the rotor is mounted.
  • the tuning of the vibration behavior of bladed rotors is of central importance for the design of a turbomachine.
  • the frequency detuning is very difficult.
  • Known frequency detuning methods provide rotor blades with different natural frequencies. This is usually done by adding or removing masses.
  • the additional material is applied as a coating on the pressure side and / or the suction side of the rotor blade in the region of the blade tip of the blade, in order to obtain differently shaped rotor blades with correspondingly different natural oscillations.
  • the US 2 271 971 A discloses a rotor for a turbine in which a plurality of blades are attached to a rotor body.
  • the blades are provided with one-sided toothed blade roots, wherein the blade roots of adjacent blades are formed in pairs mirror images of each other.
  • the rotor base body has corresponding connection structures in which the blades are arranged side by side to form a blade ring.
  • the US 2 781 998 A discloses a bladed rotor for turbines or compressors.
  • a part of the rotor blades is formed integrally with the rotor base body, while the remaining rotor blades are manufactured separately and inserted into corresponding receptacles of the rotor body. It can be provided that in each case two separate rotor blades are provided with mirror-image blade roots and pushed together into a corresponding receptacle of the rotor body.
  • a rotor for a turbomachine which has a desired vibration behavior and is easier and more reliable to produce, is inventively provided in that the blade ring comprises at least two groups of differently shaped rotor blades, each group of rotor blades blade platforms are assigned, each with a complementary Vane platform of at least one other group of rotor blades and not flush with a blade platform of the same group of rotor blades are brought into abutment.
  • Each blade platform of a first group of rotor blades has at least one peripheral recess in which a complementary marginal elevation of an adjacent blade platform of an associated second group of rotor blades is arranged in a form-fitting manner.
  • the mechanical stability of the rotor under varying operating conditions for example, under varying operating temperatures and pressures, advantageously improved becomes.
  • the rotor blades that make up the blade ring of the rotor are formed such that two identical rotor blades, which accordingly belong to the same group or the same rotor blade type and have the same blade platforms, not flush mounted side by side, in the case of a faulty arrangement, the blade platforms would not lie flush against one another and thus always leave a gap between them identical trained blade platforms of the rotor blades of a single group would remain.
  • the blade ring could also not be closed.
  • the inventive design of the rotor blades only such rotor blades can instead be arranged flush side by side, which belong to different groups and their paddle platforms on the one hand geometrically different from each other and on the other hand are complementary to each other.
  • only two different groups of rotor blades are needed.
  • an integral exchange protection in the area of the hub platform of the rotor is provided by which it is reliably impossible to arrange two identically formed rotor blades with correspondingly equal vibration behavior next to one another and to add them to the blade ring. Additional components to ensure the security against confusion are not required for this, so that the weight of the rotor is advantageously not adversely affected.
  • the invention therefore makes it possible in a structurally simple and cost-effective manner to reliably manufacture a rotor with a desired frequency detuning (detuning), in which it is reliably ruled out that two identical rotor blades are inadvertently arranged next to one another.
  • each blade platform of the first group of rotor blades a marginal recess and an opposite marginal elevation and each blade platform of the second group of rotor blades to complement the blade platform of the first group complementary marginal elevation and a survey of the Bucket platform of the first group has complementary marginal depression.
  • adjacent blade platforms can be hooked to each other at their opposite edge regions, whereby a mechanically particularly stable connection of the individual rotor blades while ensuring the swap protection is achieved.
  • the recesses and the complementary elevations are formed in the region of lateral contact surfaces of the rotor blades, wherein the elevations are arranged in a form-fitting manner in the associated recesses.
  • a particularly effective frequency detuning of the rotor is achieved in a further embodiment of the invention in that the at least two groups of rotor blades have different blade blade geometries.
  • each group of rotor blades is provided with an associated and group-specific designed blade type, wherein the blade types of different groups of rotor blades differ from each other.
  • Rotor blades with different blade geometry are also understood to mean rotor blades whose blades themselves have the same geometry, but which differ with regard to their relative arrangement with respect to the blade platform. In this case, it may be provided, for example, that the blades of different groups also differ from one another with regard to their material, their coating or any combination of these features.
  • the at least two groups of rotor blades have blade platforms with mutually corresponding lateral contact surfaces. This is a structurally particularly simple way to create an integral swap protection and to bring adjacent rotor blades as large as possible in abutment with each other.
  • the contact surfaces being inclined and / or wavy and / or serrated and / or irregular.
  • the contact surfaces can form corresponding wedge surfaces with each other, which in addition to an integral swap protection and increased friction between the rotor blades and thus a mechanically particularly stable connection of adjacent rotor blades is achieved.
  • the design of the contact surfaces is basically not limited to certain geometries. In the geometric design of the corresponding contact surfaces, it is merely necessary to ensure that the contact surfaces of one group of rotor blades can not be brought flush into contact with the corresponding contact surfaces of a further group of rotor blades but not with contact surfaces of the same group of rotor blades.
  • a further aspect of the invention relates to a method for producing a blade ring of a rotor for a turbomachine, in particular for an aircraft engine, comprising at least the steps a) providing at least two groups of differently shaped rotor blades, wherein each group of rotor blades are associated with blade platforms, each with and b) arranging the rotor blades in the form of the blade ring, wherein each complementary blade platforms of the at least two groups of rotor blades flush with each other in abutment with one another to be brought.
  • each blade platform of a first group of rotor blades has at least one marginal depression, in which a complementary marginal elevation of an adjacent blade platform of an associated second group of rotor blades is arranged positively.
  • step b) blade platforms of a first group of rotor blades and blade platforms of a second group of rotor blades are brought into contact alternately.
  • step b) blade platforms of a first group of rotor blades and blade platforms of a second group of rotor blades are brought into contact alternately.
  • a mechanically particularly stable connection of the blade ring to the rotor is made possible in a further embodiment in that blade roots of the rotor blades are arranged and fixed in step b) in a complementary groove of a rotor base body.
  • the blade roots of the individual rotor blades can in principle be identical, that is to say group-independent. Alternatively, however, it can also be provided that the rotor blades have group-specific blade roots.
  • rotor blades are used which have group-specific designed blade types, wherein the blade blade types of different groups of rotor blades differ from each other. It can be provided, for example, that the blades of different groups additionally differ from each other in terms of their material, their coating or any combination of these features. This allows a particularly effective frequency detuning of the rotor, since in this way in combination with the group-specific trained blade platforms never two identically designed blades can be installed flush side by side. Vice versa However, it is advantageously not necessary to design each individual blade of the rotor individually in order to achieve a sufficient frequency detuning.
  • Another aspect of the invention relates to an aircraft engine, wherein it is provided according to the invention that it comprises a rotor according to one of the preceding embodiments and / or a blade ring, which is produced by means of a method according to one of the preceding embodiments.
  • Fig. 1 shows a schematic plan view of two flush-mounted rotor blades 10a, 10b during the manufacture of a blade ring (not shown) of a rotor for an aircraft engine. From the rotor blades 10a, 10b, the cut blades 12a, 12b are shown, which are connected to blade platforms 14a, 14b of the rotor blades 10a, 10b and extending in a conventional manner from the blade platforms 14a, 14b from radially upwards. Radially below the blade platforms 14a, 14b, the rotor blades 10a, 10b comprise respective blade roots 16a, 16b (see FIG. Fig.
  • the two rotor blades 10a, 10b comprise differently designed blade platforms 14a, 14b and belong to two different groups.
  • the blade platforms 14a, 14b of the two groups of rotor blades 10a, 10b lie flush against each other and form in the finished mounted blade ring or in the finished rotor a continuous, radially inner shroud, which limits the flow path in the associated aircraft engine.
  • the blades 12a, 12b are formed group-specific, wherein blades blades 12a and 12b of the same group have an identical blade geometry and blades 12a, 12b of different groups have different blade geometry.
  • the blade platform 14a belonging to the first group of rotor blades 10a is designed such that it is flush with the blade platform 14b belonging to the second group of rotor blades 10b and designed to be complementary to the blade platform 14a.
  • the blade platform 14a of the first group in the region I has a recess which is peripheral with respect to the dot-dashed dividing plane A and, in the opposite region II, a marginal elevation with respect to the dash-dotted dividing plane A.
  • Corresponding blade platform 14b of the second group accordingly has a marginal elevation complementary to the depression of the blade platform 14a in region I and a marginal depression complementary to the elevation of blade platform 14a in region II.
  • the graduation plane A hereby identifies the theoretical graduation plane between two conventional rotor blades whose blade platforms have consistently planar contact surfaces and thus can not be arranged so that they are not interchangeable.
  • first rotor blades provided with identical blade platforms and the wells and elevations then by a corresponding milling treatment of the blade platforms 14a, 14b are generated.
  • the blade platform 14a of the first group of rotor blades 10a can not be placed flush with another blade platform 14a of the first group, but only on the blade platform 14b belonging to the second group of rotor blades 10b.
  • the blade platform 14b belonging to the second group of rotor blades 10b can also be placed flush with the paddle platform 14a belonging to the first group, but not flush with another paddle platform 14b of the second group.
  • two identical rotor blades 10a-10a or 10b-10b of the same group with identical blade platforms 14a-14a or 14b-14b can never be installed flush next to each other.
  • blade platforms 14a of rotor blades 10a of the first group and blade platforms 14b of rotor blades 10b of the second are alternately formed to form a blade ring Group attached to each other.
  • a particularly effective frequency detuning of the finished blade ring and thus of the assembled rotor is reliably achieved.
  • one or more further groups of differently shaped rotor blades are used with group-specific blade platforms, wherein the blade platforms are always to be designed such that they are not flush with blade platforms of rotor blades of the same group, but flush with blade platforms of rotor blades at least can be applied to another group.
  • the depressions and elevations are formed in lateral contact or contact surfaces of the blade platforms 14a, 14b of the rotor blades 10a, 10b and form a tongue and groove connection.
  • a structurally particularly simple swap protection can be achieved, for example, in that the first group of rotor blades 10a has bilateral elevations (springs) and the second group of rotor blades 10b has recesses (grooves) on both sides.
  • Fig. 2 shows a schematic frontal view of two alternately formed rotor blades 10a, 10b during the manufacture of a blade ring (not shown) of an aircraft engine rotor.
  • Rotor blades 10a, 10b show partially cut airfoils 12a, 12b, which are connected to blade platforms 14a, 14b of rotor blades 10a, 10b and extend radially upward from blade platforms 14a, 14b.
  • Radially below the blade platforms 14a, 14b, the rotor blades 10a, 10b comprise respective blade roots 16a, 16b, via which the connection of the rotor blades 10a, 10b to one Rotor body of the rotor takes place.
  • the blade platforms 14a, 14b have mutually corresponding lateral contact surfaces III.
  • the contact surfaces III are formed obliquely or wedge-shaped with respect to the axis of rotation of the rotor extending division plane A, so that the blade platform 14a of the first group only with the blade platform 14b of the second group, but not with a further blade platform 14a of the first Group can be brought flush into contact.
  • the blade platforms 14a, 14b of the two groups of rotor blades 10a, 10b form a continuous, radially inner shroud, which limits the flow path in the assigned aircraft engine, analogous to the previous exemplary embodiment in the completely assembled blade ring or in the finished rotor.
  • the wedge-shaped design of the contact surfaces causes depending on the angle of the wedge increased friction between the contact surfaces III.
  • the contact surfaces III have a fundamentally arbitrary contour profile and, for example, can be corrugated and / or serrated or have other suitable elevations / depressions. It is only important that the contact surfaces III of the first group of rotor blades 10a can be brought into contact flush only with corresponding contact surfaces III of the second (or another) group of rotor blades 10b, but not with contact surfaces III of the first group of rotor blades 10a.

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

Claims (12)

  1. Rotor destiné à une turbomachine, en particulier un moteur d'avion, comprenant une couronne d'aubes qui comporte une pluralité d'aubes de rotor (10a, 10b) de configurations différentes munies de plates-formes d'aube (14a, 14b) en appui affleuré les unes contre les autres, la couronne d'aubes comportant au moins deux groupes d'aubes de rotor (10a, 10b) de configurations différentes, chaque groupe d'aubes de rotor (10a, 10b) étant associé à des plates-formes d'aube (14a, 14b) qui peuvent chacune être amenées en appui affleuré avec une plate-forme d'aube complémentaire (14a, 14b) d'au moins un autre groupe d'aubes de rotor (10a, 10b) et pas avec une plate-forme d'aube (14a, 14b) du même groupe d'aubes de rotor (10a, 10b), caractérisé en ce que chaque plate-forme d'aube (14a) d'un premier groupe d'aubes de rotor (10a) comporte au moins un évidement marginal dans lequel une saillie marginale complémentaire d'une plate-forme d'aube adjacente (14b) d'un deuxième groupe associé d'aubes de rotor (10b) est disposé à complémentarité de formes.
  2. Rotor selon la revendication 1, caractérisé en ce que l'évidement et/ou la saillie de la plate-forme d'aube correspondante (14a, 14b) est introduit dans la plate-forme d'aube correspondante (14a, 14b) au moyen d'un procédé de séparation, en particulier par fraisage et/ou meulage.
  3. Rotor selon la revendication 2, caractérisé en ce que chaque plate-forme d'aube (14a) du premier groupe d'aubes de rotor (10a) comporte un évidement marginal et une saillie marginale opposée et chaque plate-forme d'aube (14b) du deuxième groupe d'aubes de rotor (10b) comporte une saillie marginale complémentaire de l'évidement de la plate-forme d'aube (14a) du premier groupe et un évidement marginal complémentaire de la saillie de la plate-forme d'aube (14a) du premier groupe.
  4. Rotor selon l'une des revendications 1 à 3, caractérisé en ce que les évidements et les saillies complémentaires sont disposés au niveau de surfaces de contact latérales des aubes de rotor (10a, 10b), les saillies étant disposées dans les évidements associés par complémentarité de formes.
  5. Rotor selon l'une des revendications 1 à 4, caractérisé en ce que les au moins deux groupes d'aubes de rotor (10a, 10b) ont des géométries d'aube différentes.
  6. Rotor selon l'une des revendications 1 à 5, caractérisé en ce que les au moins deux groupes d'aubes de rotor (10a, 10b) comportent des plates-formes d'aube (14a, 14b) ayant des surfaces d'appui latérales (III) qui correspondent les unes aux autres.
  7. Rotor selon la revendication 6, caractérisé en ce que les surfaces d'appui (III) sont obliques et/ou ondulées et/ou dentelées et/ou irrégulières.
  8. Procédé de réalisation d'une couronne d'aubes d'un rotor destinée à une turbomachine, notamment un moteur d'avion, comprenant les étapes suivantes visant à :
    a) produire au moins deux groupes d'aubes de rotor (10a, 10b) de configurations différentes, chaque groupe d'aubes de rotor (10a, 10b) étant associé à des plates-formes d'aube (14a, 14b) qui peuvent être amenées en appui affleuré avec une plate-forme d'aube complémentaire (14a, 14b) d'au moins un autre groupe d'aubes de rotor (10a, 10b) et non avec une plate-forme d'aube (14a, 14b) du même groupe d'aubes de rotor (10a, 10b) ; et
    b) disposer les aubes de rotor (10a, 10b) en forme de couronne d'aubes, des plates-formes d'aube (14a, 14b) complémentaires entre elles des au moins deux groupes d'aubes de rotor (10a, 10b) étant amenées en appui affleuré les unes contre les autres,
    caractérisé en ce que
    chaque plate-forme d'aube (14a) d'un premier groupe d'aubes de rotor (10a) comporte au moins un évidement marginal dans lequel une saillie marginale complémentaire d'une plate-forme d'aube adjacente (14b) d'un deuxième groupe associé d'aubes de rotor (10b) est disposée par complémentarité de formes.
  9. Procédé selon la revendication 8, caractérisé en ce que, à l'étape (b), des plates-formes d'aube (14a) d'un premier groupe d'aubes de rotor (10a) et des plates-formes d'aube (14b) d'un deuxième groupe d'aubes de rotor (10b) sont amenées alternativement en appui les unes contre les autres.
  10. Procédé selon la revendication 8 ou la revendication 9, caractérisé en ce que les pieds des aubes de rotor (10a, 10b) sont disposés et fixés à l'étape b) dans une rainure complémentaire du corps de base du rotor.
  11. Procédé selon l'une des revendications 8 à 10, caractérisé en ce qu'au moins deux groupes d'aubes de rotor (10a, 10b) ayant des géométries d'aube différentes sont produits à l'étape a).
  12. Moteur d'avion comprenant un rotor selon l'une des revendications 1 à 7 et/ou une couronne d'aubes qui est fabriquée par un procédé selon l'une des revendications 8 à 11.
EP12152073.8A 2012-01-23 2012-01-23 Rotor pour une turbomachine et procédé de fabrication Not-in-force EP2617945B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES12152073.8T ES2668268T3 (es) 2012-01-23 2012-01-23 Rotor para una turbomáquina y procedimiento para su fabricación
EP12152073.8A EP2617945B1 (fr) 2012-01-23 2012-01-23 Rotor pour une turbomachine et procédé de fabrication
US13/746,650 US9657581B2 (en) 2012-01-23 2013-01-22 Rotor for a turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12152073.8A EP2617945B1 (fr) 2012-01-23 2012-01-23 Rotor pour une turbomachine et procédé de fabrication

Publications (2)

Publication Number Publication Date
EP2617945A1 EP2617945A1 (fr) 2013-07-24
EP2617945B1 true EP2617945B1 (fr) 2018-03-14

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Family Applications (1)

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EP12152073.8A Not-in-force EP2617945B1 (fr) 2012-01-23 2012-01-23 Rotor pour une turbomachine et procédé de fabrication

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US (1) US9657581B2 (fr)
EP (1) EP2617945B1 (fr)
ES (1) ES2668268T3 (fr)

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EP2918784A1 (fr) * 2014-03-13 2015-09-16 Siemens Aktiengesellschaft Pied d'aube pour une aube de turbine
US10823192B2 (en) 2015-12-18 2020-11-03 Raytheon Technologies Corporation Gas turbine engine with short inlet and mistuned fan blades
US10408231B2 (en) * 2017-09-13 2019-09-10 Pratt & Whitney Canada Corp. Rotor with non-uniform blade tip clearance
US10865806B2 (en) 2017-09-15 2020-12-15 Pratt & Whitney Canada Corp. Mistuned rotor for gas turbine engine
US11002293B2 (en) 2017-09-15 2021-05-11 Pratt & Whitney Canada Corp. Mistuned compressor rotor with hub scoops
US10443411B2 (en) * 2017-09-18 2019-10-15 Pratt & Whitney Canada Corp. Compressor rotor with coated blades
US10837459B2 (en) 2017-10-06 2020-11-17 Pratt & Whitney Canada Corp. Mistuned fan for gas turbine engine

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ES2668268T3 (es) 2018-05-17
US9657581B2 (en) 2017-05-23
US20130189111A1 (en) 2013-07-25
EP2617945A1 (fr) 2013-07-24

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