EP3192966B1 - Rotor pour une turbomachine axiale avec une bride d'équilibrage orientée axialement et compresseur - Google Patents

Rotor pour une turbomachine axiale avec une bride d'équilibrage orientée axialement et compresseur Download PDF

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Publication number
EP3192966B1
EP3192966B1 EP16151268.6A EP16151268A EP3192966B1 EP 3192966 B1 EP3192966 B1 EP 3192966B1 EP 16151268 A EP16151268 A EP 16151268A EP 3192966 B1 EP3192966 B1 EP 3192966B1
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EP
European Patent Office
Prior art keywords
rotor
flange
balancing
main body
base body
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
EP16151268.6A
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German (de)
English (en)
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EP3192966A1 (fr
Inventor
Thomas Binsteiner
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
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MTU Aero Engines AG
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Publication date
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Priority to EP16151268.6A priority Critical patent/EP3192966B1/fr
Publication of EP3192966A1 publication Critical patent/EP3192966A1/fr
Application granted granted Critical
Publication of EP3192966B1 publication Critical patent/EP3192966B1/fr
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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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • F05D2220/3219—Application in turbines in gas turbines for a special turbine stage for a special compressor stage for the last stage of a compressor or a high pressure compressor
    • 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

Definitions

  • the present invention relates to a rotor for a turbo machine according to the preamble of claim 1.
  • the present invention also relates to a compressor according to claim 10.
  • Rotors for turbo machines have to meet a wide range of requirements and boundary conditions.
  • individual rotor base bodies or rotor stages should be able to be balanced in order to be able to operate unbalance-free, low-wear and low-maintenance during operation.
  • the common balancing options include, for example, the assembly of individual balancing weights on rotor base bodies (or rotor disks).
  • areas in rotor drums i.e. in rotor inner areas of lined up rotor stages, can form in which bearing oil accumulations or other fluids collect due to their centrifugal force during operation of the rotor.
  • This accumulation of bearing oil can lead to undesirable effects if the rotor is stopped and started again in the meantime.
  • These effects include an escape of bearing oil (for example due to bearing seal leakage) or bearing oil mist into the main flow area of, for example, aircraft turbines and a subsequent unwanted or undesired transfer to so-called bleed air areas for cabin air entrances.
  • a rotor for a turbo machine with a first and a second rotor base body is known, the first rotor base body having a connecting flange and a radially aligned balancing flange.
  • the post-published European patent application EP 3 091 179 A1 describes a rotor assembly having a shaft-hub connection, the hub being connected to the downstream rotors. A balancing flange running in the axial direction is arranged on the hub.
  • EP 3 091 178 A1 relates to a rotor for a turbomachine with a first and a second Rotor base body, the first rotor base body having a connecting flange with a balancing flange arranged radially on the outside of the first connecting flange.
  • One object of the present invention is to propose a rotor for a turbomachine which has suitable balancing options taking into account the problems mentioned.
  • a further object of the present invention is to propose a compressor with a rotor according to the invention.
  • the object according to the invention is achieved by a rotor with the features of claim 1. It is also achieved by a compressor having the features of claim 10.
  • a rotor for a turbomachine comprising at least one first rotor base body with a first connecting flange for connecting the first rotor base body to a second rotor base body.
  • the first rotor base body is connected to at least one rotor blade and has an axially aligned balancing flange.
  • the first connecting flange is materially connected to the balancing flange and the balancing flange is arranged radially on the inside of the first connecting flange.
  • a compressor according to the invention of a turbo machine has at least one rotor according to the invention.
  • the compressor can be a high pressure compressor of an aircraft engine.
  • Exemplary embodiments according to the invention can have one or more of the features mentioned below.
  • the axial flow machine is an axial gas turbine, for example an aircraft gas turbine.
  • An axial flow machine can be referred to as an aircraft engine.
  • An aircraft engine can have a compressor with several Compressor stages and a turbine with multiple turbine stages include. Compressor stages and turbine stages can each have several rotor stages and several stator stages.
  • rotor can include one or more rotor stages which, when the turbo machine is used as intended, rotate about an axis of rotation or axis of rotation of the turbo machine.
  • a rotor or a rotor stage can be referred to as an impeller or comprise an impeller.
  • a rotor or a rotor stage can comprise several rotor blades and a rotor base body.
  • the rotor base body can be referred to as a rotor disk or rotor ring or comprise these.
  • a rotor can be installed and assembled in a turbo machine, in particular in an axial gas turbine.
  • the rotor blades of a rotor or an impeller can be positively connected by means of a releasable connection or integrally with the rotor base body.
  • An integral connection is in particular a material or material connection.
  • An integral connection can be produced using a generative manufacturing process.
  • a rotor base body with blades integrally connected to the rotor base body can be referred to as an integrally bladed rotor.
  • An integrally bladed rotor can be a so-called BLISK (Bladed Disk) or a BLING (Blade Ring).
  • the rotor base body can comprise rotor disks directed radially inward and / or axially oriented rotor arms.
  • the rotor disks directed radially inward can be referred to as extensions or T-shaped extensions of the rotor blades.
  • the rotor can be designed or prepared for direct or indirect connection to a shaft of the turbomachine.
  • rotor drum can include sections of at least two axially interconnected basic rotor bodies.
  • rotor arms can form a radial or cylindrical shape of the rotor drum.
  • a rotor drum can likewise be formed over more than two rotor base bodies and optionally over several rotor arms and rotor disks.
  • rotor interior and rotor exterior can designate the spaces inside and outside of rotor drums.
  • the rotor interior can thus be delimited radially outward essentially by one or more rotor arms.
  • the rotor interior can essentially be delimited by rotor disks.
  • the outer rotor space can be delimited radially inward essentially by one or more rotor arms.
  • the rotor outer space essentially comprises the main flow channel of the turbo machine. Between a rotor arm and the main flow channel, for example, stator inner rings, with or without inlet seals, can also be arranged.
  • the rotor interior and / or the rotor exterior can comprise several rotor stages.
  • Rotor base bodies arranged axially one behind the other can be connected to one another by means of rotor arms and / or rotor disks.
  • the connection is in particular form-fitting and / or force-fitting.
  • connecting flange can mean a component for, in particular form-fitting and / or force-fitting, connecting or flanging a rotor base body or a rotor stage to a further rotor base body or to a further rotor stage. In some embodiments according to the invention, this connection of the connecting flange does not have a screw connection for connecting to one another.
  • a positive connection of a connecting flange with, for example, a further connecting flange of an adjacent or axially adjoining basic rotor body can mean fitting into one another of radial and / or axial shoulders of the two connecting flanges.
  • a positive connection can have a fit between the two components.
  • a fit can be a clearance fit, a transition fit, or an interference fit. In the case of a press fit, an additional force fit can be added to the form fit.
  • balancing flange can be a shoulder, a web, an extension or the like in order to balance a component, in particular the component on which the balancing flange is fixed or of which the balancing flange is a section or to balance.
  • the balancing flange can be used additionally or exclusively for balancing other, in particular adjacent, components.
  • a balancing flange is not provided or designed for connection to a further component, that is to say not for flange-mounting to a further component.
  • the balancing flange is provided for receiving material for balancing.
  • a material uptake can be a punctiform or Area-shaped application, for example a material-locking application by means of welding, soldering or gluing mean.
  • the balancing flange is provided for removing material and for receiving material for balancing.
  • the first connecting flange is integrally connected to the balancing flange.
  • An integral connection can be a one-piece connection.
  • a one-piece connection can be produced, for example, by means of a casting process or by means of a generative manufacturing process.
  • a radially inner contour of the first rotor base body in the area of the first connecting flange and the balancing flange is designed for the flow of fluids into a radially outer rotor space, in particular due to centrifugal forces, i.e. in an operating state with a rotary movement of the rotor.
  • the fluid can also flow out of the rotor interior to the outside when the rotor or turbine is at a standstill, in particular after the rotor or turbine has been switched off. In the case of an aircraft turbine, this can lead to an oil smell in the cabin of the aircraft when the rotor is restarted or subsequently started.
  • Escaping oil can be blown out immediately after a start process via ejection bores.
  • the design of the contour does not have any cavities or storage areas for receiving fluid.
  • the radially inner contour of the first rotor base body can be referred to as the boundary or border of a rotor drum (see definition above).
  • a centrifugal force-induced outflow of fluids, in particular of bearing oils from rotor bearings arranged upstream and / or downstream of the rotor stages into the rotor outer space, can take place by means of radial bores or openings in the rotor drum.
  • the radial bore (or a plurality of radial bores) can be arranged at a largest possible radius or maximum radius within the rotor drum.
  • the radially inner contour of the first rotor base body in the area of the first connecting flange and the balancing flange does not have any cavities in which the fluid can collect or accumulate due to centrifugal forces.
  • the radially inner contour of the first rotor base body is im
  • the area of the first connecting flange and the balancing flange are designed to be barrier-free and flow-optimized.
  • the axially arranged balancing flange is arranged radially on the inside of the first connecting flange. In other embodiments, the axially arranged balancing flange can be arranged radially on the outside of the first connecting flange.
  • the balancing flange has at least one area for removing material for balancing the rotor.
  • the area for material removal can be on an axial end area, on a radial inner and / or outer area of the balancing flange.
  • the area for material removal can extend over the entire circumference of the balancing flange or only affect individual areas over the circumference. For example, smaller or larger areas can be removed by cutting (e.g. by means of milling).
  • the balancing flange can be shortened and removed axially at the end, over the entire circumference or only in individual circumferential segments, and / or further areas on the radially inner and / or outer side can be removed for balancing.
  • the ablated areas on the radially inner side of the balancing flange do not have any cavities that could hinder a possible outflow of fluids from the interior of the rotor.
  • the circumferential segments for material removal can extend, for example, over 5 degrees, 10 degrees, 15 degrees, 20 degrees or other angular ranges.
  • a radial gap is arranged between the balancing flange and the second rotor base body.
  • the radial gap can simplify balancing by removing material from the balancing flange.
  • the radial gap can simplify a form-fitting and / or force-fitting connection of the first connection flange to a second connection flange of the second rotor base body.
  • the balancing flange and the first connecting flange are made from one material.
  • the first rotor base body, the balancing flange and the first connecting flange are integrally connected to one another.
  • the first rotor base body has no balancing weights and / or screw passages for fixing balancing weights.
  • the first rotor base body has no shoulders or flanges directed radially inward for fixing balancing weights.
  • the first rotor base body, the balancing flange and the first connecting flange are made from one material.
  • a unit made from one material and comprising the first rotor base body, balancing flange and first connecting flange can be referred to as being in one piece.
  • oil accumulations for example bearing oil accumulations, in the interior of the rotor, that is to say inside the rotor drum, can advantageously be avoided or at least reduced.
  • the arrangement of the balancing flange enables only small cavities or no cavities at all, in which oil can collect, to be created in the rotor drum. This can at least reduce the possibility of contamination of cabin air by bearing oil when the rotor is used in an aircraft engine.
  • the balancing flange can advantageously be balanced as an individual part.
  • This balancing can be referred to as individual part balancing.
  • Individual part balancing enables balancing with an equivalent potential compared to alternative solutions according to the prior art, in which Individual balancing weights can be used, which are screwed on, flanged or shrunk on as additional parts by means of press fits.
  • a flange cavity can advantageously be reduced to zero or to approximately zero compared to connecting flanges with separate balancing weights.
  • the rotor according to the invention can be used in turbines and / or compressors. Due to the design of a first rotor base body with an integral balancing flange, the installation space and the weight of the rotor and thus of the turbomachine can advantageously be optimized. This can result in economic advantages, for example through lower kerosene consumption and / or a compact design.
  • Fig. 1 shows a rotor 100 according to the prior art with a first rotor base body 101, a flanged-on second rotor base body 103, riveted balancing weights 105 on the first rotor base body 101 and a stator 107 in a longitudinal sectional view.
  • the rotor 100 is flowed through in the axial direction a in the main flow direction 109.
  • a plurality of rotor blades 111 arranged over the circumference u are fixed to the first rotor base body 101.
  • the stator 107 Downstream (in the axial direction a) of the first rotor base body 101 and the rotor blades 111, the stator 107 is arranged, which is statically connected to the housing of the Turbo machine (in Fig. 1 not shown) is connected.
  • An inner ring 115 is arranged radially inward on the guide vanes 113 of the guide wheel 107 arranged over the circumference u. Further downstream after the stator 107, the rotor blades 117 connected to the second rotor base body 103 are shown.
  • the first rotor base body 101 has a connection flange 119 and one (or more fastening flanges 121 distributed over the circumference u) for fastening balancing weights 105.
  • the connecting flange 119 connects the first rotor base body 101 to the second rotor base body 103.
  • the second rotor base body 103 has a rotor arm 123, at the axial, upstream end of which a further connecting flange 125 is arranged.
  • the two connecting flanges 119, 125 are positive (the connecting flange 125 encloses or includes the connecting flange 119 on the axial and radial sides) and non-positive (the first rotor stage with the first rotor base body 101 and the rotor blades 111 is axially connected to the second rotor stage with the second rotor base body 103 and the rotor blades 117 clamped) connected to one another.
  • the rotor arm 123 has at least one radial bore 127. Further radial bores can be arranged over the circumference of the rotor arm 123.
  • fluids for example bearing oils from rotor bearings arranged axially upstream and / or downstream, are to be transported from the rotor drum space 129, which can also be referred to as the rotor interior, into the rotor exterior 131.
  • the rotor drum space 129 which can also be referred to as the rotor interior
  • these fluids are thrown outward through the bore 127 due to centrifugal forces.
  • the fluids can be transported further with the main flow from the rotor outer space 131.
  • the radial bore 127 can be referred to as an oil throw-off bore.
  • bearing oil can collect in so-called radial cavities 133 in the area of the fastening flange 121. This accumulated bearing oil can drip or flow off into the rotor outer space 129 and / or into housing cavities when the rotor 100 stops or comes to a standstill. When the turbine engine is started again or afterwards, this bearing oil is then sucked directly into the main flow channel by the flow. However, since the main flow is initially still low in this starting phase of the rotor 100, the bearing oil or When the turbo machine is used as an aircraft engine, at least parts of the bearing oil enter the so-called bleed air, which could enter the cabin air through radial openings in the housing. This could result in an oil smell in the cabin air, which could have further consequences and must be avoided at all costs.
  • FIG Fig. 2 A constructive avoidance of such cavities 133 is shown in FIG Fig. 2 illustrated and described by the rotor 100 according to the invention.
  • Fig. 2 shows a detailed section of a rotor 100 according to the invention with a connecting flange 119 for connecting a first rotor base body 101 to a further connecting flange 125 of a second rotor base body 103, as well as an axially aligned balancing flange 201.
  • the first rotor base body 101 has in comparison to Fig. 1 (State of the art) does not have a mounting flange with balancing weights.
  • the axial alignment of the balancing flange 201 By means of the axial alignment of the balancing flange 201, one or more radial cavity, like them in Fig. 1 should be avoided. This allows the effects mentioned as they are to Fig.
  • Balancing by means of the balancing flange 201 can be carried out by removing material at the axial end (in Fig. 2 at the right end) of the balancing flange 201.
  • the necessary point or position for balancing can be analyzed and localized using suitable and known methods. Material can then be removed at the appropriate points, for example at selected angular positions over the circumference of the balancing flange 201, and thus the component (of the first rotor base body 101 or the first rotor stage as a whole) can be balanced.
  • the radial gap 203 is for an outflow of fluids from the rotor interior (see Fig. 1 ) unproblematic, since a fluid, for example bearing oil, can easily flow off to a radial opening without being blocked or collected in a cavity. Furthermore, the radial gap 203 can simplify the form-fitting and / or force-fitting connection of the two connecting flanges 119, 125.
  • the first rotor base body 101 is designed in an integral construction together with the first connecting flange 119 and the axial balancing flange 201.
  • An integral construction means a material connection of these components, which are made in particular by means of the same material. With a generative process as a manufacturing option, different materials can also be used to manufacture an integral component. This can be advantageous, for example, to use an optimized material for removing material from the balancing flange 201.
  • the dividing line 205 can indicate a maximum possible axial material removal from the balancing flange 201. This can be necessary, for example, for the stability and component integrity of the first rotor base body 101.
  • a material removal on the balancing flange 201 can for example by means of cutting removal, z. B. by milling or drilling.

Landscapes

  • 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 (11)

  1. Rotor (100) pour une turbomachine axiale, comprenant au moins un premier corps de base de rotor (101), dans lequel le premier corps de base de rotor (101) comporte une première bride de liaison (119) permettant de relier le premiercorps de base de rotor (101) à un second corps de base de rotor(103), dans lequel le premier corps de base de rotor (101) est relié à au moins une aube mobile (111) et comporte une bride d'équilibrage (201), dans lequel la première bride de liaison (119) est reliée par liaison complémentarité de matière à la bride d'équilibrage (201) et la bride d'équilibrage (201) est disposée radialement à l'intérieur de la première bride de liaison (119), caractérisé en ce que la bride d'équilibrage est orientée axiale.
  2. Rotor (100) selon la revendication 1, dans lequel un contour radialement intérieur du premier corps de base de rotor (101) est conçu, dans la zone de la première bride de liaison (119) et de la bride d'équilibrage (201), pourpermettre l'écoulement, en particulier par la force de centrifugation, des fluides dans un espace extérieur de rotor(131) disposé radialement extérieur, dans lequel la configuration ne comportepas en particulier de cavités (133) et de zones de retenu permettant de recevoir le fluide.
  3. Rotor (100) selon l'une quelconque des revendications précédentes, dans lequel la bride d'équilibrage (201) comporte au moins une zone de prélèvement de matière pour permettre l'équilibrage.
  4. Rotor (100) selon la revendication précédente, dans lequel la zone d prélèvement de matière est disposée dans la zone d'extrémité axiale de la bride d'équilibrage (201).
  5. Rotor (100) selon la revendication précédente, dans lequel, à l'état monté des premier (101) et second corps de base de rotor (103), un espace radial est disposé entre la bride d'équilibrage (201) et le second corps de base de rotor (103).
  6. Rotor (100) selon l'une quelconque des revendications précédentes, dans lequel la bride d'équilibrage (201) et la première bride de liaison (101) sont fabriquées d'une matière.
  7. Rotor (100) selon l'une quelconque des revendications précédentes, dans lequel le premier corps de base de rotor (101), la bride d'équilibrage (201) et la première bride de liaison (119) sont reliées les uns auxautres de manière solidaire.
  8. Rotor (100) selon l'une quelconque des revendications précédentes, dans lequel le premier corps de base de rotor (101) ne comporte pas de poids d'équilibrage (105) et/ou d'ouvertures de vis permettant de fixer des poids d'équilibrage (105).
  9. Rotor (100) selon l'une quelconque des revendications précédentes, dans lequel le premier corps de base de rotor (101), la bride d'équilibrage (201) et la première bride de liaison (119) sont fabriqués d'une matière.
  10. Compresseur d'une turbomachine axiale, dans lequel ledit compresseur comporte au moins un rotor (100) selon l'une quelconque des revendications 1 à 9.
  11. Compresseur selon la revendication 10, dans lequel ledit compresseur est un compresseur haute pression d'un moteur d'avion.
EP16151268.6A 2016-01-14 2016-01-14 Rotor pour une turbomachine axiale avec une bride d'équilibrage orientée axialement et compresseur Active EP3192966B1 (fr)

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Application Number Priority Date Filing Date Title
EP16151268.6A EP3192966B1 (fr) 2016-01-14 2016-01-14 Rotor pour une turbomachine axiale avec une bride d'équilibrage orientée axialement et compresseur

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EP16151268.6A EP3192966B1 (fr) 2016-01-14 2016-01-14 Rotor pour une turbomachine axiale avec une bride d'équilibrage orientée axialement et compresseur

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EP3192966A1 EP3192966A1 (fr) 2017-07-19
EP3192966B1 true EP3192966B1 (fr) 2021-05-19

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102022101762A1 (de) 2022-01-26 2023-07-27 MTU Aero Engines AG Rotor mit einem Wuchtflansch, Rotoranordnung mit zumindest einem Rotor und Strömungsmaschine mit zumindest einem Rotor oder mit einer Rotoranordnung

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3096073B1 (fr) * 2019-05-13 2021-05-14 Safran Aero Boosters Tambour de rotor pour une turbomachine
FR3108360B1 (fr) * 2020-03-23 2023-04-14 Safran Aircraft Engines Procede et dispositif d’equilibrage d’une piece tournante pour une turbomachine d’aeronef
DE102021123173A1 (de) * 2021-09-07 2023-03-09 MTU Aero Engines AG Rotorscheibe mit gekrümmtem Rotorarm für eine Fluggasturbine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3091179A1 (fr) * 2015-05-07 2016-11-09 MTU Aero Engines GmbH Système de rotor pour une turbomachine et compresseur
EP3091178A1 (fr) * 2015-05-07 2016-11-09 MTU Aero Engines GmbH Tambour-rotor pour une turbomachine et compresseur

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4848182A (en) * 1987-09-08 1989-07-18 United Technologies Corporation Rotor balance system
US5628621A (en) * 1996-07-26 1997-05-13 General Electric Company Reinforced compressor rotor coupling
DE102004037608A1 (de) * 2004-08-03 2006-03-16 Rolls-Royce Deutschland Ltd & Co Kg Unwuchtkompensation von rotierenden Bauteilen

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3091179A1 (fr) * 2015-05-07 2016-11-09 MTU Aero Engines GmbH Système de rotor pour une turbomachine et compresseur
EP3091178A1 (fr) * 2015-05-07 2016-11-09 MTU Aero Engines GmbH Tambour-rotor pour une turbomachine et compresseur

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102022101762A1 (de) 2022-01-26 2023-07-27 MTU Aero Engines AG Rotor mit einem Wuchtflansch, Rotoranordnung mit zumindest einem Rotor und Strömungsmaschine mit zumindest einem Rotor oder mit einer Rotoranordnung
EP4219897A1 (fr) 2022-01-26 2023-08-02 MTU Aero Engines AG Rotor comprenant une bride d'équilibrage, ensemble rotor comprenant au moins un rotor et turbomachine comprenant au moins un rotor ou un ensemble rotor

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