EP3091178A1 - Tambour-rotor pour une turbomachine et compresseur - Google Patents

Tambour-rotor pour une turbomachine et compresseur Download PDF

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Publication number
EP3091178A1
EP3091178A1 EP15166681.5A EP15166681A EP3091178A1 EP 3091178 A1 EP3091178 A1 EP 3091178A1 EP 15166681 A EP15166681 A EP 15166681A EP 3091178 A1 EP3091178 A1 EP 3091178A1
Authority
EP
European Patent Office
Prior art keywords
rotor
drum
rotor drum
compressor
arm
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.)
Withdrawn
Application number
EP15166681.5A
Other languages
German (de)
English (en)
Inventor
Stefan Boewing
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 EP15166681.5A priority Critical patent/EP3091178A1/fr
Priority to US15/091,320 priority patent/US20160327065A1/en
Publication of EP3091178A1 publication Critical patent/EP3091178A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/70—Suction grids; Strainers; Dust separation; Cleaning
    • F04D29/701—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/083—Sealings especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/609—Deoiling or demisting

Definitions

  • the present invention relates to a rotor drum for a turbomachine according to the preamble of claim 1 and to a compressor according to claim 8.
  • liquid accumulations can form during operation in certain situations, which accumulate during operation of the rotors in cavities of rotor drums due to centrifugal force. Only when the rotors are at a standstill can this accumulated liquid flow into another area of the rotors and possibly cause various disadvantages.
  • oil can be distributed as a liquid after restarting the rotor in areas of the turbomachine, which cause significant disadvantages for such oil accumulations.
  • the oil can, for example, at a restart of the rotors via housing channels in the cabin inlet air and there lead to oil odor and contamination.
  • An object of the present invention is to propose a rotor drum for a turbomachine, in which fluid accumulations can be avoided. It is another object of the present invention to propose a compressor.
  • the object of the invention is achieved by a rotor drum having the features of claim 1. It is further achieved by a compressor according to claim 8.
  • the invention thus proposes a rotor drum for a turbomachine, the rotor drum comprising sections of at least one first rotor main body and a second rotor main body.
  • the second rotor base body has at least one rotor arm.
  • the rotor drum further has at least one opening as a passage opening, in particular as a bore, for the passage of fluids, in particular of bearing oil or condensed bearing oil mist of a rotor bearing, from a rotor interior into a rotor outer space.
  • the opening is arranged radially outward, relative to the main flow axis of the turbomachine. Furthermore, the opening is arranged at the largest radius of an inner contour of the rotor drum.
  • Inventive exemplary embodiments may have one or more of the following features.
  • the term "rotor” refers to a body of revolution in a turbomachine that, when used as intended, rotates about an axis of rotation or axis of rotation of the turbomachine.
  • the rotor comprises at least one rotor stage.
  • a rotor stage may be referred to as an impeller or comprise an impeller.
  • a rotor stage comprises at least a plurality of rotor blades and a rotor body.
  • the rotor base body may be referred to as or comprise a disk, rotor disk, ring or rotor ring.
  • a rotor may include one or more rotor stages.
  • a rotor can be installed and mounted in a turbomachine, in particular in a gas turbine.
  • An aircraft engine may be a gas turbine or include a gas turbine.
  • An aircraft engine may include a compressor with multiple compressor stages and a turbine with multiple turbine stages. Compressor stages and turbine stages may each have rotor stages and stator stages.
  • the blades may be referred to as blades and at least each comprise an airfoil, a blade root and a blade platform.
  • the blades may be connected separately, for example by means of a form-fit, by means of a detachable so-called dovetail joint, or integrally with the rotor base body.
  • Separate blades may be releasably and / or positively and / or materially connected to the rotor body.
  • An integral connection is in particular a material connection.
  • An integral connection can be made by means of a generative manufacturing process.
  • a rotor body having vanes integrally connected to the rotor body may be referred to as an integrally bladed rotor become.
  • An integrally bladed rotor may be a so-called BLISK (Bladed Disk) or a BLING (Blade Ring).
  • the rotor base body may comprise radially inwardly directed rotor disks and / or axially aligned rotor arms.
  • the radially inwardly directed rotor disks may be referred to as extensions or T-shaped extensions of the rotor blades.
  • the rotor arms can be called drum bodies.
  • the rotor is designed or prepared for direct or indirect connection to a shaft of the turbomachine.
  • An indirect connection can be made by means of hub and / or by means of further rotors.
  • the rotor In a direct connection, the rotor can be flanged directly to the shaft.
  • rotor drum refers to portions of at least two axially interconnected rotor bases.
  • rotor arms can form a rotor drum.
  • a rotor drum can also be formed over more than two rotor base body and optionally via a plurality of rotor arms and rotor disks.
  • a plurality of rotor main body of an eight-stage compressor in a turbomachine can form a rotor drum.
  • rotor interior and rotor exterior refer to the spaces inside and outside the rotor drum of rotors.
  • the rotor interior is thus limited radially outward substantially by one or more rotor arms.
  • In the axial direction of the rotor interior is essentially limited by rotor disks, wherein between a shaft to which the rotor drum is connected directly or indirectly and the rotor disks is generally formed a gap.
  • the rotor outer space is bounded radially inwardly substantially by one or more rotor arms.
  • the rotor outer space substantially comprises the main flow channel of the turbomachine. Between a rotor arm and the main flow channel, for example, stator inner rings, with or without inlet seals, can furthermore be arranged.
  • the rotor interior and / or the rotor outer space may comprise a plurality of rotor stages.
  • Rotor 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 positive and / or non-positive.
  • annular balancing frets within the rotor drum can be arranged annular balancing frets, in particular on the inside of the rotor arms.
  • the balancing collars can be frictionally connected to the rotor arms.
  • further balancing devices for example flanges with balancing weights fastened over the circumference, may be arranged.
  • the turbomachine is an axial flow machine, in particular a gas turbine, in particular an aircraft gas turbine.
  • the rotor drum according to the invention may be designed for use in a high-pressure compressor, in a low-pressure compressor, in a high-pressure turbine or in a low-pressure turbine of an aircraft engine.
  • a rotor arm may have one or more openings.
  • the openings may be arranged radially (perpendicular to the central axis of the rotor drum) or at a different angle in or on the rotor arm.
  • the openings are open to the rotor drum interior and the rotor drum outer space and form an opening between these two spaces or areas. The opening thus pierces the rotor arm from radially inward to radially outward.
  • the opening at the radially furthest or largest radius of the inner contour of the rotor drum can advantageously enable or bring about centrifugal force-dependent flow during rotation, in particular during operational use of the rotor drum of fluids, in particular bearing oil, from the rotor drum into the rotor drum outer space (radially outside the rotor drum) ,
  • you restart the Aero engine could then get this oil in the engine housing in the supply air of the cabin air and contaminate the cabin air in this way.
  • the interior of the rotor drum is shaped in such a way that centrifugal force accumulations of oil can flow out or escape through one or more openings into the outer space of the rotor drum.
  • the interior is designed in particular flow optimized.
  • bearing oil for example in a so-called front-hub and / or rear-hub bearing of a rotor, can evaporate in the bearing area due to increased frictional heat in the bearing and then condense again in the rotor drum according to the invention.
  • the condensation process can occur in a rotor drum, which is arranged in the immediate vicinity of the storage.
  • the condensed bearing oil can exit through the radial opening of the rotor drum according to the invention or can be thrown out into the main flow channel and then advantageously exit from the turbomachine with the main flow.
  • a bearing oil mist can escape through the radial opening of the rotor drum according to the invention.
  • the bearing oil mist can exit during operation of the turbomachine in the main flow channel and exit with the main flow from the turbomachine.
  • the rotor arm has at least one sealing tip for forming a gap seal against a stator.
  • the stator may be a stator stage or a stator, in particular a stator with adjustable guide vanes.
  • the opening is arranged axially between the at least one sealing tip and a radially inwardly directed rotor disk of the second rotor main body.
  • the at least one rotor arm of the rotor drum according to the invention has a balancing ring.
  • the balancing ring is arranged in particular radially on the outside of the rotor arm.
  • a balancing ring can be called a balancing band.
  • the balancing ring is disposed at the upstream and / or downstream end or end portion of the rotor arm.
  • the terms upstream and downstream refer to the main flow direction of the turbomachine.
  • the end region or the end regions of the rotor arms can be regions for connecting to further components of the turbomachine.
  • the end regions can have positive connections to further rotor main bodies.
  • the end regions can be flanged by means of screw connections to further rotor main body.
  • An end region of a rotor arm may have a balancing ring and at the same time have a form-locking connection to a further rotor disk.
  • Such an end portion may be referred to as an integral end portion because two functions, balancing and joining, are achieved simultaneously.
  • a rotor base body which has no rotor arm does not have a balancing device.
  • a balancing device may for example be a balancing ring or balancing weights arranged on a flange.
  • the balancing ring is positively connected to the rotor arm.
  • a non-positive connection can be achieved for example by shrinking.
  • a frictional connection may be a connection by means of a press fit.
  • the connection of the balancing ring with the rotor arm has no screw connection.
  • One by means of a non-positive connection Applied balancing ring can be advantageous by means of a material-removing method, eg. As milling, drilling or grinding, be balanced without the balancing ring must be dismantled by the rotor arm.
  • the balancing ring is materially connected to the rotor arm.
  • a material-locking connection is, for example, an adhesive connection, a welded connection or a connection by means of a generative production method.
  • the rotor arm is made of a first material or comprises a first material.
  • the balancing ring can be made of a second material or have a second material.
  • the first material and the second material are different.
  • the balancing ring has at least one area for removing material for balancing the rotor on the circumference of the balancing ring.
  • Material removing processes for material removal of the balancing ring are, for example, milling, drilling or grinding.
  • balancing device may comprise one or more balancing rings, one or more balancing weights and other devices for balancing or balancing a component.
  • Some or all embodiments according to the invention may have one, several or all of the advantages mentioned above and / or below.
  • oil accumulations for example storage oil accumulations
  • Bearing oil or bearing oil mist can be transported in a rotating rotor drum according to the invention directly through the opening at the largest radius of the inner contour of the rotor drum in the main stream of the guide and impeller blading and the outlet of the turbomachine to get redirected. Due to this rapid removal, a possible risk of fire from the oil can at least be reduced. Collecting oil and / or condensing an oil mist during a standstill of the rotor drum with a subsequent possible transport of the oil from the main flow in branches for the bleed air, z. B. for the cabin air in aircraft, can be advantageously avoided.
  • Fig. 1 shows a rotor drum 100 according to the invention with an opening as a Abschleuderbohrung 1, a first rotor body 3, a second rotor body 5, a rotor arm 7 and a balancing ring 9 in a sectional view.
  • the Abschleuderbohrung 1 is an opening of the rotor drum 100 in the boundary radially outward.
  • the rotor drum 100 has a radially inwardly open shape.
  • the rotor drum 100 which is directed radially inward (counter to the radial direction r, relative to the axis of rotation 11 of the rotor drum 100), is bounded in the axial direction a by a first rotor disk 13 and a second rotor disk 15.
  • the two rotor disks 13, 15 are sections of the two rotor base bodies 3, 5.
  • the first rotor disk 13 is arranged upstream, the second rotor disk 15 downstream, the main flow direction 17 being represented by an arrow.
  • the Abschleuderbohrung 1 is disposed at the largest radius 19 an inner contour 21 of the rotor drum 100.
  • Abschleuderbohritch 1 in Fig. 1 not shown, in particular in the rotor arm 7, be arranged.
  • the rotor drum 100 may extend and / or expand further upstream and / or downstream in further embodiments and comprise further rotor arms. Likewise, further Abschleuderbohritch be arranged in the other rotor arms.
  • a multi-stage high pressure compressor (or low pressure compressor, high pressure turbine, low pressure turbine) of an aircraft engine may include a rotor drum.
  • the Abschleuderbohrung 1 can during a rotation of the rotor drum 100 about the rotation axis 11 (in the context of a proposed operation of the rotor drum 100, for example in an aircraft engine) bearing oil, bearing oil mist or other fluids from the rotor drum 100 into a rotor outer space 23 are transported. This transporting or draining of a fluid is caused or caused by the centrifugal force of the fluid.
  • the flow properties are influenced, for example, by the viscosity and temperature.
  • the size of an opening cross-section (or the diameter) of the Abschleuderbohrung 1 influences the outflow of a fluid from the rotor drum 100 in the rotor outer space 23rd
  • the balancing ring 9 in the embodiment of Fig. 1 on the outer side (with respect to the radial direction r) of the rotor drum 100 favors a drainage of oil in the rotor drum 100 through the Abschleuderbohrung 1. If the balancing ring 9 on the inside of the rotor drum 100 on the rotor arm 7 arranged (in Fig. 1 not shown), the oil could accumulate in the rotor interior 22 due to centrifugal force. This accumulated oil would then flow into the interior only when the rotor drum 100 stopped. In a restart of the rotational movement of the rotor drum 100 then this oil could escape through the Abschleuderbohrung 1.
  • the oil from the rotor outer space 23 could then enter the cabin air of an aircraft and cause contamination through the bleed air, which is discharged from the main flow, branched or tapped.
  • This risk of contamination is advantageously prevented or at least reduced by the arrangement of the balancing ring 9 on the outside of the rotor drum 100.
  • the first rotor base body 3 is positively connected in the region of the balancing ring 9 with the second rotor base body 5 via the rotor arm 7 (shown by means of the dashed circle 25).
  • the rotor main body 3, 5 are in the embodiment of Fig. 1 integral with blades 27.
  • the rotor arm 7 has sealing tips 29, which can form a gap for minimizing a leakage flow between the rotor drum 100 and a stator 200 with a so-called inlet seal 31.
  • the inlet seal 31 is connected to an inner ring 33.
  • the inner ring 33 is connected to adjustable guide vanes 35 of the stator 200.
  • the guide vanes 35 are rotatably arranged and supported about their longitudinal axis by means of an inner journal 37.
  • Fig. 2 shows a further rotor drum 100 according to the invention with one opposite Fig. 1 changed arrangement of the Abschleuderbohrung 1.
  • the longitudinal alignment of the Abschleuderbohrung 1 is aligned perpendicular to the central axis or axis of rotation of the rotor drum 100.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP15166681.5A 2015-05-07 2015-05-07 Tambour-rotor pour une turbomachine et compresseur Withdrawn EP3091178A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP15166681.5A EP3091178A1 (fr) 2015-05-07 2015-05-07 Tambour-rotor pour une turbomachine et compresseur
US15/091,320 US20160327065A1 (en) 2015-05-07 2016-04-05 Rotor drum for a turbomachine and compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15166681.5A EP3091178A1 (fr) 2015-05-07 2015-05-07 Tambour-rotor pour une turbomachine et compresseur

Publications (1)

Publication Number Publication Date
EP3091178A1 true EP3091178A1 (fr) 2016-11-09

Family

ID=53054925

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15166681.5A Withdrawn EP3091178A1 (fr) 2015-05-07 2015-05-07 Tambour-rotor pour une turbomachine et compresseur

Country Status (2)

Country Link
US (1) US20160327065A1 (fr)
EP (1) EP3091178A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3192966B1 (fr) * 2016-01-14 2021-05-19 MTU Aero Engines AG Rotor pour une turbomachine axiale avec une bride d'équilibrage orientée axialement et compresseur
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 (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016218285A1 (de) * 2016-09-23 2018-03-29 MTU Aero Engines AG Rotorstufe für eine Strömungsmaschine, Rotortrommel und Rotor
US10865646B2 (en) 2017-05-04 2020-12-15 Rolls-Royce Corporation Turbine assembly with auxiliary wheel
US10968744B2 (en) 2017-05-04 2021-04-06 Rolls-Royce Corporation Turbine rotor assembly having a retaining collar for a bayonet mount
US20180320522A1 (en) * 2017-05-04 2018-11-08 Rolls-Royce Corporation Turbine assembly with auxiliary wheel
US10774678B2 (en) 2017-05-04 2020-09-15 Rolls-Royce Corporation Turbine assembly with auxiliary wheel
GB201715169D0 (en) 2017-09-20 2017-11-01 Rolls Royce Plc Seal for a gas turbine
FR3096073B1 (fr) * 2019-05-13 2021-05-14 Safran Aero Boosters Tambour de rotor pour une turbomachine
IT201900014724A1 (it) * 2019-08-13 2021-02-13 Ge Avio Srl Elementi di trattenimento delle pale per turbomacchine.
DE102021123173A1 (de) * 2021-09-07 2023-03-09 MTU Aero Engines AG Rotorscheibe mit gekrümmtem Rotorarm für eine Fluggasturbine

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US4835827A (en) * 1987-09-08 1989-06-06 United Technologies Corporation Method of balancing a rotor
US20110193293A1 (en) * 2010-02-10 2011-08-11 Rolls-Royce Plc Seal arrangement
FR2961249A1 (fr) * 2010-06-10 2011-12-16 Snecma Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine

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DE69305326T2 (de) * 1992-02-10 1997-05-07 United Technologies Corp Ejektor für kühlfluid
US5388963A (en) * 1993-07-02 1995-02-14 United Technologies Corporation Flange for high speed rotors
DE10310815A1 (de) * 2003-03-12 2004-09-23 Rolls-Royce Deutschland Ltd & Co Kg Wirbelgleichrichter in Röhrenbauweise mit Haltering
FR2935764B1 (fr) * 2008-09-05 2014-06-13 Snecma Carter de compresseur resistant au feu de titane, compresseur haute pression comprenant un tel carter et moteur d'aeronef equipe d'un tel compresseur
US9297258B2 (en) * 2009-06-16 2016-03-29 General Electric Company Trapped spring balance weight and rotor assembly
EP3091179B1 (fr) * 2015-05-07 2021-06-30 MTU Aero Engines AG Système de rotor pour une turbomachine et compresseur
BE1023233B1 (fr) * 2015-07-01 2017-01-05 Safran Aero Boosters S.A. Tambour perfore de compresseur de turbomachine axiale
DE102016218285A1 (de) * 2016-09-23 2018-03-29 MTU Aero Engines AG Rotorstufe für eine Strömungsmaschine, Rotortrommel und Rotor

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Publication number Priority date Publication date Assignee Title
US4835827A (en) * 1987-09-08 1989-06-06 United Technologies Corporation Method of balancing a rotor
US20110193293A1 (en) * 2010-02-10 2011-08-11 Rolls-Royce Plc Seal arrangement
FR2961249A1 (fr) * 2010-06-10 2011-12-16 Snecma Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3192966B1 (fr) * 2016-01-14 2021-05-19 MTU Aero Engines AG Rotor pour une turbomachine axiale avec une bride d'équilibrage orientée axialement et compresseur
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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US20160327065A1 (en) 2016-11-10

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