EP2705218A2 - Dispositif de recouvrement, corps de base de rotor intégralement à aubage, procédé et turbomachine - Google Patents

Dispositif de recouvrement, corps de base de rotor intégralement à aubage, procédé et turbomachine

Info

Publication number
EP2705218A2
EP2705218A2 EP12769875.1A EP12769875A EP2705218A2 EP 2705218 A2 EP2705218 A2 EP 2705218A2 EP 12769875 A EP12769875 A EP 12769875A EP 2705218 A2 EP2705218 A2 EP 2705218A2
Authority
EP
European Patent Office
Prior art keywords
cover
channels
integrally bladed
bladed rotor
turbomachine
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Withdrawn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
EP12769875.1A
Other languages
German (de)
English (en)
Inventor
Frank Stiehler
Manuel Hein
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
Publication of EP2705218A2 publication Critical patent/EP2705218A2/fr
Withdrawn legal-status Critical Current

Links

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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • 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

Definitions

  • the invention relates to a covering device for an integrally bladed rotor base body according to the preamble of patent claim 1, an integrally bladed rotor base body with such a covering device, a method for assembling such an integrally bladed rotor base body and a turbomachine.
  • Integrally bladed rotor main body of a rotor for turbomachines such as aircraft engines with a variety of bonded to a disc or annular body cohesively and forming a blade row blades have for manufacturing reasons regularly between blade roots or blade shafts adjacent blades a channel-like passage through which in axial Direction of cooling air can flow from the high pressure side to the low pressure side.
  • a channel-like passage through which in axial Direction of cooling air can flow from the high pressure side to the low pressure side.
  • the channels on the outlet side, i. low pressure side to close by a cover.
  • the cover device comprises a sheet-like ring, which surrounds the base body and is arranged between a radially inner hook-shaped holder and a radially outer hook-shaped holder.
  • the object of the invention is to provide a covering device for an integrally bladed rotor body of a turbomachine, which eliminates the aforementioned disadvantages and They are also easy to assemble and disassemble. Furthermore, it is an object of the invention to provide an integrally bladed rotor main body for a turbomachine with an optimized covering device, a method for assembling such an integrally bladed rotor main body and a turbomachine.
  • a covering device for an integrally bladed rotor main body of a turbomachine for adjusting a cooling air flow from a high pressure side to a low pressure side through channels formed between adjacent blades has a plurality of cover members individually insertable into the channels and having at least one circumferential sealing surface.
  • the cover elements are inserted into the channels, so that the formation of the aforementioned brackets is not necessary. Furthermore, it is advantageous that the cover elements can be arranged virtually arbitrarily in the channels by the respective at least one circumferential sealing surface, which simplifies their assembly and disassembly.
  • the ⁇ ffhungsqueritese the channels can be set individually. For example, it is possible to control individual channels and to reduce the number of other channels.
  • the cover members have a cup-like or hat-like profile with an outer body portion such as a collar.
  • the body sections allow for mounting an accurate positioning of the cover in the channels. After assembly, the body sections act as axial securing elements of the centrifugal force loaded covering elements.
  • the cover elements are centrifugally activated.
  • the cover elements are only movable or loose to position in the channels, which further simplifies both the assembly and disassembly.
  • the cover can have according to a modular design a variety of mountable and disassembled items.
  • the modular construction allows different cover plates and connecting arms to be combined with each other, so that a large number of different cover elements can be produced with a small number of cover plates and connecting arms.
  • the modular design allows that when a defect of one of the components only the defective component must be replaced with a new part.
  • the cover elements on two cover plates and the cover plates releasably interconnecting connecting arm.
  • a double cross-sectional adjustment of the channels is achieved, so that it is possible, for example, to enter via the front cover a reduced flow of cooling air into the channels to then supply them to a scoop-leaf internal cooling air system.
  • the channels are then closed via the rear cover plate, so that an axial cooling air flow through the channels is prevented and the reduced cooling air flow is used exclusively for internal blade cooling.
  • the cover plates can stabilize each other in particular in combination with the centrifugally activated cover elements, so that they can not tilt or jam in the channels and always an optimal seal is achieved.
  • the cover elements can have overflow openings.
  • the overflow openings can be e.g. be formed as holes or axial circumferential grooves in the respective sealing surface.
  • An integrally bladed rotor main body according to the invention for a turbomachine with a multiplicity of moving blades has a covering device with a plurality of covering elements for setting a cooling air flow from a high-pressure side to a low-pressure side. pressure side through channels which are formed between adjacent blades, wherein in each channel at least one cover element is inserted with at least one circumferential sealing surface.
  • Such integrally bladed rotor main body is characterized by a quiet running behavior, since the cover are arranged only in the channels and no or only very small additional masses are introduced into the blade, so that by the cover or no or almost no repercussions on the vibration mechanics of the blades takes place. In addition, a good mutual demarcation and management of the cooling air flows and the hot gas flows is achieved.
  • the sealing surfaces are arranged in the channels such that they are positioned with their at least one sealing surface inlet or outlet side and thus end in the channels, whereby in particular the assembly and disassembly is simplified.
  • the cover elements can each be fixed under force and form fit in the channels and abut with their respective radially outer body portion of the front side of the blades, so that the cover are securely received in the channels and are accurately positioned by the body sections. Due to the positive and positive fit thus a secure positional fixation and optimum sealing is achieved. In addition, component and assembly tolerances can be compensated in particular by the frictional connection.
  • the cover elements are arranged axially displaceable in the channels and axially secured with a securing element at least on one side.
  • the cover elements Upon rotation of the rotor base body, the cover elements are moved radially outward in the channels due to the centrifugal force and are then pressed with their sealing surfaces against wall sections of the channels.
  • the fuse elements Depending on the orientation and profile of the channels prevent the fuse elements thereby falling out of the cover at a standstill or squeezing the cover during operation. It can be provided for a plurality of cover for each cover a single fuse element or a fuse element.
  • the cover elements are first formed with a cross section in the region of its at least one sealing surface such that it corresponds approximately to a cross section of a receiving channel section. Then the cover elements are positioned in the channel sections.
  • the assembly is facilitated and also ensures that the cover can be positioned in its desired position.
  • the cover elements for fixing the position are radially expanded by a deformation, wherein advantageously a radially outer body portion is formed quasi as a positioning aid and after forming as a fuse element, so that the cover elements are positively and positively held in the channels.
  • the cover elements are preformed with the collar, so that the degree of deformation is kept low and damage to the cover is prevented due to excessive deformation forces.
  • the collar can also already have their final contour, so that a reshaping of the collar is eliminated.
  • the cover elements are pressed in and adapt to, for example, a radially outward and conically rising inner contour of the channels. Thus they are secured in both axial directions.
  • cover elements can also be accommodated with tolerances in the channels.
  • cover elements consist of a plurality of individual parts
  • these are assembled at least occasionally after insertion into the channel, so that component tolerances of the channels can be compensated by the choice of suitable individual parts.
  • a turbomachine according to the invention has at least one integrally bladed rotor main body according to the invention and is distinguished by a high delimitation of a hot gas flow from a cooling air flow, by a smooth running behavior and by a high ease of maintenance with respect to its blade-side axial covering device.
  • FIG. 1 shows a front view of a portion of an integrally bladed rotor body in the region of two adjacent blades with a first embodiment of a cover according to the invention
  • FIG. 2 shows a rear view of a cover element shown in FIG. 1,
  • FIG. 3 shows a section in the radial plane of the integrally bladed rotor main body from FIG. 1,
  • FIG. 4 shows a frontal view of a section of an integrally bladed rotor base body in the region of a blade with a second embodiment of the covering device according to the invention
  • Figure 5 is a side view of the integrally bladed rotor body of Figure 4, and
  • FIG. 6 shows a rear view of the integrally bladed rotor main body from FIG. 4.
  • Figures 1 and 2 show a portion of an integrally bladed rotor body 1 for a turbomachine such as an aircraft engine in a front perspective view ( Figure 1) and in a rear perspective view ( Figure 2).
  • the rotor base body 1 has a multiplicity of adjacent rotor blades 2 forming a blade row, which are connected to a turbine-side ring-shaped or disk-shaped base body 4.
  • the blades each have a blade root 6, a blade neck 8, an airfoil 10 and a platform 12 disposed between the blade neck 8 and the airfoil 10 with a forward high pressure side projection 14 and a downstream low pressure side projection 16, viewed in the flow direction of a hot gas flow.
  • the blade root 6 is formed either as an integral part of the blade 2 or as a separately formed and subsequently joined to the blade 2 component. He is with its radially inner peripheral surface cohesively connected, for example by means of a Reibsch spavons to a base of the base body 4, not shown, and has two shown in Figure 2 concave side walls 18, 20, each pass flush in a base body side peripheral wall 22.
  • the blade neck 8 is formed widened viewed in relation to the blade root 6 in the circumferential direction. He has two laterally opposite to each other formed recesses 24, which are surrounded by a respective side surface 26, 28.
  • the side surfaces 26, 28 respectively extend over the projections 14, 16 and are provided in a region remote from the platform and near the channel, each having a downgrading 30 extending in the axial direction.
  • the side surfaces 26, 28 in the region of the rearward projections 16, each having a circumferentially extending downgrade 32 for establishing fluid communication between a cavity 34 formed by the respective opposing recesses 24 (see FIG 3) and a low pressure side of the blades 2 may be provided.
  • the airfoil 10 extends approximately centrally from the platform 12 and is conventional in nature, so that a single explanation is omitted. In principle, it can be provided with an internal cooling system (see FIG. 5).
  • the platform 12 is formed by the blade neck 8 and forms with platforms 12 of adjacent blades 2 a numbered in Figure 2 radially outer hot gas flow side annulus 38 and a radially inner cooling air flow side cooling chamber 40.
  • adjacent blades 2 each have a lateral contact portion 36.
  • the adjacent blades touch 2 with their opposite side surfaces 26, 28 and thus form the annulus 38 and the cooling chamber 40.
  • the opposite side walls 18, 20 of the rotor blades 2 define in the circumferential direction in each case a channel 42, which is in radial fluid communication with the cavity 34 formed by the recesses 24 via a gap 44 formed by the downgrades 30.
  • the channels 42 are inclined relative to the axis of rotation and each have a high-pressure side. a radially inwardly located inlet and a low-pressure-side radially outer outlet.
  • the respectively oppositely extending in the circumferential direction, not visible in the sectional view downgrades 32 of the blades 2 each form a communicating with the cooling chamber 40 in the axial direction low-pressure side réelleöffhung.
  • a first cover 46 according to the invention with a plurality of cup-like cover members 48 is provided.
  • the cover elements 48 each have a cup-shaped profile with a conical wall 50, a bottom 52 and a head-side radially outer collar 54. They consist of a heat-resistant steel which is readily cold-deformable, such as a nickel-based alloy, and are preferably in the channels 42 on the inlet side arranged.
  • the conical wall 50 has cross sections which correspond to cross sections of an inlet-side surface section 56 of the channels 42 receiving it and forms an outer peripheral sealing surface 58. In the mounted state shown, the wall 50 with its sealing surface 58 seals against the surface section 56.
  • the conicity of the wall 50 corresponds to the conicity of the respective channel 42, so that in the exemplary embodiment shown in Figures 1 and 2, the cover 48 are radially expanded starting from its collar 54 in the direction of its bottom 52.
  • the bottom 52 is formed closed. However, it may have an overflow orifice 60 through which cooling air can flow into an internal scoop-blade side cooling system through an input bore 62 (see Figure 5) passing through the side walls 26,28.
  • the collar 54 forms during assembly in each case a positioning aid for the precise positioning of the respective cover 48 in the channels 42.
  • it In the assembled state, it is in contact with a channel 42 surrounding the frame-like end face portion 64 of Blade Feet 6 and then acts as an integral one-sided axial securing element.
  • the conical wall 50 In combination with the conical wall 50 thus both a movement of the respective cover 48 in the flow direction and in the opposite direction is prevented.
  • the cover elements 48 are pushed as shown in the figure 2 according to the arrow from the low pressure side to the high pressure side and thus backward into the channels 42 until the cover 48 projects with its head portions of the channels 42 inlet side. Then, a tool is attached to the cover 48 and the collar 54 formed by crimping under pressure in the flow direction or from the front. At the same time, the sealing surfaces 58 are pressed against the surface portions 56 of the channels 42, so that the cover 48 are received without play and under pressure in the channels 42. The cover 48 are now due to the taper of the channels 42 and the subsequently flanged collar 54 non-positively and positively secured against axial displacements.
  • the collar 54 may be slightly crimped even before the onset of the cover 48.
  • the collar 54 can be made even before the insertion of the cover 48 into the channels 42 to its final dimensions, so that a reshaping of the collar 54 is omitted.
  • the cover elements 48 are inserted from the front into the channels 42 and brought into contact with their collar 54 in abutment with an unnumbered front disc wall for pressing.
  • a further variant of the method envisages arranging the cover elements 48 in the channels 42 with tolerances.
  • the cover 48 are plastically deformed so that they are secured by means of positive locking against falling out of the channels 42, however, are pressed under centrifugal force radially outwards and the channels 42 close.
  • the cover elements 48 can also be arranged in the channels 42 on the rear side and thus on the outlet side. Likewise, the cover elements 48 can be arranged on the inlet side and the outlet side and thus in pairs in channels 42.
  • FIGS. 4, 5 and 6 show a second exemplary embodiment of an embodiment according to the invention.
  • the covering device 46 has, as shown in FIG. 4, a plurality of centrifugal force-activatable cover elements 48 arranged in the channels 42, each having a dumbbell-like shape with two end covers 66, 68 which are detachably connected to one another via a connecting arm 70.
  • the cover plates 66, 68 are plate-like bodies, preferably cast bodies, with a cross section corresponding to the respective channel cross section. As shown in FIG. 5, each has a circumferential sealing surface 58, 72 for engagement with corresponding inlet-side and outlet-side surface portions 56, 74 of FIGS Channels 42.
  • the cover disks 66, 68 may have corresponding overflow openings (not shown) in the form of axial circumferential grooves or bores (see overflow opening 60 in FIG.
  • the connecting arm 70 has a T-shaped cross-section with a plurality of weight-reducing openings 76, numbered in FIG. 5. It is fixedly connected at one end to one of the cover disks 66. With its free end portion 78 it is guided by an opening of the free cover 68 and releasably connected by means of a locking element 80 such as a sheet metal fitting or a wire with this.
  • a locking element 80 such as a sheet metal fitting or a wire with this.
  • the connecting arm 70 is in each case firmly connected to the inlet-side cover disks 66.
  • the cover members 48 are forced outwardly into the channels 42 due to centrifugal force.
  • an axial stop (not shown) is provided on the blade side.
  • the channels 42 have an outlet radially outwardly of their inlet and are tapered in the direction of the outlet, a stop to prevent them from falling out at standstill is necessary. If the channels 42 have a constant cross-section over their axial length, a stop is necessary both on the inlet side and on the outlet side.
  • the mounting of the cover 48 is carried out in the channels 42, wherein only the cover plates 66 is positioned with the connected connecting arm 70 in the channels 42 and then the free cover 68 is attached to the free end portion of the respective connecting arm 70. Thereafter, the securing of the free cover plates 68 takes place at the end portions 78 by means of the positive locking elements 80th
  • a covering device for an integrally bladed rotor body of a turbomachine for suppressing or reducing a cooling air flow from a high pressure side to a low pressure side through channels formed between adjacent blades, wherein a plurality of cover members are provided, which are individually insertable into the channels, and at least have a circumferential sealing surface, an integrally bladed rotor main body with such a covering device, a method for producing such an integrally bladed rotor main body, and a turbomachine with such an integrally bladed rotor main body.

Landscapes

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

Abstract

L'invention concerne un dispositif de recouvrement pour un corps de base de rotor intégralement à aubage d'une turbomachine, destiné à empêcher ou à réduire un courant d'air de refroidissement d'un côté haute pression à un côté basse pression à travers des canaux formés entre des aubes mobiles voisines, une pluralité d'éléments de recouvrement pouvant être introduits individuellement dans les canaux et comprenant au moins une surface d'étanchéité côté périphérie. L'invention concerne également un corps de base de rotor intégralement à aubage doté d'un dispositif de recouvrement de ce type, un procédé de fabrication d'un corps de base de rotor intégralement à aubage de ce type et une turbomachine dotée d'un tel corps de base de rotor intégralement à aubage.
EP12769875.1A 2011-05-02 2012-04-25 Dispositif de recouvrement, corps de base de rotor intégralement à aubage, procédé et turbomachine Withdrawn EP2705218A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102011100221.2A DE102011100221B4 (de) 2011-05-02 2011-05-02 Integral beschaufelter Rotorgrundkörper, Verfahren und Strömungsmaschine
PCT/DE2012/000431 WO2012149925A2 (fr) 2011-05-02 2012-04-25 Dispositif de recouvrement, corps de base de rotor intégralement à aubage, procédé et turbomachine

Publications (1)

Publication Number Publication Date
EP2705218A2 true EP2705218A2 (fr) 2014-03-12

Family

ID=47008202

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12769875.1A Withdrawn EP2705218A2 (fr) 2011-05-02 2012-04-25 Dispositif de recouvrement, corps de base de rotor intégralement à aubage, procédé et turbomachine

Country Status (4)

Country Link
US (1) US20140161590A1 (fr)
EP (1) EP2705218A2 (fr)
DE (1) DE102011100221B4 (fr)
WO (1) WO2012149925A2 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101663306B1 (ko) 2015-10-02 2016-10-06 두산중공업 주식회사 가스터빈 디스크
CN106150563A (zh) * 2016-08-25 2016-11-23 张家港市中程进出口贸易有限公司 内燃机汽封
US10648354B2 (en) 2016-12-02 2020-05-12 Honeywell International Inc. Turbine wheels, turbine engines including the same, and methods of forming turbine wheels with improved seal plate sealing
US11111804B2 (en) * 2019-03-11 2021-09-07 Raytheon Technologies Corporation Inserts for slotted integrally bladed rotor

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL70887C (fr) * 1944-12-22 1900-01-01
US3291446A (en) * 1965-04-13 1966-12-13 Chrysler Corp Turbine wheel
US3847506A (en) 1973-11-29 1974-11-12 Avco Corp Turbomachine rotor
GB2043797A (en) * 1979-03-10 1980-10-08 Rolls Royce Bladed Rotor for Gas Turbine Engine
FR2503247B1 (fr) * 1981-04-07 1985-06-14 Snecma Perfectionnements aux etages de turbine a gaz de turboreacteurs munis de moyens de refroidissement par air du disque de la roue de la turbine
US4505640A (en) * 1983-12-13 1985-03-19 United Technologies Corporation Seal means for a blade attachment slot of a rotor assembly
DE19516694C2 (de) * 1995-05-06 2001-06-28 Mtu Aero Engines Gmbh Einrichtung zur Fixierung von Laufschaufeln am Laufrad, insbesondere einer Turbine eines Gasturbinentriebwerks
US6945749B2 (en) * 2003-09-12 2005-09-20 Siemens Westinghouse Power Corporation Turbine blade platform cooling system
US7097429B2 (en) * 2004-07-13 2006-08-29 General Electric Company Skirted turbine blade
US7244101B2 (en) * 2005-10-04 2007-07-17 General Electric Company Dust resistant platform blade
US20090148298A1 (en) * 2007-12-10 2009-06-11 Alstom Technologies, Ltd. Llc Blade disk seal
US8047786B2 (en) 2008-01-10 2011-11-01 General Electric Company Apparatus for plugging turbine wheel holes
FR2931873B1 (fr) * 2008-05-29 2010-08-20 Snecma Ensemble d'un disque de turbine d'un moteur a turbine a gaz et d'un tourillon support de palier,circuit de refroidissement d'un disque de turbine d'un tel ensemble.
DE102009007468A1 (de) 2009-02-04 2010-08-19 Mtu Aero Engines Gmbh Integral beschaufelte Rotorscheibe für eine Turbine
DE102009011879A1 (de) * 2009-03-05 2010-09-16 Mtu Aero Engines Gmbh Integral beschaufelter Rotor und Verfahren zur Herstellung eines integral beschaufelten Rotors
US8459953B2 (en) * 2010-01-19 2013-06-11 General Electric Company Seal plate and bucket retention pin assembly
US9133855B2 (en) * 2010-11-15 2015-09-15 Mtu Aero Engines Gmbh Rotor for a turbo machine
JPWO2016143103A1 (ja) * 2015-03-11 2017-11-30 株式会社東芝 タービン

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
None *
See also references of WO2012149925A2 *

Also Published As

Publication number Publication date
WO2012149925A2 (fr) 2012-11-08
DE102011100221B4 (de) 2017-03-09
DE102011100221A1 (de) 2012-11-08
US20140161590A1 (en) 2014-06-12
WO2012149925A3 (fr) 2013-02-28

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