EP3412874A1 - Bague interne d'une turbomachine divisée axiale - Google Patents

Bague interne d'une turbomachine divisée axiale Download PDF

Info

Publication number
EP3412874A1
EP3412874A1 EP18171212.6A EP18171212A EP3412874A1 EP 3412874 A1 EP3412874 A1 EP 3412874A1 EP 18171212 A EP18171212 A EP 18171212A EP 3412874 A1 EP3412874 A1 EP 3412874A1
Authority
EP
European Patent Office
Prior art keywords
ring
partial
inner ring
support surfaces
partial ring
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Withdrawn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
EP18171212.6A
Other languages
German (de)
English (en)
Inventor
Karl Maar
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 EP3412874A1 publication Critical patent/EP3412874A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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

Definitions

  • the present invention relates to an axially divided inner ring for attachment to, in particular adjustable, vanes of a turbomachine, in particular a compressor or turbine stage of a gas turbine, a guide grid and a turbomachine, in particular gas turbine, with the inner ring and method for its production and assembly.
  • An object of an embodiment of the present invention is to improve an axially split inner ring.
  • Claims 12-15 provide protection for a guide grid and a turbomachine with (at least) an inner ring described here, or a method for producing or mounting an inner ring described here.
  • Advantageous embodiments of the invention are the subject of the dependent claims.
  • the functionality of a screw the two sub-rings set both in the radial direction and in the axial direction to each other, distributed to the dowel pins and the support.
  • the assembly improves, reduces the installation space and / or the reliability, in particular strength, of the connection can be improved.
  • the directional indication "axial” refers in a usual way to a direction parallel to a rotational or (main) machine axis of the turbomachine
  • the direction indication “circumferential direction” corresponds to a direction of rotation about this rotation or (main) machine axis
  • the second partial ring is or is clamped in the axial direction between the two mutually facing support surfaces of the first partial ring, in particular elastically.
  • the second part-ring has at least one, in particular radially inner or inner, annular or circumferential groove for reducing its rigidity in the axial direction, which is communicated or connected in a further development with at least one recess into which one of the dowel pins is plugged in.
  • an assembly and / or clamping of the second partial ring and / or a production of the recess (s) can be improved.
  • the second part-ring in particular with support surfaces, contacts the two mutually facing support surfaces of the first part-ring or lies directly or directly against it, in an embodiment with an interference fit or under prestress.
  • the second sub-ring by the or between the two support surfaces contacting it, in particular elastic, compressed and thereby clamped, in particular by an axial distance or an axial clearance between the support surfaces is shorter than an axial distance of these contacting support surfaces of the second sub-ring or a wall thickness of the second sub-ring between the two support surfaces with undeformed second part ring.
  • the second partial ring is shrunk or clamped with a shrink fit between the two mutually facing support surfaces of the first partial ring, in particular by the first and / or second partial ring for assembly corresponding, in particular different, tempered, in particular cooled or warmed up, becoming or becoming.
  • play in the axial direction can be reduced or avoided and / or the fixation by the dowel pins in the radial direction can be assisted or relieved of frictional engagement.
  • spring means in particular a one or more parts, in particular beveled and / or curved, spring plate arranged
  • at least partially (engaging) in a groove (s) in the first part ring and / or a groove in the second part ring by which the second part ring between the mutually facing support surfaces of the first part ring, in particular elastically, is braced or is and over which the second sub-ring indirectly supported on the corresponding one of the two mutually facing support surfaces of the first sub-ring in the axial direction.
  • an assembly and / or disassembly can be improved, in particular in comparison to a contact of the partial ring with two mutually facing support surfaces.
  • the second sub-ring is supported in the axial direction directly with its supporting surfaces contacting the two axially facing support surfaces.
  • the second partial ring is supported in the axial direction on one or both support surfaces indirectly via (in each case) a one- or multi-part spring means.
  • a single- or multi-layer intermediate layer may be arranged or, in particular these embodiments or power flows as a support in the axial direction of the or the ( respective) support surface (s) of the first partial ring in the context of the present invention.
  • a dowel pin in one embodiment can be unilaterally secured in the axial direction or be.
  • a passage recess assembly can be improved in one embodiment.
  • One or more, in particular all, dowel pins are smooth or threadless in one embodiment or are or are not bolted to the first and / or second part ring.
  • compared to a screw assembly improves the installation, reduces the space and / or reliability, in particular strength, the connection can be improved.
  • one or more, in particular all, dowel pins are secured in the axial direction by a, in particular mono- or multi-part, securing means, in particular one-way, which is attached to one or both partial rings, in particular by frictional engagement, in particular by a single or multi-part, in particular bevelled and / or curved, locking plate or a one-part or multi-part wedge-like securing element or a one or more parts Securing wedge, which in one embodiment at least partially (engaging) in at least one (r) groove in the first part ring and / or at least one (r) groove in the second part ring, arranged, in particular frictionally engaged therein is or is.
  • a, in particular mono- or multi-part, securing means in particular one-way, which is attached to one or both partial rings, in particular by frictional engagement, in particular by a single or multi-part, in particular bevelled and / or curved, locking plate or a one-part or multi-part wedge-like securing element or
  • the likelihood of damage to the turbomachine can be reduced.
  • the securing means may comprise the spring means, in particular at the same time be the spring means.
  • the wedge-like securing means or the securing wedge in particular one or more parts of the securing wedge respectively, has a wall thickness increasing or decreasing in the circumferential direction.
  • the wedge-like securing means or the securing wedge can advantageously be fixed by friction in the groove (s).
  • the locking plate or the securing wedge is inserted in the circumferential direction in the groove (s). As a result, in one embodiment, the assembly can be facilitated.
  • the determination supported by the dowel pins in the radial direction and / or assembly can be improved.
  • the (end) flange is arranged in an embodiment frontally on the first part of the ring, he can in particular limit or complete the opposite surface of the first part of the ring.
  • the flange or collar between one end face and the other of the two support surfaces is arranged, in particular on the mating surface of the first part ring.
  • At least one of the support surfaces in a radially extending or radial groove, in particular annular or circumferential groove of the first partial ring is arranged, in particular formed, in particular in the groove in which the spring means is at least partially disposed or in which it intervenes.
  • At least one of the support surfaces is flat and / or at least one of the support surfaces is curved.
  • the first and / or second partial ring is / are or are segmented in the circumferential direction, in particular in two halves.
  • a production and / or assembly can be improved.
  • the inner ring has a, in particular integrally formed with the first and / or second part ring or on the first and / or second part ring, in particular non-destructive releasably, in particular materially, or non-destructively detachable, in particular friction and / or form-fitting, fixed , one or multi-part radial seal, which is arranged in a version radially inward on the inner or partial ring.
  • the inner ring can thus be in one embodiment in particular a sealing ring or seal carrier.
  • the first and second sub-rings form or limit blind-hole-like or through-recesses, in particular, bores in which the guide vanes are fastened, in particular cones of the guide vanes mounted directly or via bushings.
  • there is a parting plane of the first and second part ring in one embodiment at least substantially symmetrical, in or through these recesses, in particular a contact plane between one of the support surfaces of the first part ring and a support surface of the second part ring resting thereon.
  • a production and / or assembly can be improved.
  • the cones of the guide vanes, the bushings and / or the first and / or second sub-ring, in particular the blind-hole-like or passage recesses are at least partially coated. In this way, in one embodiment, a bearing, in particular adjustment, of the guide vanes can be improved.
  • the first and / or second part ring in particular material removal, in particular-removing, in particular machined, machined, in particular (the) recesses for the dowel pins and / or vanes manufactured, in particular finished, and / or the first and / or second sub-segment segmented, while at least one, in particular finished, the support surfaces of the first sub-ring and one, in particular finished, supporting surface of the second sub-ring are arranged and pressed against each other in the axial direction against each other or are.
  • the two partial rings can be released from each other again, attached to the guide vanes and thereby connected by the dowel pins.
  • the second part ring in the axial direction between the two mutually facing support surfaces of the first part ring elastically clamped, in particular by shrinking or the or arranging the spring means (s), and, in particular before, simultaneously or subsequently, fixed in the radial direction by the dowel pins on the first part ring.
  • the two partial rings are displaced in the opposite direction to each other in the axial direction and at least partially surround the guide vanes, in particular their bearing journal.
  • a production, assembly and / or dimensional stability can be improved.
  • Fig. 1 shows a part of a guide grid of a turbomachine with an inner ring according to an embodiment of the present invention in a meridian section in which a (main) machine axis (horizontally in Fig. 1 ) lies.
  • the inner ring has a first partial ring 10 and a second partial ring 20 and is thus axially or in the axial direction (horizontally in FIG Fig. 1 ) (two) shared. In the circumferential direction is or are the inner ring or the partial rings 10, 20 (each) segmented in two halves.
  • a radial seal 19 is arranged.
  • the first and second part ring 10, 20 together form blind hole-like holes 52, in which pins 51 are rotatably supported by adjustable vanes 50, in one embodiment directly, in another embodiment via sockets (not shown).
  • the second partial ring 20 is in the radial direction (vertically in Fig. 1 ) fixed by a plurality of circumferentially distributed dowel pins 40 on the first part of the ring 10, the frictionally engaged in through holes 24 in the second part of ring 20 and partially inserted through this in blind hole-like holes 14 in the first part ring 10.
  • the second partial ring 20 is supported in the axial direction on two axially facing support surfaces 11, 12 of the first partial ring 10, wherein the support surface 12 is arranged in a radial groove 13 of the first partial ring 10.
  • a support surface 21 of the second sub-ring 20 contacts the support surface 11 of the first sub-ring 10, while between the second sub-ring 20 and the other support surfaces 12, a spring means 30 is arranged, through or over which the second sub-ring 20 in the axial direction at the other Supporting surface 12 of the two axially facing support surfaces 11, 12 of the first partial ring 10 is supported and thereby clamped between them in the axial direction.
  • This spring means 30 is partially arranged in the groove 13 of the first partial ring 10 and partially in a groove 23 of the second partial ring 20 or frictionally secured and thus acts at the same time as a securing means that secures the dowel pins 40 in the axial direction.
  • a support surface 25 of the second partial ring 20 is located radially outward (from above in FIG Fig. 1 ) on a mating surface 15 of the first part ring 10.
  • the support surface 11 and counter surface 15 of the first part ring 10 and the support surface 21 and support surface 25 of the second part ring 20 are first finished, arranged on each other and both partial rings 10, 20 clamped together in the axial direction by means not shown clamping means, so that support surface 11 and support surface 21 are pressed against each other.
  • the two partial rings 10, 20 are released from each other again and moved in opposite directions to each other for mounting in the axial direction, wherein they enclose the bearing pin 51 of the guide vanes 50. Then, the dowel pins 40 are inserted and then the spring means 30 in the grooves 13, 23 attached.
  • Fig. 2 shows a part of a guide grid of a turbomachine with an inner ring according to a further embodiment of the present invention in Fig. 1 corresponding representation.
  • Corresponding features are identified by identical reference numerals, so that reference is made to the preceding description and will be discussed below only differences.
  • the support surface 12 of the first part ring 10 is curved and not arranged in a groove, but on a radial collar 16, which in turn is arranged on the mating surfaces 15 of the first part ring 10.
  • the second sub-ring 20, which is in the execution of Fig. 2 supported directly on the support surfaces 11, 12 of the first part of ring 10 may be between these braced or be by an axial distance between the support surfaces 11, 12 is slightly shorter than an axial distance between these contacting support surfaces 21, 22 at undeformatorm second Partial ring 20.
  • first the support surfaces 11, 12 and counter surface 15 of the first part ring 10 and the support surfaces 21, 22 and support surface 25 of the second part ring 20 are finished, arranged on each other and both partial rings 10, 20 clamped together in the axial direction by means not shown clamping means ,
  • the two partial ring 10, 20 are released from each other and moved in opposite directions to each other for mounting in the axial direction, wherein they enclose the bearing pin 51 of the vanes 50, wherein the curvature of the support surface 12 favors assembly.
  • the dowel pins 40 are inserted and then the securing means 30 are secured in grooves of the first part ring 10.
  • Fig. 3 shows a part of a guide grid of a turbomachine with an inner ring according to a further embodiment of the present invention in Fig. 1, 2 corresponding representation.
  • Corresponding features are identified by identical reference numerals, so that reference is made to the preceding description and will be discussed below only differences.
  • the support surface 12 of the first part ring 10 is flat and not in a groove, but arranged on a radial end flange 17 which limits the mating surfaces 15 of the first part ring 10.
  • the second sub-ring 20, which is in the execution of Fig. 3 is also supported directly on the support surfaces 11, 12 of the first part ring 10, is clamped in the axial direction between these with a shrink or press fit.
  • annular groove 26 for reducing its rigidity in the axial direction.
  • the axially facing support surfaces 11, 12 and the counter surface 15 of the first partial ring 10 and the support surfaces (in FIG Fig. 3 is only the support surface 21 provided with reference numerals) and bearing surface of the second sub-ring 20 finished, arranged on each other and both sub-rings 10, 20 clamped together in the axial direction by the second sub-ring 20 is shrunk.
  • the two partial ring 10, 20 are released from each other again and moved towards the assembly in the axial direction in opposite directions, wherein they enclose the bearing pin 51 of the vanes 50, wherein the small radial height of the end flange 17 favors shrinking of the second partial ring 20 for assembly.
  • the dowel pins 40 are inserted and then the securing means 30 are secured in grooves of the first part ring 10.
  • the securing means 30 may be formed as a one-piece or multi-piece wedge with increasing wall thickness in the circumferential direction, the or its parts are inserted in the circumferential direction in the grooves 13, 23 and fixed therein by friction.

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)
EP18171212.6A 2017-06-08 2018-05-08 Bague interne d'une turbomachine divisée axiale Withdrawn EP3412874A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102017209682.9A DE102017209682A1 (de) 2017-06-08 2017-06-08 Axial geteilter Turbomaschinen-Innenring

Publications (1)

Publication Number Publication Date
EP3412874A1 true EP3412874A1 (fr) 2018-12-12

Family

ID=62142985

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18171212.6A Withdrawn EP3412874A1 (fr) 2017-06-08 2018-05-08 Bague interne d'une turbomachine divisée axiale

Country Status (3)

Country Link
US (1) US10858959B2 (fr)
EP (1) EP3412874A1 (fr)
DE (1) DE102017209682A1 (fr)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017209682A1 (de) * 2017-06-08 2018-12-13 MTU Aero Engines AG Axial geteilter Turbomaschinen-Innenring
US11066947B2 (en) 2019-12-18 2021-07-20 Rolls-Royce Corporation Turbine shroud assembly with sealed pin mounting arrangement
FR3108358B1 (fr) * 2020-03-19 2024-03-22 Safran Aircraft Engines Ensemble rotatif pour turbomachine comprenant une pièce annulaire de serrage.
US11255210B1 (en) 2020-10-28 2022-02-22 Rolls-Royce Corporation Ceramic matrix composite turbine shroud assembly with joined cover plate
US11761351B2 (en) 2021-05-25 2023-09-19 Rolls-Royce Corporation Turbine shroud assembly with radially located ceramic matrix composite shroud segments
US11629607B2 (en) 2021-05-25 2023-04-18 Rolls-Royce Corporation Turbine shroud assembly with radially and axially biased ceramic matrix composite shroud segments
US11286812B1 (en) 2021-05-25 2022-03-29 Rolls-Royce Corporation Turbine shroud assembly with axially biased pin and shroud segment
US11346237B1 (en) 2021-05-25 2022-05-31 Rolls-Royce Corporation Turbine shroud assembly with axially biased ceramic matrix composite shroud segment
US11346251B1 (en) 2021-05-25 2022-05-31 Rolls-Royce Corporation Turbine shroud assembly with radially biased ceramic matrix composite shroud segments
US11499444B1 (en) 2021-06-18 2022-11-15 Rolls-Royce Corporation Turbine shroud assembly with forward and aft pin shroud attachment
US11319828B1 (en) 2021-06-18 2022-05-03 Rolls-Royce Corporation Turbine shroud assembly with separable pin attachment
US11441441B1 (en) 2021-06-18 2022-09-13 Rolls-Royce Corporation Turbine shroud with split pin mounted ceramic matrix composite blade track
CN114135348B (zh) * 2021-11-11 2024-01-19 河北国源电气股份有限公司 一种汽轮机用可调集成式持环
US11773751B1 (en) 2022-11-29 2023-10-03 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating threaded insert
US12031443B2 (en) 2022-11-29 2024-07-09 Rolls-Royce Corporation Ceramic matrix composite blade track segment with attachment flange cooling chambers
US11840936B1 (en) 2022-11-30 2023-12-12 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating shim kit
US11713694B1 (en) 2022-11-30 2023-08-01 Rolls-Royce Corporation Ceramic matrix composite blade track segment with two-piece carrier
US11732604B1 (en) 2022-12-01 2023-08-22 Rolls-Royce Corporation Ceramic matrix composite blade track segment with integrated cooling passages
US11885225B1 (en) 2023-01-25 2024-01-30 Rolls-Royce Corporation Turbine blade track with ceramic matrix composite segments having attachment flange draft angles
US11879480B1 (en) 2023-04-07 2024-01-23 Rolls-Royce North American Technologies Inc. Sectioned compressor inner band for variable pitch vane assemblies in gas turbine engines

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070286719A1 (en) * 2006-06-10 2007-12-13 United Technologies Corporation Stator assembly for a rotary machine
EP2261467A2 (fr) * 2009-06-05 2010-12-15 United Technologies Corporation Ensemble d'enveloppe de diamètre interne pour structure d'aube d'entrée variable dans une turbine à gaz
US20160123188A1 (en) * 2014-11-03 2016-05-05 United Technologies Corporation Stator shroud systems
US20160363133A1 (en) * 2013-07-30 2016-12-15 Snecma Device for guiding variable pitch diffuser vanes of a turbine engine

Family Cites Families (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3829233A (en) 1973-06-27 1974-08-13 Westinghouse Electric Corp Turbine diaphragm seal structure
US4792277A (en) * 1987-07-08 1988-12-20 United Technologies Corporation Split shroud compressor
US5062767A (en) * 1990-04-27 1991-11-05 The United States Of America As Represented By The Secretary Of The Air Force Segmented composite inner shrouds
FR2685033B1 (fr) 1991-12-11 1994-02-11 Snecma Stator dirigeant l'entree de l'air a l'interieur d'une turbomachine et procede de montage d'une aube de ce stator.
US5487642A (en) * 1994-03-18 1996-01-30 Solar Turbines Incorporated Turbine nozzle positioning system
US5421703A (en) * 1994-05-25 1995-06-06 General Electric Company Positively retained vane bushing for an axial flow compressor
DE10161292A1 (de) * 2001-12-13 2003-06-26 Rolls Royce Deutschland Lagerring zur Lagerung von Schaufelfüßen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine
DE10351202A1 (de) 2003-11-03 2005-06-02 Mtu Aero Engines Gmbh Vorrichtung zum Verstellen von Leitschaufeln
FR2874977A1 (fr) 2004-09-07 2006-03-10 Snecma Moteurs Sa Douille de support pivotant pour pivot d'aube a calage variable de turbomachine
FR2875270B1 (fr) 2004-09-10 2006-12-01 Snecma Moteurs Sa Retenue des clavettes de centrage des anneaux sous aubes de stator a calage variable d'un moteur a turbine a gaz
US7690889B2 (en) 2005-07-20 2010-04-06 United Technologies Corporation Inner diameter variable vane actuation mechanism
US7753647B2 (en) 2005-07-20 2010-07-13 United Technologies Corporation Lightweight cast inner diameter vane shroud for variable stator vanes
US7510369B2 (en) * 2005-09-02 2009-03-31 United Technologies Corporation Sacrificial inner shroud liners for gas turbine engines
DE102005042747A1 (de) 2005-09-05 2007-03-08 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelkranz für eine Gasturbine
EP1788199A3 (fr) 2005-11-22 2011-02-23 General Electric Company Assemblage d'aubes statoriques variables avec une couche résistant à l'usure
JP4918263B2 (ja) 2006-01-27 2012-04-18 三菱重工業株式会社 軸流圧縮機の静翼環
US7713022B2 (en) 2007-03-06 2010-05-11 United Technologies Operations Small radial profile shroud for variable vane structure in a gas turbine engine
DE102007015669A1 (de) 2007-03-31 2008-10-02 Mtu Aero Engines Gmbh Turbomaschine
US8500394B2 (en) 2008-02-20 2013-08-06 United Technologies Corporation Single channel inner diameter shroud with lightweight inner core
US9309778B2 (en) 2010-12-30 2016-04-12 Rolls-Royce North American Technologies, Inc. Variable vane for gas turbine engine
WO2013110792A1 (fr) * 2012-01-26 2013-08-01 Alstom Technology Ltd Élément formant stator pourvu d'une bague intérieure segmentée pour une turbomachine
FR2988787B1 (fr) 2012-04-03 2016-01-22 Snecma Redresseur a calage variable pour compresseur de turbomachine comprenant deux anneaux internes
FR2994453B1 (fr) 2012-08-08 2014-09-05 Snecma Ensemble a faible usure pour couronne aubagee de stator de turbomachine d'aeronef
US9140133B2 (en) 2012-08-14 2015-09-22 United Technologies Corporation Threaded full ring inner air-seal
CA2881861C (fr) 2012-09-20 2019-08-20 United Technologies Corporation Module de systeme d'engrenage d'entrainement de soufflante et mecanisme d'accouplement d'aube de guidage d'entree
US9327368B2 (en) 2012-09-27 2016-05-03 United Technologies Corporation Full ring inner air-seal with locking nut
EP2716874B1 (fr) 2012-10-08 2017-12-27 MTU Aero Engines AG Stator, procédé de montage et turbomachine
WO2014143445A2 (fr) 2013-02-10 2014-09-18 United Technologies Corporation Enveloppe de recouvrement d'aube fixe à incidence variable
DE102013203870B4 (de) 2013-03-07 2015-06-03 MTU Aero Engines AG Verdrehsicherung für Turbomaschinen
EP2787180A1 (fr) 2013-04-04 2014-10-08 MTU Aero Engines GmbH Agencement d'aubes directrices pour une turbomachine
EP2806107B1 (fr) 2013-05-22 2017-08-09 MTU Aero Engines AG Bague intérieure séparée
WO2015031058A1 (fr) 2013-08-28 2015-03-05 United Technologies Corporation Douille d'aube variable
US9533485B2 (en) 2014-03-28 2017-01-03 Pratt & Whitney Canada Corp. Compressor variable vane assembly
EP3056683B1 (fr) * 2015-02-16 2018-05-23 MTU Aero Engines GmbH Bague intérieure séparée axialement pour une turbomachine et stator
EP3056684B1 (fr) * 2015-02-16 2018-05-16 MTU Aero Engines GmbH Bague intérieure séparée axialement pour une turbomachine, un stator et groupe motopropulseur
DE102017209682A1 (de) * 2017-06-08 2018-12-13 MTU Aero Engines AG Axial geteilter Turbomaschinen-Innenring

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070286719A1 (en) * 2006-06-10 2007-12-13 United Technologies Corporation Stator assembly for a rotary machine
EP2261467A2 (fr) * 2009-06-05 2010-12-15 United Technologies Corporation Ensemble d'enveloppe de diamètre interne pour structure d'aube d'entrée variable dans une turbine à gaz
US20160363133A1 (en) * 2013-07-30 2016-12-15 Snecma Device for guiding variable pitch diffuser vanes of a turbine engine
US20160123188A1 (en) * 2014-11-03 2016-05-05 United Technologies Corporation Stator shroud systems

Also Published As

Publication number Publication date
US10858959B2 (en) 2020-12-08
DE102017209682A1 (de) 2018-12-13
US20180355761A1 (en) 2018-12-13

Similar Documents

Publication Publication Date Title
EP3412874A1 (fr) Bague interne d'une turbomachine divisée axiale
EP2399004B1 (fr) Section de rotor pour un rotor d'une turbomachine, aube rotorique pour une turbomachine et élément de blocage
DE102006004613B4 (de) Gasturbine, die eine Abdichtstruktur aufweist
EP3056683B1 (fr) Bague intérieure séparée axialement pour une turbomachine et stator
DE102010060284B4 (de) Sicherungs-Abstandshalteranordnung für ein Schaufelblattbefestigungssystem zur Einführung in Umfangsrichtung und Rotoranordnung mit derartiger Sicherungs-Abstandshalteranordnung
EP2806107B1 (fr) Bague intérieure séparée
EP1148209B1 (fr) Configuration de joint inter-étages
CH698039A2 (de) Voll eingekapselter Haltestift für eine Turbinendüse.
DE112013001838B4 (de) Leitschaufelsegment und dieses enthaltende Axialströmungsfluidmaschine
DE102009044089A1 (de) Verfahren und Vorrichtung zur Anpassung der thermisch wirksamen Masse und Steifigkeit von verschraubten Teilringen
WO2016116105A1 (fr) Agencement de palier et turbocompresseur à gaz d'échappement
EP1135578B1 (fr) Dispositif d'appui pour pales de groupes moteurs
DE102012008723A1 (de) Leitrad für Turbomaschinen und Herstellungsverfahren
EP2960530A1 (fr) Procédé de montage pour une machine électrique dotée d'au moins deux segments de machine
EP3287608B1 (fr) Bague intérieure d'une couronne d'aubes directrices d'une turbomachine
EP3181918B1 (fr) Dispositif de fixation
DE102016201766A1 (de) Leitschaufelsystem für eine Strömungsmaschine
WO2010031693A1 (fr) Rotor axial de turbomachine à système de verrouillage d'aube et son procédé de fabrication
EP3176386A1 (fr) Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés
EP2716874A1 (fr) Stator, procédé de montage et turbomachine
EP3695100B1 (fr) Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité
EP2816198B1 (fr) Ensemble d'aube directrice, aube directrice et procédé de montage d'une aube directrice
DE102020209471A1 (de) Verdrehgesicherter Spannverbund einer Strömungsmaschine
EP2886799A1 (fr) Couronne d'aubes de turbomachine et procédé de montage des aubes d'une couronne d'aubes de turbomachine
EP2725202A1 (fr) Agencement de support d'étanchéité d'anneau intérieur pour assemblage des aubes statoriques variables d'une turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20190612

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20200214

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20210501