EP2947281A1 - Système de boîtier de turbine à gaz - Google Patents

Système de boîtier de turbine à gaz Download PDF

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Publication number
EP2947281A1
EP2947281A1 EP15164583.5A EP15164583A EP2947281A1 EP 2947281 A1 EP2947281 A1 EP 2947281A1 EP 15164583 A EP15164583 A EP 15164583A EP 2947281 A1 EP2947281 A1 EP 2947281A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
turbine housing
ring
radial flange
housing element
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.)
Granted
Application number
EP15164583.5A
Other languages
German (de)
English (en)
Other versions
EP2947281B1 (fr
Inventor
Manfred Feldmann
Franz-Josef Ertl
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 EP2947281A1 publication Critical patent/EP2947281A1/fr
Application granted granted Critical
Publication of EP2947281B1 publication Critical patent/EP2947281B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F05D2240/11—Shroud seal segments

Definitions

  • the present invention relates to a gas turbine housing assembly having a gas turbine housing member and a nozzle, a gas turbine, in particular an aeroengine gas turbine, with such a gas turbine housing assembly and a method for securing the guide ring in the flow direction axially to the gas turbine housing element of such a gas turbine housing assembly.
  • a gas turbine with a gas turbine housing element and a guide ring with an outer ring is known.
  • the outer ring is secured by Genzouseelementfeste spokes on the housing element, which engage radially in recesses in the outer ring.
  • a shroud ring which is radially opposite a wheel lattice adjacent the playpen, is attached directly to the outer ring and engages with axial projections in recesses in the outer ring axially.
  • the gas turbine housing element, the guide ring and the shroud have different thermal expansions. Due to the direct axial support between the outer and outer ring with the associated high normal forces cause the thermally induced relative radial movements wear high.
  • An object of one embodiment of the present invention is to provide an improved gas turbine.
  • a gas turbine housing assembly having the features of claim 1.
  • the claims 14, 15 provide a gas turbine, in particular an aircraft engine gas turbine, with such a gas turbine housing assembly or a method for securing the guide ring in the flow direction axially to the gas turbine housing element of such a gas turbine housing arrangement under protection.
  • Advantageous embodiments of the invention are the subject of the dependent claims.
  • a gas turbine housing assembly includes a housing having one or more gas turbine housing members, a nozzle ring having in one embodiment a plurality of guide vanes defining vanes and an outer ring, and a shroud ring integral with the nozzle ring and guide vanes thereof. in particular in the flow direction below, radially adjacent to adjacent playpens with a plurality of blades.
  • the guide ring in particular its guide grid and outer ring, integrally formed.
  • the shroud is segmented in one embodiment or has a plurality of circumferentially adjacent segments.
  • the shroud has a gland radially outwardly surrounding seal, in particular a honeycomb seal on.
  • the shroud is secured in one embodiment on the gas turbine housing element axially in and / or against the flow direction and / or radially and / or circumferentially, in particular fixed. In particular, it can be fastened to a, preferably downstream, axial region directly or without intermediate element or indirectly or via one or more intermediate elements, connected to the gas turbine housing element, in particular detachably or stationarily attached thereto.
  • the gas turbine housing assembly comprises an intermediate ring with a downstream end face a housing element fixed upstream stop and engages with an upstream end face of a radial flange of the intermediate ring outer ring fixed downstream stop to axially secure the guide ring in the flow direction of the gas turbine housing element, or which axially secures the guide ring in the flow direction to the gas turbine housing element.
  • a gap between the radial flange and the shroud is formed in an installed position to allow movement of the radial flange radially outward or which allows a movement of the radial flange radially outward.
  • an axial movement of the radial flange and / or a movement of the radial flange in the circumferential direction and / or a tilting movement of the radial flange are allowed or be.
  • a movement of the radial flange radially outward may include, in particular, a widening of the radial flange in the radial direction.
  • An upstream end face or an upstream stop in the sense of the present invention is an area whose outward normal is opposite to the throughflow direction of an exhaust gas flowing through the gas turbine or encloses with it an angle greater than 90 °, in particular at least substantially equal to 180 °, i. in other words facing an inlet of the gas turbine or facing away from the playpens.
  • a downstream end face or an upstream stop means a surface whose outward normal is in the same direction as the flow direction or encloses an angle of less than 90 °, in particular at least substantially equal to 0 °, ie. In other words, it faces an outlet of the gas turbine or the playpens.
  • the outer ring of the guide ring which is acted upon by the flow axially in the flow direction, axially supported in the flow direction with its downstream stop on the upstream end face of the radial flange of the intermediate ring, which in turn with its downstream end face axially in the flow direction at the upstream housing element fixed stop supported.
  • An installation position is, in particular, a non-operating state of the stationary, uncontrolled gas turbine, whereby this particular normal or ambient temperature, in particular at least 10 ° C and / or at most 50 ° C, having.
  • this particular normal or ambient temperature in particular at least 10 ° C and / or at most 50 ° C, having.
  • the intermediate ring in the installed position substantially the same temperature everywhere, in particular the normal or ambient temperature, preferably also further the guide ring, the turbine housing member and / or the shroud.
  • an operating position is in particular an operating state of the working person, i. fired and rotating gas turbine, in particular a design state, preferably in a take-off, landing or cruising operating point, wherein in one embodiment the guide ring, the turbine housing element, the shroud and / or the ferrule ring a temperature of at least 100 ° C, in particular at least 150 ° C has.
  • the intermediate ring may have a temperature gradient, in particular between its downstream end face associated with the housing and its upstream, the outer ring of the guide ring associated end face.
  • the temperature of the gas turbine casing element - and thus the downstream end face of the intermediate ring - can be significantly higher, in particular at least 50 ° C, than the temperature of the outer ring of the guide ring - and so that the upstream end face of the intermediate ring.
  • the gap between the radial flange and the shroud is in one embodiment, a radial and / or axial gap, which allows a thermally induced movement of the radial flange out of the mounting position radially outward, without the shroud prevents this.
  • this gap or axial and / or radial, in particular shortest, distance between the radial flange and the shroud is at least 0.5 mm, in particular at least 1 mm, in particular at least 5 mm. Additionally or alternatively, in one embodiment, this gap is at most 50 mm, in particular at most 25 mm, in particular at most 10 mm.
  • the radial flange (at the latest) in an operating position on the shroud and supported in a development axially and / or radially on this form-fitting and / or frictional engagement.
  • the initial or in the installed position (still) existing gap between the intermediate and shroud sealed operationally and thus reduces unwanted leakage, in particular be prevented.
  • the shroud can touch the radial flange already in the installed position, preferably from radially outside.
  • a contact surface of the radial flange for contacting the shroud be designed such that it is in the operating position, at least substantially, parallel to a contact surface of the shroud for contacting the radial flange. In other words, an angle by which the radial flange tilts in the radial expansion, held in the installed position.
  • an axial flange of the intermediate ring, on which its radial flange is arranged has a kink for this purpose.
  • the radial flange is (at the latest) in the operating position, in particular flat, on a support wall of the shroud ring, which is arranged at its the outside of the playpen radially surrounding seal.
  • the radial flange forms an outer wall of a flow channel in which the playpens is arranged.
  • the radial flange is acted upon and heated by the hot exhaust gas flowing through the flow duct and the playpens, which causes or intensifies the above-explained thermally induced radial expansion.
  • the intermediate ring on an axial flange, which is arranged between its downstream and its upstream end face, and on which the radial flange of the intermediate ring is arranged.
  • This can, as explained above, have a kink in a meridian section.
  • the axial flange is or is elastically deformed in the operating position.
  • the axial flange can be designed to be correspondingly elastic, in particular by appropriate choice of material and / or geometry. As a result of this elastic deformation, as explained above, the radial flange can expand radially during operation due to thermal conditions.
  • downstream end face can be arranged on a further radial flange of the intermediate ring, which is tiltably coupled to the gas turbine housing element.
  • this is to be understood in particular as meaning that the further radial flange of the intermediate ring is rotatably supported in a meridian section on the stop element fixed to the housing element.
  • the further radial flange of the intermediate ring on its the downstream end face of the intermediate ring or the housing element fixed upstream stop opposite side have a rounding and / or an axial clearance to the gas turbine housing element, which in the meridian section a rotation of the cross section of the housing element fixed stop supporting further radial flange allows or permitted.
  • a cross section of the intermediate ring rotates with a radial widening of its radial flange.
  • the outer ring is attached to the gas turbine housing element by one or more radial spokes, in particular with radial play in the installed position.
  • spokes in particular with radial play in the installed position.
  • This is understood in particular a positive connection between radially inwardly projecting element fixed to the housing projections and radially outwardly projecting outer ring fixed projections, which secure the outer ring at least in the circumferential direction of the gas turbine housing element, in particular set.
  • the guide ring is a guide ring of an internal stage or in the gas turbine housing element at least one further, downstream Leitkranz is arranged
  • the housing element fixed upstream stop is arranged on a retaining ring in one embodiment
  • the assembly can be simplified, in particular by the intermediate ring, in particular its further radial flange, inserted into a corresponding groove in the gas turbine housing element and then secured axially in the flow direction by the retaining ring.
  • the housing element-fixed upstream stop is arranged in a circumferential groove of a bayonet catch.
  • the assembly can also be simplified, in particular by the intermediate ring, in particular its further radial flange, is rotated in the circumferential groove of the bayonet verhakung in the circumferential direction and engages behind the defined by this circumferential groove housing element fixed stop.
  • the housing element fixed upstream stop may alternatively be arranged on a releasably connected to the gas turbine housing element, in particular positive and / or frictional, or non-detachable, in particular cohesively, further gas turbine housing element, ie in particular the gas turbine housing part part of a turbine intermediate housing and the other gas turbine housing element Part of a housing of a (low pressure) turbine.
  • the assembly can also be simplified, in particular by axially securing the intermediate ring, in particular its further radial flange, between the gas turbine casing element and the further gas turbine casing element.
  • the circlip explained above is supported in a development, at least in the operating position, on the shroud radially. As a result, the shroud can take on a further functionality.
  • the jacket ring in particular from radially outside, is supported radially on the intermediate ring. This allows the intermediate ring to take on a further functionality.
  • a radial widening of the intermediate ring in particular a tilting of its further radial flange with corresponding tilting of a cross section of the axial flange, can bring about an advantageous radial adjustment of the jacket ring supported on it: namely, the intermediate ring, in particular its radial flange, widens radially on the outside, as well as the radially outwardly resting on it shroud is guided radially outward.
  • a radial gap between the shroud, in particular a jacket-ring-tight seal, and the radially opposite playpens be optimized.
  • the shroud ring so on the intermediate ring radially from that supports a radial distance between the shroud and the playpen or its outer periphery, in the installation and operating position, at least substantially, remains the same.
  • the shroud is supported with a, in particular upstream, axial region radially from the outside of the intermediate ring and is preferably connected to a further, in particular downstream, axial region with the gas turbine housing element, in particular directly or without intermediate element, or indirectly or over one or more intermediate elements with these releasably or permanently connected.
  • the intermediate ring can lead or expand the one, in particular upstream, axial region of the sheath ring radially outwards relative to the further, in particular downstream, housing-fixed axial region of the sheath ring, and thus to form a radial gap Optimize playpen automatically.
  • the one, in particular upstream, axial region of the shroud ring which is supported radially from the outside radially on the intermediate ring, preferably also a sealing of the shroud radially outwardly surrounding seal, radially outward play or Free space, in particular a radial gap to the gas turbine housing element or an associated element, which faces it radially outward.
  • the shroud is supported with a, in particular upstream, radially outwardly, in particular elastically, movable axial region radially from the outside of the intermediate ring and is preferably connected to a further, in particular downstream, axial region with the gas turbine housing element.
  • the supports in particular upstream.
  • Axial Scheme of the shroud from radially outside on the axial flange of the intermediate ring.
  • a gas passage from one of the Leitkranz facing surface of the intermediate ring to one of these opposite surface of the intermediate ring is provided or formed, in particular by a leakage between the downstream end face and the upstream stop or corresponding passages on the axial and / or the other radial flange.
  • the intermediate ring in the installed position is arranged on the guide ring and the gas turbine housing element such that a gap is formed between the radial flange of the guide ring and the cover ring, in order to move the radial flange to allow radially outward.
  • Fig. 1 shows a gas turbine housing assembly according to an embodiment of the present invention in a meridian section, ie a section showing a rotational axis of the gas turbine (horizontally in Fig. 1 ), in an installation position.
  • the gas turbine housing assembly has an in Fig. 1 only partially shown gas turbine housing element 10, a Leitkranz with an outer ring 20 and a shroud 30, which is the Leitkranz in the flow direction (from left to right in Fig. 1 ) Next adjacent playpen with an outer shroud 40 radially (from bottom to top in Fig. 1 ) is opposite.
  • the shroud 30 has a the honeycomb radially outwardly surrounding honeycomb seal 31.
  • the gas turbine housing assembly further comprises an intermediate ring 50 which engages with a downstream end face 51 a housing element fixed upstream stop 61 and an upstream end surface 52 of a radial flange 53 of the intermediate ring 50, an outer ring fixed downstream stop 22 to the guide ring in the flow direction axially (from left to right ) to the gas turbine housing element, wherein in the in Fig. 1 shown mounting position a gap s between the radial flange 53 and the shroud 30 is formed to a movement of the radial flange 53 radially outward (upward in Fig. 1 ).
  • Fig. 2 shows the gas turbine housing assembly of Fig. 1 in an operating position: after the radial flange 53 has widened radially as a result of operational heating, it lies in the operating position flat against a support wall 32 of the shroud 30, which is arranged on the radially outer sealing ring 31 surrounding the playpen, and relies on this Support wall 32 from.
  • a support wall 32 of the shroud 30 which is arranged on the radially outer sealing ring 31 surrounding the playpen, and relies on this Support wall 32 from.
  • the radial flange 53 forms an outer wall of a flow channel 70, in which the playpens is arranged. As a result, during operation, the radial flange is acted upon by the hot exhaust gas flowing through the flow channel 70 and the playpens.
  • the intermediate ring 50 has an axial flange 55, which is arranged between its downstream and upstream end face 51, 52, and on which the radial flange 53 of the intermediate ring is arranged. This points in the meridian section of the Fig. 1 a bend to hold the angle by which the radial flange 53 tilts in the radial expansion.
  • the downstream end face 51 is arranged on a further radial flange 54 of the intermediate ring 50, which is tiltably hinged to the gas turbine housing element 10.
  • the further radial flange 54 of the intermediate ring rotates in the meridian section of Fig. 1 . 2 around a contact point on the housing element fixed stop 61 on which it is rotatably supported for this purpose.
  • the further radial flange 54 of the intermediate ring on its the downstream end face 51 of the intermediate ring or the housing element fixed upstream stop 61 opposite side (ie left in Fig. 1 ) a rounding and / or an axial clearance to the gas turbine housing element 10, which allows in the meridian section a rotation of the cross section of the housing element fixed to the stop 61 supporting further radial flange 54 or allowed.
  • the outer ring 20 is fixed to the gas turbine casing member 10 by a plurality of radial spokes 11,21 with radial clearance between the radially inwardly projecting housing element fixed projections 11 and the radially outwardly projecting outer ring fixed projections 21 in the installation position, the outer ring 20 in the circumferential direction of the gas turbine housing element 10 secure.
  • the Leitkranz is a Leitkranz an internal stage. Therefore, the housing member fixed upstream stop 61 is disposed on a snap ring 60 which is frictionally secured in the gas turbine housing member 10.
  • the housing element fixed upstream stop is instead arranged in a circumferential groove of a bayonet Verhakung.
  • the circlip 60 is integrally formed with the gas turbine housing member 10, with the further radial flange 54 and the circlip 60 then corresponding gaps in the circumferential direction (perpendicular to the plane of the Fig. 1 ), so that the further radial flange can initially be inserted axially against the flow direction and then rotated in the circumferential direction, so that its end face 51 then engages behind the stop 61.
  • the explained locking ring 60 is supported in the operating position (see. Fig. 2 ) radially on the shroud 30.
  • the shroud 30 in turn is supported both in the installed and the operating position with an upstream (left in Fig. 1 . 2 ) Axial Scheme of radially outside (from above in Fig. 1 ) on the intermediate ring 50 radially.
  • opposite, downstream axial region is connected directly or indirectly to the gas turbine housing element.
  • Fig. 1 . 2 shows the intermediate ring 50 at a radial expansion of its radial flange 53 due to the support of the upstream Axial Society of the shroud 30 this with radially outward.
  • a radial gap can be kept constant, at least substantially, with respect to the playpen 40, which thermally expands radially outwards, or to the fins on its outer cover tape.
  • FIG. 3 shows in Fig. 1 corresponding representation of a gas turbine housing assembly of a gas turbine according to a further embodiment of the present invention.
  • Corresponding features are identified by identical reference numerals, so that reference is made to the above description and will be discussed below only differences.
  • the guide ring is a last or downstream guide ring of the housing element and arranged at a module interface between a turbine intermediate housing and a low-pressure turbine.
  • the housing element-fixed upstream stop 61 ' is arranged on a further gas turbine housing element 60' connected to the gas turbine housing element 10, which is part of a turbine intermediate housing, which is part of a housing of the low-pressure turbine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP15164583.5A 2014-05-14 2015-04-22 Système de boîtier de turbine à gaz Not-in-force EP2947281B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102014209057.1A DE102014209057A1 (de) 2014-05-14 2014-05-14 Gasturbinengehäuseanordnung

Publications (2)

Publication Number Publication Date
EP2947281A1 true EP2947281A1 (fr) 2015-11-25
EP2947281B1 EP2947281B1 (fr) 2017-06-14

Family

ID=53008311

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15164583.5A Not-in-force EP2947281B1 (fr) 2014-05-14 2015-04-22 Système de boîtier de turbine à gaz

Country Status (4)

Country Link
US (1) US9816386B2 (fr)
EP (1) EP2947281B1 (fr)
DE (1) DE102014209057A1 (fr)
ES (1) ES2630187T3 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109252902A (zh) * 2018-09-14 2019-01-22 中国航发湖南动力机械研究所 轴向限位结构和涡轮发动机
EP3000990B1 (fr) 2014-09-26 2019-05-29 Rolls-Royce plc Dispositif de retenue de virole d'une turbine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018210601A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Segmentring zur montage in einer strömungsmaschine
US12529322B1 (en) 2024-11-08 2026-01-20 Pratt & Whitney Canada Corp. Gas turbine engine stator vane stage

Citations (6)

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Publication number Priority date Publication date Assignee Title
FR2646221A1 (fr) * 1989-04-19 1990-10-26 Snecma Joint d'etancheite, dispositif le comportant et application a une turbomachine
US5839878A (en) * 1996-09-30 1998-11-24 United Technologies Corporation Gas turbine stator vane
EP0937864A2 (fr) * 1998-02-20 1999-08-25 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Configuration des aubes de guidage pour une turbomachine axiale
US20070122270A1 (en) 2003-12-19 2007-05-31 Gerhard Brueckner Turbomachine, especially a gas turbine
FR2957115A1 (fr) * 2010-03-05 2011-09-09 Snecma Etage de turbine dans une turbomachine
GB2485016A (en) * 2010-10-29 2012-05-02 Gen Electric Turbine component with resilient mounting

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DE19756734A1 (de) * 1997-12-19 1999-06-24 Bmw Rolls Royce Gmbh Passives Spalthaltungssystem einer Gasturbine
DE10312956B4 (de) * 2003-03-22 2011-08-11 MTU Aero Engines GmbH, 80995 Anordnung für das axiale und radiale Festlegen einer Leitschaufelbaugruppe in dem Gehäuse eines Turbinentriebwerkes
FR2913050B1 (fr) * 2007-02-28 2011-06-17 Snecma Turbine haute-pression d'une turbomachine
US8147192B2 (en) * 2008-09-19 2012-04-03 General Electric Company Dual stage turbine shroud
FR2961554B1 (fr) * 2010-06-18 2012-07-20 Snecma Secteur angulaire de redresseur pour compresseur de turbomachine, redresseur de turbomachine et turbomachine comprenant un tel secteur
FR2989724B1 (fr) * 2012-04-20 2015-12-25 Snecma Etage de turbine pour une turbomachine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2646221A1 (fr) * 1989-04-19 1990-10-26 Snecma Joint d'etancheite, dispositif le comportant et application a une turbomachine
US5839878A (en) * 1996-09-30 1998-11-24 United Technologies Corporation Gas turbine stator vane
EP0937864A2 (fr) * 1998-02-20 1999-08-25 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Configuration des aubes de guidage pour une turbomachine axiale
US20070122270A1 (en) 2003-12-19 2007-05-31 Gerhard Brueckner Turbomachine, especially a gas turbine
FR2957115A1 (fr) * 2010-03-05 2011-09-09 Snecma Etage de turbine dans une turbomachine
GB2485016A (en) * 2010-10-29 2012-05-02 Gen Electric Turbine component with resilient mounting

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3000990B1 (fr) 2014-09-26 2019-05-29 Rolls-Royce plc Dispositif de retenue de virole d'une turbine
CN109252902A (zh) * 2018-09-14 2019-01-22 中国航发湖南动力机械研究所 轴向限位结构和涡轮发动机
CN109252902B (zh) * 2018-09-14 2021-09-07 中国航发湖南动力机械研究所 轴向限位结构和涡轮发动机

Also Published As

Publication number Publication date
DE102014209057A1 (de) 2015-11-19
ES2630187T3 (es) 2017-08-18
US9816386B2 (en) 2017-11-14
US20150330237A1 (en) 2015-11-19
EP2947281B1 (fr) 2017-06-14

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