EP0531202B1 - Shrouded turbine guide vane - Google Patents

Shrouded turbine guide vane Download PDF

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Publication number
EP0531202B1
EP0531202B1 EP92402384A EP92402384A EP0531202B1 EP 0531202 B1 EP0531202 B1 EP 0531202B1 EP 92402384 A EP92402384 A EP 92402384A EP 92402384 A EP92402384 A EP 92402384A EP 0531202 B1 EP0531202 B1 EP 0531202B1
Authority
EP
European Patent Office
Prior art keywords
platform
casing
outer platform
turbine guide
turbine
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.)
Expired - Lifetime
Application number
EP92402384A
Other languages
German (de)
French (fr)
Other versions
EP0531202A1 (en
Inventor
Carmen Miraucourt
Philippe Thieux
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0531202A1 publication Critical patent/EP0531202A1/en
Application granted granted Critical
Publication of EP0531202B1 publication Critical patent/EP0531202B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer

Definitions

  • the present invention relates to a turbine distributor comprising a plurality of fixed vanes regularly distributed radially in an annular flow path for circulation of hot gases delimited by an internal platform and by an external platform, said distributor being disposed inside.
  • a casing and each fixed vane having on the one hand, an outer casing of aerodynamic shape which delimits an internal cavity, and on the other hand, a cooling circuit formed by an attached part disposed in said internal cavity, said external casing being fixed by one of its ends to the external platform and by the other end to the internal platform.
  • turbomachines there is provided, in particular at the outlet of the combustion chamber, a stage of fixed blades, constituting the distributor of the turbine, whose role is to deflect the jet of hot gases coming from the combustion chamber and intended driving the first stage of the turbine's moving vanes.
  • the gases from the combustion chamber being very hot, the vanes of the distributor are subjected to significant thermal stresses; also, it is known to cool them with a cooling fluid, in particular with cold air taken upstream from the combustion chamber. Due to the deviation of the jet of hot gases and possible differences in the pressures of the hot gases between the upstream and downstream of the distributor, the latter is also subjected to high mechanical stresses.
  • the cooling circuit being at a temperature lower than the temperature of the envelope, the temperature differences can cause additional mechanical stresses.
  • Document GB 2 210 415 shows a distributor vane comprising an outer casing and a cooling circuit formed by a tubular jacket, one end of which is fixed to the external platform and the other end of which is free.
  • the outer envelope of the blade must withstand both the high temperatures and the mechanical stresses.
  • the French document FR 2 465 068 also relates to a distributor blade, the outer envelope of which also supports high temperatures and mechanical stresses.
  • the cooling circuit consists of a tubular part fixed by one end to the external casing and the other end of which can slide with play along a sleeve secured to the external platform depending on the respective expansions of the 'outer casing and tubular part.
  • the object of the present invention is to provide a turbine distributor in which the outer envelope of the blades only supports high temperatures and in which the mechanical stresses are supported by the coldest elements of the distributor, which makes it possible to increase the lifespan of the blades.
  • the insert of each blade is fixed by one of its ends to the internal platform and by the other end to the casing, and by the fact that the platform outer shape has a plurality of holes for the passage of the inserts and is separated from the housing by an annular space.
  • the external envelope and the external platform can expand freely in the radial direction.
  • the insert which is the coldest part of the blade, links the interior platform to the casing and supports all of the mechanical stresses.
  • the orifices of the external platform are dimensioned to allow at least partial evacuation of the cooling fluid circulating inside the blades towards the annular space surrounding said external platform.
  • the insert has at its end near the housing a sleeve fixed in a bore formed in the housing, said sleeve serving for the introduction of the coolant into the corresponding blade.
  • Said sleeve preferably crosses the corresponding orifice of the external platform.
  • the drawing shows, in axial section, a blade 1 of a distributor 2 of a turbomachine.
  • This distributor 2 comprises a plurality of vanes 1 spaced regularly in an annular vein 3 delimited by an external platform 4 and an internal platform 5 and in which flow, from upstream to downstream, the very hot gases from of the combustion chamber.
  • the distributor 2 is arranged inside a casing 6.
  • the blade 1 consists of an envelope 7, having a section of aerodynamic profile, which is located in the flow of hot gases and which delimits an internal cavity 8.
  • This envelope is linked to the external 4 and internal 5 platforms by brazing, respectively in 9 and 10.
  • the internal platform 5 comprises, at its internal central part, a recess 11 intended to receive the base 12 of an insert 13 forming the cooling circuit of the blade 1.
  • the insert 13 is brazed at its base 12 in the recess 11, and its upper part 14 passes through the outer platform 4 and is linked to the casing 6.
  • the upper part 14 of the insert is present under the shape of a sleeve fixed in a bore 16 provided correspondingly in the casing 6.
  • the sleeve 14 passes through an orifice 17 formed in the external platform 4.
  • the insert 13 has a plurality of radial partitions 13a provided with coolant passage orifices and forming between them and the casing 7 circulation channels for the coolant.
  • the radial partitions 13a are connected to the sleeve 14 by a plate 18 substantially parallel to the external platform 4.
  • the portion 4a of the external platform 4 which surrounds the orifice 17 is interposed between the plate 18 and the casing 6 so as to provide a first annular space 19 between the plate 18 and said portion 4a, as well as a second space annular 20 between said portion 4a and the casing 6.
  • the walls facing the sleeve 14 and the portion 4a have axial grooves 21 allowing the passage of at least part of the cooling fluid, having circulated in the 'blade 1, from the annular space 18 towards the annular space 19 surrounding the external platform 4.
  • This part of cooling fluid is reintroduced into the vein 3 upstream and downstream of the external platform 4.
  • a seal can be placed downstream of the external platform 4 in a groove machined in the turbine ring 22. In this case, all the coolant escaping through the grooves 21 is reintroduced into the vein 3 upstream of the dish outdoor e-form 4.
  • the cooling air as represented by the arrows F, is introduced in a centripetal manner into the insert 13, then it cools the internal wall of the envelope 7. It is then reintroduced into the vein 3 after having circulated between the external platform 4 and the casing 6.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

La présente invention concerne un distributeur de turbine comportant une pluralité d'aubes fixes régulièrement réparties radialement dans une veine annulaire de circulation de gaz chauds délimitée par une plate-forme intérieure et par une plate-forme extérieure, ledit distributeur étant disposé à l'intérieur d'un carter et chaque aube fixe présentant d'une part, une enveloppe externe de forme aérodynamique qui délimite une cavité interne, et d'autre part, un circuit de refroidissement formé par une pièce rapportée disposée dans ladite cavité interne, ladite enveloppe externe étant fixée par l'une de ses extrémités à la plate-forme extérieure et par l'autre extrémité à la plate-forme intérieure.The present invention relates to a turbine distributor comprising a plurality of fixed vanes regularly distributed radially in an annular flow path for circulation of hot gases delimited by an internal platform and by an external platform, said distributor being disposed inside. a casing and each fixed vane having on the one hand, an outer casing of aerodynamic shape which delimits an internal cavity, and on the other hand, a cooling circuit formed by an attached part disposed in said internal cavity, said external casing being fixed by one of its ends to the external platform and by the other end to the internal platform.

Dans les turbomachines il est prévu, notamment à la sortie de la chambre de combustion, un étage d'aubes fixes, constituant le distributeur de la turbine, dont le rôle est de dévier le jet des gaz chauds issus de la chambre de combustion et destiné à entraîner le premier étage d'aubes mobiles de la turbine. Les gaz issus de la chambre de combustion étant très chauds, les aubes du distributeur sont soumises à des contraintes thermiques importantes ; aussi, il est connu de les refroidir avec un fluide de refroidissement, notamment avec de l'air froid prélevé en amont de la chambre de combustion. Du fait de la déviation du jet de gaz chauds et des différences éventuelles des pressions des gaz chauds entre l'amont et l'aval du distributeur, ce dernier est également soumis à des efforts mécaniques élevés. Enfin, le circuit de refroidissement étant à une température inférieure à la température de l'enveloppe, les différences de température peuvent entraîner des contraintes mécaniques supplémentaires.In turbomachines there is provided, in particular at the outlet of the combustion chamber, a stage of fixed blades, constituting the distributor of the turbine, whose role is to deflect the jet of hot gases coming from the combustion chamber and intended driving the first stage of the turbine's moving vanes. The gases from the combustion chamber being very hot, the vanes of the distributor are subjected to significant thermal stresses; also, it is known to cool them with a cooling fluid, in particular with cold air taken upstream from the combustion chamber. Due to the deviation of the jet of hot gases and possible differences in the pressures of the hot gases between the upstream and downstream of the distributor, the latter is also subjected to high mechanical stresses. Finally, the cooling circuit being at a temperature lower than the temperature of the envelope, the temperature differences can cause additional mechanical stresses.

Le document GB 2 210 415 montre une aube de distributeur comportant une enveloppe externe et un circuit de refroidissement formé par une chemise tubulaire dont l'une des extrémités est fixée à la plate-forme extérieure et dont l'autre extrémité est libre. Dans ce mode de construction, l'enveloppe externe de l'aube doit supporter à la fois les hautes températures et les contraintes mécaniques.Document GB 2 210 415 shows a distributor vane comprising an outer casing and a cooling circuit formed by a tubular jacket, one end of which is fixed to the external platform and the other end of which is free. In this method of construction, the outer envelope of the blade must withstand both the high temperatures and the mechanical stresses.

Le document français FR 2 465 068 concerne également une aube de distributeur dont l'enveloppe externe supporte aussi les hautes températures et les contraintes mécaniques. Le circuit de refroidissement est constitué d'une pièce tubulaire fixée par une extrémité à l'enveloppe externe et dont l'autre extrémité peut coulisser avec jeu le long d'un manchon solidaire de la plate-forme extérieure en fonction des dilatations respectives de l'enveloppe externe et de la pièce tubulaire.The French document FR 2 465 068 also relates to a distributor blade, the outer envelope of which also supports high temperatures and mechanical stresses. The cooling circuit consists of a tubular part fixed by one end to the external casing and the other end of which can slide with play along a sleeve secured to the external platform depending on the respective expansions of the 'outer casing and tubular part.

Il est connu que la résistance mécanique des matériaux diminue aux hautes températures.It is known that the mechanical resistance of materials decreases at high temperatures.

Le but de la présente invention est de proposer un distributeur de turbine dans lequel l'enveloppe extérieure des aubes supporte uniquement les hautes températures et dans lequel les contraintes mécaniques sont supportées par les éléments les plus froids du distributeur, ce qui permet d'augmenter la durée de vie des aubes.The object of the present invention is to provide a turbine distributor in which the outer envelope of the blades only supports high temperatures and in which the mechanical stresses are supported by the coldest elements of the distributor, which makes it possible to increase the lifespan of the blades.

Le but est atteint selon l'invention par le fait que la pièce rapportée de chaque aube est fixée par l'une de ses extrémités à la plate-forme intérieure et par l'autre extrémité au carter, et par le fait que la plate-forme extérieure présente une pluralité d'orifices pour le passage des pièces rapportées et est séparée du carter par un espace annulaire.The object is achieved according to the invention by the fact that the insert of each blade is fixed by one of its ends to the internal platform and by the other end to the casing, and by the fact that the platform outer shape has a plurality of holes for the passage of the inserts and is separated from the housing by an annular space.

Grâce à cette structure, l'enveloppe externe et la plate-forme extérieure peuvent se dilater librement dans le sens radial. La pièce rapportée, qui est la partie la plus froide de l'aube, lie la plate-forme intérieure au carter et supporte la totalité des contraintes mécaniques.Thanks to this structure, the external envelope and the external platform can expand freely in the radial direction. The insert, which is the coldest part of the blade, links the interior platform to the casing and supports all of the mechanical stresses.

De préférence les orifices de la plate-forme extérieure sont dimensionnés pour permettre une évacuation au moins partielle du fluide de refroidissement circulant à l'intérieur des aubes vers l'espace annulaire entourant ladite plate-forme extérieure.Preferably, the orifices of the external platform are dimensioned to allow at least partial evacuation of the cooling fluid circulating inside the blades towards the annular space surrounding said external platform.

La piéce rapportée comporte à son extrémité voisine du carter un manchon fixé dans un alésage ménagé dans le carter, ledit manchon servant à l'introduction du fluide de refroidissement dans l'aube correspondante.The insert has at its end near the housing a sleeve fixed in a bore formed in the housing, said sleeve serving for the introduction of the coolant into the corresponding blade.

Ledit manchon traverse de préférence l'orifice correspondant de la plate-forme extérieure.Said sleeve preferably crosses the corresponding orifice of the external platform.

Il est prévu sur l'une au moins des parois en vis-à-vis du manchon et de la plate-forme extérieure, des rainures axiales permettant l'évacuation du fluide de refroidissement.There are provided on at least one of the walls opposite the sleeve and the external platform, axial grooves allowing the evacuation of the cooling fluid.

D'autres avantages et caractéristiques de l'invention ressortiront à la lecture de la description suivante faite en référence au dessin annexé dans lequel :

  • la figure 1 unique représente une coupe axiale du distributeur de turbine de la présente invention, cette coupe étant réalisée au travers d'une aube.
Other advantages and characteristics of the invention will emerge on reading the following description made with reference to the appended drawing in which:
  • FIG. 1 single represents an axial section of the turbine distributor of the present invention, this section being made through a blade.

Le dessin montre, en coupe axiale, une aube 1 d'un distributeur 2 de turbomachine. Ce distributeur 2 comporte une pluralité d'aubes 1 espacées régulièrement dans une veine annulaire 3 délimitée par une plate-forme extérieure 4 et une plate-forme intérieure 5 et dans laquelle s'écoulent, d'amont en aval, les gaz très chauds issus de la chambre de combustion. Le distributeur 2 est disposé à l'intérieur d'un carter 6.The drawing shows, in axial section, a blade 1 of a distributor 2 of a turbomachine. This distributor 2 comprises a plurality of vanes 1 spaced regularly in an annular vein 3 delimited by an external platform 4 and an internal platform 5 and in which flow, from upstream to downstream, the very hot gases from of the combustion chamber. The distributor 2 is arranged inside a casing 6.

L'aube 1 est constituée d'une enveloppe 7, ayant une section de profil aérodynamique, qui est située dans l'écoulement des gaz chauds et qui délimite une cavité interne 8. Cette enveloppe est liée aux plate-formes extérieure 4 et intérieure 5 par brasage, respectivement en 9 et 10.The blade 1 consists of an envelope 7, having a section of aerodynamic profile, which is located in the flow of hot gases and which delimits an internal cavity 8. This envelope is linked to the external 4 and internal 5 platforms by brazing, respectively in 9 and 10.

La plate-forme intérieure 5 comporte à sa partie médiane interne, un évidement 11 destiné à recevoir la base 12 d'une pièce rapportée 13 formant le circuit de refroidissement de l'aube 1.The internal platform 5 comprises, at its internal central part, a recess 11 intended to receive the base 12 of an insert 13 forming the cooling circuit of the blade 1.

La pièce rapportée 13 est brasée à sa base 12 dans l'évidement 11, et sa partie supérieure 14 traverse la plate-forme extérieure 4 et, est liée au carter 6. De préférence la partie supérieure 14 de la pièce rapportée se présente sous la forme d'un manchon fixé dans un alésage 16 prévu en correspondance dans le carter 6. Le manchon 14 traverse un orifice 17 ménagé dans la plate-forme extérieure 4.The insert 13 is brazed at its base 12 in the recess 11, and its upper part 14 passes through the outer platform 4 and is linked to the casing 6. Preferably the upper part 14 of the insert is present under the shape of a sleeve fixed in a bore 16 provided correspondingly in the casing 6. The sleeve 14 passes through an orifice 17 formed in the external platform 4.

La pièce rapportée 13 présente une pluralité de cloisons radiales 13a munies d'orifices de passage de fluide de refroidissement et ménageant entre elles et l'enveloppe 7 des canaux de circulation pour le fluide de refroidissement.The insert 13 has a plurality of radial partitions 13a provided with coolant passage orifices and forming between them and the casing 7 circulation channels for the coolant.

Les cloisons radiales 13a sont reliées au manchon 14 par une plaque 18 sensiblement parallèle à la plate-forme extérieure 4.The radial partitions 13a are connected to the sleeve 14 by a plate 18 substantially parallel to the external platform 4.

La portion 4a de la plate-forme extérieure 4 qui entoure l'orifice 17 est interposée entre la plaque 18 et le carter 6 de manière à ménager un premier espace annulaire 19 entre la plaque 18 et ladite portion 4a, ainsi qu'un deuxième espace annulaire 20 entre ladite portion 4a et la carter 6. Les parois en vis-à-vis du manchon 14 et de la portion 4a présentent des rainures axiales 21 permettant le passage d'au moins une partie du fluide de refroidissement, ayant circulé dans l'aube 1, de l'espace annulaire 18 vers l'espace annulaire 19 entourant la plate-forme extérieure 4. Cette partie de fluide de refroidissement est réintroduite dans la veine 3 en amont et en aval de la plate-forme extérieure 4. En variante un joint d'étanchéité peut être placé en aval de la plate-forme extérieure 4 dans une rainure usinée dans l'anneau de turbine 22. Dans ce cas, tout le fluide de refroidissement s'échappant par les rainures 21 est réintroduit dans la veine 3 en amont de la plate-forme extérieure 4.The portion 4a of the external platform 4 which surrounds the orifice 17 is interposed between the plate 18 and the casing 6 so as to provide a first annular space 19 between the plate 18 and said portion 4a, as well as a second space annular 20 between said portion 4a and the casing 6. The walls facing the sleeve 14 and the portion 4a have axial grooves 21 allowing the passage of at least part of the cooling fluid, having circulated in the 'blade 1, from the annular space 18 towards the annular space 19 surrounding the external platform 4. This part of cooling fluid is reintroduced into the vein 3 upstream and downstream of the external platform 4. In variant a seal can be placed downstream of the external platform 4 in a groove machined in the turbine ring 22. In this case, all the coolant escaping through the grooves 21 is reintroduced into the vein 3 upstream of the dish outdoor e-form 4.

Différents aménagements permettant d'améliorer le refroidissement de l'enveloppe 7 sont possibles sur la paroi interne de cette dernière ou sur les cloisons 13a de la pièce rapportée : présence de picots, de copeaux brasés ou autres perturbateurs de types connus. On peut également prévoir des orifices d'évacuation sur l'enveloppe 7.Different arrangements for improving the cooling of the casing 7 are possible on the internal wall of the latter or on the partitions 13a of the insert: presence of pins, brazed chips or other disturbers of known types. Evacuation orifices can also be provided on the casing 7.

Ce qui est important dans l'invention c'est qu'il n'y ait pas de liaison entre la pièce rapportée 13 et l'enveloppe 7. On découple ainsi la fonction aérodynamique de guidage des gaz chauds réalisée par l'enveloppe 7, et la fonction mécanique qui est réalisée par la pièce rapportée 13.What is important in the invention is that there is no connection between the insert 13 and the envelope 7. The aerodynamic function of guiding the hot gases produced by the envelope 7 is thus decoupled, and the mechanical function which is performed by the insert 13.

L'air de refroidissement, comme représenté par les flèches F, est introduit de manière centripète dans la pièce rapportée 13, puis il vient refroidir la paroi interne de l'enveloppe 7. Il est ensuite réintroduit dans la veine 3 après avoir circulé entre la plate-forme extérieure 4 et le carter 6.The cooling air, as represented by the arrows F, is introduced in a centripetal manner into the insert 13, then it cools the internal wall of the envelope 7. It is then reintroduced into the vein 3 after having circulated between the external platform 4 and the casing 6.

Claims (5)

  1. A turbine guide comprising a number of fixed vanes (1) evenly spaced radially in an annular hot gas flow path (3) defined by an outer platform (4) and an inner platform (5), the guide being disposed in a casing (6), each fixed vane (1) having a streamlined outer envelope (7) defining an inner cavity (8) and a cooling circuit embodied by an insert member (13) disposed in the inner cavity (8), the outer envelope (7) being secured at one end to the outer platform (4) and at the other end to the inner platform (5),
    characterised in that the insert member (13) of each vane (1) is secured at one end (12) to the inner platform (5) and at the other end (14) to the casing (6) and the outer platform (4) is formed with a number of orifices (17) for receiving the insert members (13) and is separated from the casing (6) by an annular gap (20).
  2. A turbine guide according to claim 1,
    characterised in that the orifices (17) in the outer platform (4) are dimensioned for removal of at least some of the fluid coolant flowing in the vanes (1) to the annular gap (20) which extends around the outer platform (4).
  3. A turbine according to claim 1 or 2, characterised in that the insert member (13) has at its end near the casing (6) a neck (14) which is secured in a bore (16) in the casing (6) and through which the fluid coolant enters the corresponding vane (1).
  4. A turbine guide according to claim 3,
    characterised in that the neck (14) extends through the corresponding orifice (17) in the outer platform (4).
  5. A turbine guide according to claim 4,
    characterised in that at least one of the facing walls of the neck (14) and outer platform (4) is formed with axial grooves (21) for removal of the fluid coolant.
EP92402384A 1991-09-05 1992-09-02 Shrouded turbine guide vane Expired - Lifetime EP0531202B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9110966A FR2681095B1 (en) 1991-09-05 1991-09-05 CARENE TURBINE DISTRIBUTOR.
FR9110966 1991-09-05

Publications (2)

Publication Number Publication Date
EP0531202A1 EP0531202A1 (en) 1993-03-10
EP0531202B1 true EP0531202B1 (en) 1994-11-02

Family

ID=9416647

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Application Number Title Priority Date Filing Date
EP92402384A Expired - Lifetime EP0531202B1 (en) 1991-09-05 1992-09-02 Shrouded turbine guide vane

Country Status (4)

Country Link
US (1) US5217347A (en)
EP (1) EP0531202B1 (en)
DE (1) DE69200622T2 (en)
FR (1) FR2681095B1 (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5394687A (en) * 1993-12-03 1995-03-07 The United States Of America As Represented By The Department Of Energy Gas turbine vane cooling system
US6398486B1 (en) * 2000-06-01 2002-06-04 General Electric Company Steam exit flow design for aft cavities of an airfoil
JP2002155703A (en) * 2000-11-21 2002-05-31 Mitsubishi Heavy Ind Ltd Sealing structure for stream passage between stationary blade and blade ring of gas turbine
US6589010B2 (en) 2001-08-27 2003-07-08 General Electric Company Method for controlling coolant flow in airfoil, flow control structure and airfoil incorporating the same
FR2851287B1 (en) * 2003-02-14 2006-12-01 Snecma Moteurs ANNULAR DISPENSER PLATFORM FOR TURBOMACHINE LOW PRESSURE TURBINE
US8454303B2 (en) * 2010-01-14 2013-06-04 General Electric Company Turbine nozzle assembly
EP2626519A1 (en) 2012-02-09 2013-08-14 Siemens Aktiengesellschaft Turbine assembly, corresponding impingement cooling tube and gas turbine engine
JP5868802B2 (en) * 2012-07-20 2016-02-24 株式会社東芝 Turbine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3471126A (en) * 1966-10-31 1969-10-07 United Aircraft Corp Movable vane unit
BE794195A (en) * 1972-01-18 1973-07-18 Bbc Sulzer Turbomaschinen COOLED STEERING VANE FOR GAS TURBINES
US4288201A (en) * 1979-09-14 1981-09-08 United Technologies Corporation Vane cooling structure
JPS58206803A (en) * 1982-05-27 1983-12-02 Hitachi Ltd Nozzle segment of gas turbine
JPS61132705A (en) * 1984-11-30 1986-06-20 Hitachi Ltd Gas turbine nozzle
SU1359439A1 (en) * 1986-07-11 1987-12-15 Московский энергетический институт Steam turbine take-off chamber
JP2862536B2 (en) * 1987-09-25 1999-03-03 株式会社東芝 Gas turbine blades

Also Published As

Publication number Publication date
US5217347A (en) 1993-06-08
DE69200622T2 (en) 1995-04-27
FR2681095A1 (en) 1993-03-12
DE69200622D1 (en) 1994-12-08
FR2681095B1 (en) 1993-11-19
EP0531202A1 (en) 1993-03-10

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