EP1508670B1 - Cooled vane of a gas turbine - Google Patents

Cooled vane of a gas turbine Download PDF

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Publication number
EP1508670B1
EP1508670B1 EP04300530.5A EP04300530A EP1508670B1 EP 1508670 B1 EP1508670 B1 EP 1508670B1 EP 04300530 A EP04300530 A EP 04300530A EP 1508670 B1 EP1508670 B1 EP 1508670B1
Authority
EP
European Patent Office
Prior art keywords
blade
sleeve
opening
liner
air
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
EP04300530.5A
Other languages
German (de)
French (fr)
Other versions
EP1508670A2 (en
EP1508670A3 (en
Inventor
Christophe Texier
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
Safran Aircraft Engines SAS
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Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP1508670A2 publication Critical patent/EP1508670A2/en
Publication of EP1508670A3 publication Critical patent/EP1508670A3/en
Application granted granted Critical
Publication of EP1508670B1 publication Critical patent/EP1508670B1/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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the present invention relates to blade cooling in a gas turbine engine, in particular turbine nozzle blades.
  • air is compressed in a compressor and mixed with fuel in the combustion chamber.
  • the flow out of the latter drives one or more turbines, before being ejected into an ejection nozzle.
  • the turbine stages comprise rotors separated by distributors for orienting the gas flows. Due to the temperature of the gases flowing through them, the blades are subjected to very severe operating conditions; it is therefore necessary to cool them, usually by forced convection or by air impact, inside the blades.
  • the figure 1 represents a prior art distributor blade 1, in which the cooling is provided by a multi-perforated longitudinal sleeve 4.
  • the blade 1 extends between two platforms, an inner platform 3 and an external platform 2, which define the annular channel 5 for circulating the gas in the turbine. This channel is subdivided circumferentially by the blades 1.
  • the multiperforated jacket 4 is slid longitudinally into the central cavity 6 of the blade 1.
  • a duct 7 supplies the jacket 4 with cold air, taken from the compressor, for example. Due to the pressure difference existing between the interior of the liner 4 and the peripheral zone of the cavity 6 delimited by the outer wall of the liner 4 and the inner wall of the blade 1, part of the air is projected, via the perforations of the liner 4, against the inner wall of the blade 1, thus ensuring its cooling.
  • This air is then evacuated, along the trailing edge of the blade 1, by calibrated perforations in the gas vein 5. The rest of the air is evacuated through the internal platform 3 into a second duct 8 which leads to other parts of the engine to be cooled, such as the turbine disk or the bearings.
  • the central cavity 6 of the blade 1 comprises two openings 9, 10, respectively at the outer platform 2 and the inner platform 3.
  • the jacket 4 is slid by the outer opening 9 of the blade 1, and secured to the outer platform 2, generally by brazing along the wall of the outer opening 9.
  • the opposite part of the sleeve 4 is guided in the opening inner 10 of the blade 1, forming a slide in the inner platform 3 to allow relative movement between the shirt and the blade. Indeed, because of the differences between the materials and the manufacturing methods between the blade 1 and the jacket 4, as well as between the operating temperatures, it follows a variation of elongation between the blade 1 and the shirt 4.
  • the slide 10 ensures the maintenance of the whole.
  • the blade 1 is formed by casting, while the jacket 4 is formed by forming a sheet. Given the difference between the development modes of the blade 1 and the sleeve 4, the play along the slide 10 is relatively important; this game results in particular manufacturing tolerances. It creates an air leak at the outlet of the jacket 4, since the pressure in the peripheral zone of the cavity 6 is lower than in the central channel formed by the jacket 4.
  • the present invention aims to overcome these disadvantages.
  • the invention relates to a blade according to the subject of claim 1.
  • the solution of the invention is simple and inexpensive. It also has the advantage of allowing the calibration of the cooling rate of the disks.
  • the distributor vane 11 of the invention extends between an outer platform 12 and an inner platform 13 of the gas turbine engine distributor, which delimit an annular channel 15 for circulating the gas in the turbine . It comprises a central longitudinal cavity 16, providing two outer and inner openings 19, respectively at the level of the outer platform 12 and the inner platform 13.
  • a liner 14 is inserted into the central cavity 16 of the blade, providing a peripheral cooling cavity between the outer wall of the liner 14 and the inner wall of the blade 11.
  • the liner 14 is attached to the wall of the liner. outer opening 19 of the blade 11, by brazing or welding, for example. It is further guided, at an end portion 21, in the inner opening 20 forming a slide for this purpose.
  • it is possible for it to slide in the slide 20, in order to make the whole of the blade integral despite the differential expansions between its various elements.
  • the part of the air not projected on the inner wall of the blade 11 is removed from the jacket 14 by a pipe 18 extending at the level of the inner platform 13, following the slide 20.
  • the shirt 14 of the dawn 11 of the figure 3 formed by folding sheet metal is folded in the region of its end portion 21 guided by the slide 20, so as to form a narrowing 22 for the flow of air which is guided in its cavity. More specifically, the constriction 22 is made in the region of the end portion 21 of the liner 14 housed inside the slideway 20. In the embodiment of FIG. figure 4 this folding is of curved profile.
  • the figure 5 represents a second embodiment of a jacket 14 'of the blade 11.
  • a jacket 14 'of the blade 11 In the latter, it is provided, to obtain the same results as above, brazing or welding, at the end of the end portion 21 14 of the liner 14 'intended to be guided by the slide 20, a calibrated wafer 23' pierced, over most of its surface in this case, an opening 24 'for passage of air. This gives a portion 22 'of transverse dimensions narrowed relative to the transverse dimensions of the slide 20.
  • the third embodiment of the liner of the invention is advantageous with respect to the second in that it makes it possible to minimize the pressure drops at the entrance of the cone.

Landscapes

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

Description

La présente invention concerne le refroidissement d'aubes dans un moteur à turbine à gaz, en particulier d'aubes de distributeur de turbine.The present invention relates to blade cooling in a gas turbine engine, in particular turbine nozzle blades.

Dans un moteur à turbine à gaz, l'air est comprimé dans un compresseur et est mélangé à un carburant dans la chambre de combustion. Le flux sortant de cette dernière entraîne une ou plusieurs turbines, avant d'être éjecté dans une tuyère d'éjection.In a gas turbine engine, air is compressed in a compressor and mixed with fuel in the combustion chamber. The flow out of the latter drives one or more turbines, before being ejected into an ejection nozzle.

Les étages de turbines comprennent des rotors séparés par des distributeurs, destinés à orienter les flux de gaz. En raison de la température des gaz qui les parcourent, les aubes sont soumises à des conditions de fonctionnement très sévères ; il est donc nécessaire de les refroidir, en général par convection forcée ou bien par impact d'air, à l'intérieur des aubes.The turbine stages comprise rotors separated by distributors for orienting the gas flows. Due to the temperature of the gases flowing through them, the blades are subjected to very severe operating conditions; it is therefore necessary to cool them, usually by forced convection or by air impact, inside the blades.

US 3 767 322 A divulgue une aube refroidie comprenant une chemise longitudinale dont la portion d'extrémité comprend un rétrécissement. US 3,767,322 A discloses a cooled blade comprising a longitudinal liner whose end portion comprises a narrowing.

La figure 1 représente une aube 1 de distributeur de l'art antérieur, dans laquelle le refroidissement est assuré par une chemise longitudinale multiperforée 4. L'aube 1 s'étend entre deux plates-formes, une plate-forme intérieure 3 et une plate-forme extérieure 2, qui délimitent le canal annulaire 5 de circulation du gaz dans la turbine. Ce canal est subdivisé circonférentiellement par les aubes 1.The figure 1 represents a prior art distributor blade 1, in which the cooling is provided by a multi-perforated longitudinal sleeve 4. The blade 1 extends between two platforms, an inner platform 3 and an external platform 2, which define the annular channel 5 for circulating the gas in the turbine. This channel is subdivided circumferentially by the blades 1.

La chemise multiperforée 4 est glissée longitudinalement dans la cavité 6 centrale de l'aube 1. Au niveau de la plate-forme extérieure 2, un conduit 7 alimente la chemise 4 en air froid, prélevé au compresseur par exemple. En raison de la différence de pression existant entre l'intérieur de la chemise 4 et la zone périphérique de la cavité 6 délimitée par la paroi extérieure de la chemise 4 et la paroi intérieure de l'aube 1, une partie de l'air est projetée, via les perforations de la chemise 4, contre la paroi interne de l'aube 1, assurant ainsi son refroidissement. Cet air est ensuite évacué, le long du bord de fuite de l'aube 1, par des perforations calibrées, dans la veine de gaz 5. Le reste de l'air est évacué à travers la plate-forme interne 3 dans un second conduit 8 qui le mène vers d'autres parties du moteur à refroidir, telles que le disque de turbine ou les paliers.The multiperforated jacket 4 is slid longitudinally into the central cavity 6 of the blade 1. At the outer platform 2, a duct 7 supplies the jacket 4 with cold air, taken from the compressor, for example. Due to the pressure difference existing between the interior of the liner 4 and the peripheral zone of the cavity 6 delimited by the outer wall of the liner 4 and the inner wall of the blade 1, part of the air is projected, via the perforations of the liner 4, against the inner wall of the blade 1, thus ensuring its cooling. This air is then evacuated, along the trailing edge of the blade 1, by calibrated perforations in the gas vein 5. The rest of the air is evacuated through the internal platform 3 into a second duct 8 which leads to other parts of the engine to be cooled, such as the turbine disk or the bearings.

La cavité centrale 6 de l'aube 1 comprend deux ouvertures 9, 10, au niveau respectivement de la plate-forme extérieure 2 et de la plate-forme intérieure 3. Au moment du montage de l'aube, la chemise 4 est glissée par l'ouverture extérieure 9 de l'aube 1, et rendue solidaire à la plate-forme extérieure 2, généralement par brasage le long de la paroi de l'ouverture extérieure 9. La partie opposée de la chemise 4 est guidée dans l'ouverture intérieure 10 de l'aube 1, formant une glissière dans la plate-forme intérieure 3 pour autoriser les déplacements relatifs entre la chemise et l'aube. En effet, en raison des différences entre les matériaux et les modes de fabrication entre l'aube 1 et la chemise 4, ainsi qu'entre les températures de fonctionnement, il s'ensuit une variation d'allongement entre l'aube 1 et la chemise 4. La glissière 10 assure le maintien de l'ensemble.The central cavity 6 of the blade 1 comprises two openings 9, 10, respectively at the outer platform 2 and the inner platform 3. At the time of assembly of the blade, the jacket 4 is slid by the outer opening 9 of the blade 1, and secured to the outer platform 2, generally by brazing along the wall of the outer opening 9. The opposite part of the sleeve 4 is guided in the opening inner 10 of the blade 1, forming a slide in the inner platform 3 to allow relative movement between the shirt and the blade. Indeed, because of the differences between the materials and the manufacturing methods between the blade 1 and the jacket 4, as well as between the operating temperatures, it follows a variation of elongation between the blade 1 and the shirt 4. The slide 10 ensures the maintenance of the whole.

L'aube 1 est formée par fonderie, tandis que la chemise 4 est formée par formage d'une tôle. Compte tenu de la différence entre les modes d'élaboration de l'aube 1 et de la chemise 4, le jeu le long de la glissière 10 est relativement important ; ce jeu résulte notamment des tolérances de fabrication. Il crée une fuite d'air au niveau de la sortie de chemise 4, puisque la pression dans la zone périphérique de la cavité 6 est plus faible que dans le canal central formé par la chemise 4.The blade 1 is formed by casting, while the jacket 4 is formed by forming a sheet. Given the difference between the development modes of the blade 1 and the sleeve 4, the play along the slide 10 is relatively important; this game results in particular manufacturing tolerances. It creates an air leak at the outlet of the jacket 4, since the pressure in the peripheral zone of the cavity 6 is lower than in the central channel formed by the jacket 4.

En référence à la figure 2, la fuite d'air illustrée par la flèche F présente le premier inconvénient d'entraîner une surpression dans la zone périphérique de la cavité 6. Cette surpression est préjudiciable à la qualité du refroidissement interne de l'aube 1 et plus particulièrement au niveau de la zone du bord d'attaque qui en est la zone la plus chaude, puisque l'air passant dans la cavité centrale de la chemise 4 a moins tendance à être projeté via les perforations de la chemise 4 contre la paroi interne de l'aube 1. Par ailleurs, l'air provenant de la fuite ne participe pas au refroidissement de l'aube puisqu'il est entraîné directement vers les orifices d'évacuation situés sur le bord de fuite. En outre, la quantité d'air entraîné dans le conduit 8 afin de refroidir d'autres parties du moteur est réduite du fait de la fuite.With reference to the figure 2 , the air leak illustrated by the arrow F has the first drawback of causing an overpressure in the peripheral zone of the cavity 6. This excess pressure is detrimental to the quality of the internal cooling of the blade 1 and more particularly to the level of the zone of the leading edge which is the hottest zone, since the air passing through the central cavity of the liner 4 is less likely to be projected via the perforations of the liner 4 against the inner wall of the dawn 1. Moreover, the air coming from the leak does not participate in the cooling of the dawn since it is driven directly towards the evacuation orifices located on the trailing edge. In addition, the amount of air entrained in the conduit 8 to cool other parts of the engine is reduced due to leakage.

Il a été envisagé de remédier à la fuite d'air par des systèmes d'étanchéité, mais ces derniers nuisent au coulissement de la chemise 4 dans la glissière 10, nécessaire à la compensation des différences de dilatation évoquées plus haut.It has been envisaged to remedy the leakage of air by sealing systems, but these impede the sliding of the liner 4 in the slideway 10, necessary to compensate for the differences in expansion mentioned above.

La présente invention vise à pallier ces inconvénients.The present invention aims to overcome these disadvantages.

A cet effet, l'invention concerne une aube selon l'objet de la revendication 1. La solution de l'invention est simple et peu coûteuse. Elle présente aussi l'avantage de permettre le calibrage du débit de refroidissement des disques.For this purpose, the invention relates to a blade according to the subject of claim 1. The solution of the invention is simple and inexpensive. It also has the advantage of allowing the calibration of the cooling rate of the disks.

L'invention sera mieux comprise grâce à la description suivante de la forme de réalisation préférée de l'aube de l'invention, en rapport au dessin annexé, sur lequel :

  • la figure 1 représente une vue de profil en coupe d'une aube de l'art antérieur ;
  • la figure 2 représente une vue de profil en coupe de la chemise dans la glissière de l'aube de la figure 1 ;
  • la figure 3 représente une vue de profil en coupe d'une première forme de réalisation de l'aube de l'invention ;
  • la figure 4 représente une vue de profil en coupe de la chemise de l'aube de la figure 3 ;
  • la figure 5 représente une vue de profil en coupe de la chemise d'une deuxième forme de réalisation de l'aube de l'invention, et
  • la figure 6 représente une vue de profil en coupe de la chemise d'une troisième forme de réalisation de l'aube de l'invention.
The invention will be better understood thanks to the following description of the preferred embodiment of the blade of the invention, with reference to the appended drawing, in which:
  • the figure 1 represents a sectional profile view of a blade of the prior art;
  • the figure 2 represents a sectional profile view of the shirt in the slide of the dawn of the figure 1 ;
  • the figure 3 represents a sectional side view of a first embodiment of the blade of the invention;
  • the figure 4 represents a sectional profile view of the dawn shirt from the figure 3 ;
  • the figure 5 represents a sectional sectional view of the liner of a second embodiment of the blade of the invention, and
  • the figure 6 represents a sectional sectional view of the liner of a third embodiment of the blade of the invention.

Bien que l'invention s'applique à tout type d'aube, elle sera particulièrement décrite en lien avec une aube de distributeur de turbine.Although the invention applies to any type of blade, it will be particularly described in connection with a turbine nozzle blade.

En référence à la figure 3, l'aube 11 de distributeur de l'invention s'étend entre une plate-forme extérieure 12 et une plate-forme intérieure 13 du distributeur du moteur à turbine à gaz, qui délimitent un canal annulaire 15 de circulation du gaz dans la turbine. Elle comprend une cavité centrale 16 longitudinale, ménageant deux ouvertures extérieure 19 et intérieure 20, respectivement au niveau de la plate-forme extérieure 12 et de la plate-forme intérieure 13.With reference to the figure 3 , the distributor vane 11 of the invention extends between an outer platform 12 and an inner platform 13 of the gas turbine engine distributor, which delimit an annular channel 15 for circulating the gas in the turbine . It comprises a central longitudinal cavity 16, providing two outer and inner openings 19, respectively at the level of the outer platform 12 and the inner platform 13.

Une chemise 14 est insérée dans la cavité centrale 16 de l'aube, ménageant une cavité périphérique de refroidissement entre la paroi externe de la chemise 14 et la paroi interne de l'aube 11. La chemise 14 est fixée à la paroi de l'ouverture extérieure 19 de l'aube 11, par brasage ou soudage, par exemple. Elle est en outre guidée, au niveau d'une portion d'extrémité 21, dans l'ouverture intérieure 20 formant glissière à cet effet. Ainsi, il lui est possible de coulisser dans la glissière 20, afin de rendre l'ensemble de l'aube solidaire malgré les dilatations différentielles entre ses divers éléments.A liner 14 is inserted into the central cavity 16 of the blade, providing a peripheral cooling cavity between the outer wall of the liner 14 and the inner wall of the blade 11. The liner 14 is attached to the wall of the liner. outer opening 19 of the blade 11, by brazing or welding, for example. It is further guided, at an end portion 21, in the inner opening 20 forming a slide for this purpose. Thus, it is possible for it to slide in the slide 20, in order to make the whole of the blade integral despite the differential expansions between its various elements.

Au niveau de la plate-forme extérieure 12, la chemise 14 est alimentée, par un conduit 17, en air provenant de niveaux plus froids du moteur à turbine. Du fait de la différence de pression existant entre la cavité centrale de la chemise 14 et la cavité périphérique de refroidissement de la cavité 16, une partie de cet air est projeté de la cavité centrale de la chemise vers la paroi interne de l'aube, par des perforations ménagées à cet effet sur la chemise 14, du côté notamment du bord d'attaque de l'aube 11. Cet air est ensuite évacué par des perforations calibrées ménagées au bord de fuite de l'aube 11.At the outer platform 12, the liner 14 is fed, via a conduit 17, with air from colder levels of the turbine engine. Due to the pressure difference existing between the central cavity of the liner 14 and the peripheral cooling cavity cavity 16, a portion of this air is projected from the central cavity of the liner to the inner wall of the blade, perforations provided for this purpose on the liner 14, in particular on the leading edge of the blade 11. This air is then evacuated by calibrated perforations formed at the trailing edge of the blade 11.

La partie de l'air non projeté sur la paroi interne de l'aube 11 est évacuée de la chemise 14 par un conduit 18 s'étendant, au niveau de la plate-forme intérieure 13, à la suite de la glissière 20.The part of the air not projected on the inner wall of the blade 11 is removed from the jacket 14 by a pipe 18 extending at the level of the inner platform 13, following the slide 20.

En référence à la figure 4, la chemise 14 de l'aube 11 de la figure 3, formée par pliage de tôle, est repliée dans la zone de sa portion d'extrémité 21 guidée par la glissière 20, de manière à former un rétrécissement 22 pour le flux d'air qui est guidé dans sa cavité. Plus précisément, le rétrécissement 22 est effectué dans la zone de la portion d'extrémité 21 de la chemise 14 logée à l'intérieur de la glissière 20. Dans la forme de réalisation de la figure 4, ce pliage est de profil courbe.With reference to the figure 4 , the shirt 14 of the dawn 11 of the figure 3 formed by folding sheet metal, is folded in the region of its end portion 21 guided by the slide 20, so as to form a narrowing 22 for the flow of air which is guided in its cavity. More specifically, the constriction 22 is made in the region of the end portion 21 of the liner 14 housed inside the slideway 20. In the embodiment of FIG. figure 4 this folding is of curved profile.

Il s'agit en fait de créer, dans la portion d'extrémité 21 de la chemise 14 guidée par la glissière 20, une zone 22 dont les dimensions transversales sont nettement rétrécies par rapport aux dimensions transversales de la glissière 20.It is in fact to create, in the end portion 21 of the liner 14 guided by the slide 20, a zone 22 whose transverse dimensions are significantly narrowed relative to the transverse dimensions of the slide 20.

Ainsi, grâce au pliage de la chemise 14, une perte de charge est créée à l'extrémité repliée 22 de la chemise 14. Cette perte de charge implique une chute de la pression statique en sortie de la chemise 14. Par conséquent, grâce à une conformation ad hoc du pliage, il est possible de régler la pression statique en sortie de la chemise 14 par rapport à la pression statique de la zone de refroidissement de la cavité 16 de l'aube 14, de façon à annuler ou au moins réduire, dans la glissière 20, la fuite d'air en sortie de la chemise 14 vers ladite zone de refroidissement.Thus, thanks to the folding of the jacket 14, a pressure drop is created at the folded end 22 of the jacket 14. This pressure drop implies a drop in the static pressure at the outlet of the jacket 14. By Therefore, thanks to an ad hoc conformation of the folding, it is possible to adjust the static pressure at the outlet of the liner 14 with respect to the static pressure of the cooling zone of the cavity 16 of the blade 14, so as to cancel or at least reduce, in the slide 20, the air leak at the outlet of the jacket 14 to said cooling zone.

Ainsi, grâce à l'invention, il est possible de remédier à la fuite d'air sans changer la structure ni le mode d'élaboration du corps de l'aube 11, en conformant convenablement la portion d'extrémité 21 de la chemise 11, sans coûts de production supplémentaires.Thus, thanks to the invention, it is possible to remedy the air leakage without changing the structure or the method of elaboration of the body of the blade 11, by suitably conforming the end portion 21 of the jacket 11 , without additional production costs.

La figure 5 représente une deuxième forme de réalisation d'une chemise 14' de l'aube 11. Dans cette dernière, il est prévu, pour obtenir les mêmes résultats que précédemment, de braser ou souder, à l'extrémité de la portion d'extrémité 21' de la chemise 14' destinée à être guidée par la glissière 20, une plaquette calibrée 23' percée, sur la majeure partie de sa surface en l'occurrence, d'une ouverture 24' de passage de l'air. On obtient bien ainsi une portion 22' de dimensions transversales rétrécies par rapport aux dimensions transversales de la glissière 20.The figure 5 represents a second embodiment of a jacket 14 'of the blade 11. In the latter, it is provided, to obtain the same results as above, brazing or welding, at the end of the end portion 21 14 of the liner 14 'intended to be guided by the slide 20, a calibrated wafer 23' pierced, over most of its surface in this case, an opening 24 'for passage of air. This gives a portion 22 'of transverse dimensions narrowed relative to the transverse dimensions of the slide 20.

La figure 6 représente une troisième forme de réalisation d'une chemise 14" de l'aube 11. Dans cette dernière, il est prévu de braser, à l'extrémité de la portion d'extrémité 21" de la chemise 14" destinée à être guidée par la glissière 20, un tube 23" de forme conique dont les dimensions transversales vont en s'amoindrissant en s'éloignant de l'extrémité de la chemise 14". On obtient bien ainsi une portion 22" de dimensions transversales rétrécies par rapport aux dimensions transversales de la glissière 20.The figure 6 represents a third embodiment of a liner 14 "of the blade 11. In the latter, it is intended to braze at the end of the end portion 21" of the liner 14 "intended to be guided by the slideway 20, a conically-shaped tube 23 ", the transverse dimensions of which are diminishing away from the end of the liner 14", thus obtaining a portion 22 "of transverse dimensions narrowed with respect to the dimensions transverse of the slide 20.

La troisième forme de réalisation de la chemise de l'invention est avantageuse par rapport à la deuxième en ce sens qu'elle permet de minimiser les pertes de charge à l'entrée du cône.The third embodiment of the liner of the invention is advantageous with respect to the second in that it makes it possible to minimize the pressure drops at the entrance of the cone.

Claims (4)

  1. A cooled gas turbine engine vane comprising a cast part (11) and a longitudinal sleeve (14, 14', 14") for guiding the flow of cooling air obtained by shaping sheet metal, the cast part (11) comprising a longitudinal body provided with a longitudinal cavity (16) having a first opening (19) for feeding and a second opening (20) for evacuating of air at the ends, the sleeve (14, 14', 14") being mounted in the cavity (16) by being attached to the wall of the first opening (19), and of which one end portion (21, 21', 21") is free to slide into the second opening forming a guide (20), characterised by the fact that said end portion (21, 21', 21") comprises a constriction (22, 22', 22") of its passage cross-section for the air flow, said constriction (22, 22', 22") being a) a fold of curved profile section of the end of the sleeve (14), or b) being obtained by fixing a tube (23") with conical shape of which the crosswise dimensions diminish while extending away from the end of the sleeve (14").
  2. A vane according to claim 1, wherein the sleeve (14, 14', 14") is attached to the wall of the first opening (19) by welding or by brazing.
  3. A vane according to claim 1 or 2, wherein the sleeve (14, 14', 14") is perforated.
  4. A vane according to claim 3, wherein the cast part comprises calibrated perforations.
EP04300530.5A 2003-08-12 2004-08-11 Cooled vane of a gas turbine Expired - Lifetime EP1508670B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0309869A FR2858829B1 (en) 2003-08-12 2003-08-12 AUBE COOLING OF GAS TURBINE ENGINE
FR0309869 2003-08-12

Publications (3)

Publication Number Publication Date
EP1508670A2 EP1508670A2 (en) 2005-02-23
EP1508670A3 EP1508670A3 (en) 2005-03-09
EP1508670B1 true EP1508670B1 (en) 2017-12-13

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP04300530.5A Expired - Lifetime EP1508670B1 (en) 2003-08-12 2004-08-11 Cooled vane of a gas turbine

Country Status (7)

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US (1) US7204675B2 (en)
EP (1) EP1508670B1 (en)
JP (1) JP4234650B2 (en)
CA (1) CA2478954C (en)
FR (1) FR2858829B1 (en)
RU (1) RU2351768C2 (en)
UA (1) UA84395C2 (en)

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FR2922597B1 (en) 2007-10-19 2012-11-16 Snecma AUBE COOLING TURBOMACHINE
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FR2943380B1 (en) * 2009-03-20 2011-04-15 Turbomeca DISTRIBUTOR VANE COMPRISING AT LEAST ONE SLOT
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Also Published As

Publication number Publication date
FR2858829B1 (en) 2008-03-14
FR2858829A1 (en) 2005-02-18
US20050089395A1 (en) 2005-04-28
EP1508670A2 (en) 2005-02-23
RU2004124543A (en) 2006-01-27
US7204675B2 (en) 2007-04-17
JP4234650B2 (en) 2009-03-04
CA2478954C (en) 2012-05-01
CA2478954A1 (en) 2005-02-12
EP1508670A3 (en) 2005-03-09
UA84395C2 (en) 2008-10-27
JP2005061412A (en) 2005-03-10
RU2351768C2 (en) 2009-04-10

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