EP0032646A1 - Turbine guide vane - Google Patents

Turbine guide vane Download PDF

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Publication number
EP0032646A1
EP0032646A1 EP80401849A EP80401849A EP0032646A1 EP 0032646 A1 EP0032646 A1 EP 0032646A1 EP 80401849 A EP80401849 A EP 80401849A EP 80401849 A EP80401849 A EP 80401849A EP 0032646 A1 EP0032646 A1 EP 0032646A1
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EP
European Patent Office
Prior art keywords
jacket
turbine distributor
perforations
rows
leading edge
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
EP80401849A
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German (de)
French (fr)
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EP0032646B1 (en
Inventor
Denis René Guy Laffitte
Guy Henri Louis
Alain Marius Marcel Raybaud
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
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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 EP0032646A1 publication Critical patent/EP0032646A1/en
Application granted granted Critical
Publication of EP0032646B1 publication Critical patent/EP0032646B1/en
Expired 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

Definitions

  • the present invention relates to a turbine distributor blade.
  • High performance turbomachines are equipped with turbine guide vanes capable of withstanding temperatures in the region of 1500 ° C. and it is even envisaged to use blades capable of operating at higher temperatures.
  • Such blades require a very sophisticated cooling system and a system of internal channels. It is known to use turbine distributor vanes comprising at least one internal cavity in which a jacket of perforated sheet metal bears against the walls by means of projecting elements.
  • the arrangement of the projecting elements constituted by cylindrical studs and fins does not generally make it possible to obtain a coefficient of heat exchange sufficient for the operating temperatures envisaged.
  • the projecting elements against which the jacket is supported are arranged for the lower and upper surfaces in an area extending substantially over the entire height to become minimal at the top, the internal cavity having an opening at its upper part through which the coolant enters.
  • This arrangement of the projecting elements according to the invention which consists of arranging them in the form of triangle or trapezoidal zones, makes it possible to arrange evolving passage sections such as the ratio of the residual cold air flow rate over the passage area remains substantially constant.
  • the jacket is kept under pressure against the projecting elements and in the open position by a rigid locking device such as a longitudinal lock pierced with orifices.
  • a rigid locking device such as a longitudinal lock pierced with orifices.
  • the main chamber located behind the leading edge and in which the jacket is mounted is divided into three cooling zones which do not communicate with each other, which improves the cooling of the blade by the air circulation.
  • FIG. 1 shows a part of the turbine of a turbomachine which is located at the outlet of a combustion chamber 1 and which comprises a guide vane 2 and a turbine fin 3 which are located in the channel d annular flow 4 of the combustion gases.
  • the guide blade 2 is part of a row of blades which is arranged circularly in the flow channel 4.
  • Each blade 2 has in known manner a head 5 and a foot 6 ( Figures 1, 2, 3) said head having an opening 7 through which penetrates the cooling air from the compressor. The air is distributed in the various internal channels as will be described later.
  • Each blade comprises a main chamber 6, an intermediate chamber 9 and a trailing edge area 10, also visible in FIGS. 4 and 5.
  • the main chamber 8 occupies almost 2/3 of the internal volume of the blade; this makes it possible to reduce the Mach number of the heat transfer fluid, therefore to maintain a high pressure level.
  • the latter is first channeled in an internal jacket 12 made of sheet metal which insulates it from the walls.
  • the sheet metal jacket 12 consists of two plates, one of which 12a extends over the entire width of the main chamber 8 and the other of which 12b is fixed on the first to form a U-shaped jacket open to one of its ends towards the leading edge 11.
  • the jacket 12 is supported in substantially sealed manner by the plate 12a against the central partition 13 separating the main chamber 8 from the intermediate chamber 9 and it is supported by its plate 12a against cylindrical or frustoconical studs 14 located on the upper surface side and by its plate 12b against transverse fins 15 located on the lower side.
  • the plates 12a and 12b of the jacket rest on two ribs 16, 16a and they are held in the open position by a longitudinal latch 17 engaged in ribs provided in the edges of the two plates 12a, 12b .
  • the latch 17 consists of a plate having openings 17a opening towards the leading edge 11.
  • the rows of studs 14 coming from the foundry on the internal face of the upper surface as well as the transverse fins 15 formed on the lower surface are arranged in an area extending substantially over the entire height. and whose width which is maximum at the base gradually evolves over the entire height to become minimum at the top.
  • This arrangement of the projecting elements 14 and 15 which consists of arranging them in the shape of a triangle or trapezoid makes it possible to arrange scalable passage sections such that the ratio of the flow of residual cold air over the passage area remains substantially constant . This results in better cooling of the walls of the blade.
  • the blade has rows of perforators 18 on the leading edge, of perforations 19 on the lower surface, near the leading edge and near the internal partition, of perforations 20 on the upper surface near the leading edge.
  • the diameter of these perforations is very small, of the order of 0.3 mm.
  • a staggered arrangement will be adopted.
  • the arrangement of the jacket 12 in the main bedroom is such that it divides said bedroom into three independent zones A, B, C (see FIG. 5).
  • zone B The air which arrives through the head 7 of the blade 2 is also distributed on the one hand in zone B, passes through the fins 15 and escapes through the perforations 19, and on the other hand in zone C, passes through the studs 14 and escapes through the perforations 20.
  • zone B between the sleeve 12 and the fins 15 and in zone C between the sleeve 12 and the studs 14 is small; this allows a high Mach number and a low feed rate which is favorable for convection cooling.
  • the external exchange coefficient (intake of calories) being stronger on the upper surface than on the lower surface, we use fins on the lower surface and studs on the upper surface.
  • This cooling by fins is less effective but provides a lower pressure drop.
  • the pads 14 have a larger wetted surface and create a turbulence favorable to exchanges.
  • the zones B for supplying the fins 15 and C for supplying the studs 14 decrease as one approaches the foot of the dawn. Conversely, the length of the fins or rows of studs increases, which makes it possible to largely balance the exchanges over the entire surface of the blade.
  • the intermediate chamber 9 comprises on the lower surface side (FIG. 2) a smooth part 21 which occupies a right triangle whose base is constituted by the upper part of the chamber and the top by the internal lower corner.
  • a smooth part 21 which occupies a right triangle whose base is constituted by the upper part of the chamber and the top by the internal lower corner.
  • rows of studs 22 from the foundry are provided, distributed over a right triangle whose apex occupies the upper downstream corner of the chamber 9.
  • the longitudinal ribs 23 and the rows of studs 24 are sufficient for cooling the upper surface. It should also be noted that, in this zone, the density of the fins decreases and that the density of the studs increases when one approaches the foot of the dawn.
  • the intermediate chamber 9 opens into a groove 26 (FIG. 4, 5) occupying the entire length of the trailing edge, by slots 27 separated by bridges 28 from the foundry.
  • the slots 27 are divided into passages 29, 30, 31 delimited by two rows of studs 32, 33 secured to the lower surface as well as the upper surface.
  • a latch 17 has been shown consisting of a perforated plate to hold the edges of the jacket 12 in the open position, it is also possible to keep the plates open by engaging the ends of the plates 12a and 12b in slots formed in the ribs 16, 16a.

Abstract

Aube de distributeur de turbine du type comportant au moins une cavité interne dans laquelle une chemise en tôle est maintenue en appui contre les parois par l'intermédiaire d'éléments en saillie. Les éléments en saillie (14, 15) contre lesquels la chemise (12) est en appui sont disposés pour les parois d'intrados et d'extrados suivant une zone s'étendant sensiblement sur toute la hauteur et dont la largeur qui est maximale à la base évolue progressivement sur toute la hauteur pour devenir minimale à la partie supérieure. L'invention est utilisée pour la réalisation d'aubes de distributeur de turbine.Turbine distributor vane of the type comprising at least one internal cavity in which a sheet metal jacket is held in abutment against the walls by means of projecting elements. The projecting elements (14, 15) against which the jacket (12) is supported are arranged for the lower and upper surfaces in an area extending substantially over the entire height and whose width which is maximum at the base gradually evolves over the entire height to become minimal at the top. The invention is used for the production of turbine distributor blades.

Description

La présente invention a pour objet une aube de distributeur de turbine.The present invention relates to a turbine distributor blade.

Les turbomachines à hautes performances sont dotées d'aubes directrices de turbine capables de résister à des températures voisines de 1500°C et il est même envisagé d'utiliser des aubes capables de fonctionner à des températures supérieures.High performance turbomachines are equipped with turbine guide vanes capable of withstanding temperatures in the region of 1500 ° C. and it is even envisaged to use blades capable of operating at higher temperatures.

De telles aubes nécessitent un système de refroidissement énergique et un système de canaux internes très élaborés. Il est connu d'utiliser des aubes de distributeur de turbine comportant au moins une cavité interne dans laquelle une chemise en tôle perforée est en appui contre les parois par l'intermédiaire d'éléments en saillie.Such blades require a very sophisticated cooling system and a system of internal channels. It is known to use turbine distributor vanes comprising at least one internal cavity in which a jacket of perforated sheet metal bears against the walls by means of projecting elements.

Toutefois la disposition des éléments en saillie constitués par des plots cylindriques et des ailettes ne permet pas généralement d'obtenir un coefficient d'échange thermique suffisant pour les températures de fonctionnement envisagées.However, the arrangement of the projecting elements constituted by cylindrical studs and fins does not generally make it possible to obtain a coefficient of heat exchange sufficient for the operating temperatures envisaged.

Conformément à la présente invention les éléments en saillie contre lesquels la chemise est en appui sont disposés pour les parois d'intrados et d'extrados suivant une zone s'étendant sensiblement sur toute la hauteur pour devenir minimale à la partie supérieure, la cavité interne présentant une ouverture à sa partie supérieure par laquelle pénètre le fluide de refroidissement. Cette disposition des éléments en saillie suivant l'invention, qui consiste à les disposer suivant des zones en forme de triangle ou de trapèze, permet d'aménager des sections de passage évolutives telles que le rapport du débit d'air froid résiduel sur l'aire de passage reste sensiblement constant.In accordance with the present invention the projecting elements against which the jacket is supported are arranged for the lower and upper surfaces in an area extending substantially over the entire height to become minimal at the top, the internal cavity having an opening at its upper part through which the coolant enters. This arrangement of the projecting elements according to the invention, which consists of arranging them in the form of triangle or trapezoidal zones, makes it possible to arrange evolving passage sections such as the ratio of the residual cold air flow rate over the passage area remains substantially constant.

Il en résulte un meilleur refroidissement des parois de l'aube. Suivant une autre caractéristique de l'invention, la chemise est maintenue en pression contre les éléments en saillie et en position d'ouverture par un dispositif de blocage rigide tel qu'un verrou longitudinal percé d'orifices. Cette disposition facilite le montage et assure un positionnement correct de la chemise d'où il résulte une bonne étanchéité des circuits délimités par la chemise.This results in better cooling of the walls of the blade. According to another characteristic of the invention, the jacket is kept under pressure against the projecting elements and in the open position by a rigid locking device such as a longitudinal lock pierced with orifices. This arrangement facilitates assembly and ensures correct positioning of the liner, which results in good sealing of the circuits delimited by the liner.

Suivant une autre caractéristique de l'invention, la chambre principale située derrière le bord d'attaque et dans laquelle est montée la chemise est divisée en trois zones de refroidissement ne communiquant pas entre elles, ce qui améliore le refroidissement de l'aube par la circulation de l'air.According to another characteristic of the invention, the main chamber located behind the leading edge and in which the jacket is mounted is divided into three cooling zones which do not communicate with each other, which improves the cooling of the blade by the air circulation.

D'autres caractéristiques et avantages de l'invention seront mieux compris à la lecture de la description qui va suivre d'un mode de réalisation et en se référant aux dessins annexés, sur lesquels :

  • - la figure 1 est une demi-vue en coupe longitudinale d'une turbine de turbomachine ;
  • - la figure 2 est une vue en coupe longitudinale d'une aube montrant la partie intérieure correspondant a l'intrados
  • - la figure 3 est une vue en coupe longitudinale d'une aube montrant la partie intérieure correspondant à l'extrados ;
  • - la figure 4 est une vue en coupe de l'aube suivant la ligne IV-IV de la figure 3 ;
  • - la figure 5 est une vue en coupe de l'aube suivant la ligne V-V de la figure 3.
Other characteristics and advantages of the invention will be better understood on reading the following description of an embodiment and with reference to the appended drawings, in which:
  • - Figure 1 is a half view in longitudinal section of a turbomachine turbine;
  • - Figure 2 is a longitudinal sectional view of a blade showing the inner part corresponding to the lower surface
  • - Figure 3 is a longitudinal sectional view of a blade showing the inner part corresponding to the upper surface;
  • - Figure 4 is a sectional view of the blade along the line IV-IV of Figure 3;
  • FIG. 5 is a sectional view of the blade along the line VV in FIG. 3.

A la figure 1 on a représenté une partie de la turbine d'une turbomachine qui est située à la sortie d'une chambre de combustion 1 et qui comprend une aube de guidage 2 et une ailette de turbine 3 qui sont situées dans le canal d'écoulement annulaire 4 des gaz de combustion. L'aube de guidage 2 fait partie d'une rangée d'aubes qui est disposée circulairement dans le canal d'écoulement 4. Chaque aube 2 présente de façon connue une tête 5 et un pied 6 (figures 1, 2, 3) ladite tête comportant une ouverture 7 par laquelle pénètre l'air de refroidissement issu du compresseur. L'air se répartit dans les différents canaux internes ainsi qu'il sera décrit ultérieurement. Chaque aube comprend une chambre principale 6, une chambre intermédiaire 9 et une zone de bord de fuite 10, visible également sur les figures 4 et 5.FIG. 1 shows a part of the turbine of a turbomachine which is located at the outlet of a combustion chamber 1 and which comprises a guide vane 2 and a turbine fin 3 which are located in the channel d annular flow 4 of the combustion gases. The guide blade 2 is part of a row of blades which is arranged circularly in the flow channel 4. Each blade 2 has in known manner a head 5 and a foot 6 (Figures 1, 2, 3) said head having an opening 7 through which penetrates the cooling air from the compressor. The air is distributed in the various internal channels as will be described later. Each blade comprises a main chamber 6, an intermediate chamber 9 and a trailing edge area 10, also visible in FIGS. 4 and 5.

Pour assurer un fonctionnement efficace du bord d'attaque 11, particulièrement critique, la chambre principale 8 occupe près des 2/3 du volume interne de l'aube ; ceci permet de réduire le nombre de Mach du fluide caloporteur,donc de conserver un niveau de pression élevé. De même, pour éviter un réchauffement prématuré de l'air de refroidissement, ce dernier est d'abord canalisé dans une chemise interne 12 en tôle qui l'isole des parois.To ensure efficient operation of the particularly critical leading edge 11, the main chamber 8 occupies almost 2/3 of the internal volume of the blade; this makes it possible to reduce the Mach number of the heat transfer fluid, therefore to maintain a high pressure level. Similarly, to avoid premature heating of the cooling air, the latter is first channeled in an internal jacket 12 made of sheet metal which insulates it from the walls.

La chemise en tôle 12 est constituée de deux plaques dont l'une 12a s'étend sur toute la largeur de la chambre principale 8 et dont l'autre 12b est fixée sur la première pour constituer une chemise en U ouverte à l'une de ses extrémités en direction du bord d'attaque 11.The sheet metal jacket 12 consists of two plates, one of which 12a extends over the entire width of the main chamber 8 and the other of which 12b is fixed on the first to form a U-shaped jacket open to one of its ends towards the leading edge 11.

La chemise 12 est en appui de façon pratiquement étanche par la plaque 12a contre la cloison centrale 13 séparant la chambre principale 8 de la chambre intermédiaire 9 et elle est en appui par sa plaque 12a contre des plots cylindriques ou tronconiques 14 situés du côté extrados et par sa plaque 12b contre des ailettes transversales 15 situées du côté intrados.The jacket 12 is supported in substantially sealed manner by the plate 12a against the central partition 13 separating the main chamber 8 from the intermediate chamber 9 and it is supported by its plate 12a against cylindrical or frustoconical studs 14 located on the upper surface side and by its plate 12b against transverse fins 15 located on the lower side.

Près du bord d'attaque, les plaques 12a et 12b de la chemise reposent sur deux nervures 16, 16a et elles sont maintenues en position d'ouverture par un verrou 17 longitudinal engagé dans des nervures prévues dans les bords des deux plaques 12a, 12b. Le verrou 17 est constitué d'une plaque présentant des ouvertures 17a débouchant en direction du bord d'attaque 11. Conformément à l'invention, les rangées de plots 14 venus de fonderie sur la face interne de la paroi d'extrados ainsi que les ailettes transversales 15 ménagées sur l'intrados sont disposées suivant une zone s'étendant sensiblement sur toute la hauteur et dont la largeur qui est maximale à la base évolue progressivement sur toute la hauteur pour devenir minimale à la partie supérieure.Near the leading edge, the plates 12a and 12b of the jacket rest on two ribs 16, 16a and they are held in the open position by a longitudinal latch 17 engaged in ribs provided in the edges of the two plates 12a, 12b . The latch 17 consists of a plate having openings 17a opening towards the leading edge 11. According to the invention, the rows of studs 14 coming from the foundry on the internal face of the upper surface as well as the transverse fins 15 formed on the lower surface are arranged in an area extending substantially over the entire height. and whose width which is maximum at the base gradually evolves over the entire height to become minimum at the top.

Cette disposition des éléments en saillie 14 et 15 qui consiste à les disposer en forme de triangle ou de trapèze permet d'aménager des sections de passage évolutives telles que le rapport du débit d'air froid résiduel sur l'aire de passage reste sensiblement constant. Il en résulte un meilleur refroidissement des parois de l'aube. Comme représenté aux figures 4 et 5 l'aube comporte des rangées de perforatins 18 sur le bord d'attaque, de perforations 19 sur l'intrados, à proximité du bord d'attaque et à proximité de la cloison interne, de perforations 20 sur l'extrados à proximité du bord d'attaque. Selon une particularité de l'invent.icn, le diamètre de ces perforations est très faible, de l'ordre de 0,3 mm. On adoptera de préférence une disposition en quinconce.This arrangement of the projecting elements 14 and 15 which consists of arranging them in the shape of a triangle or trapezoid makes it possible to arrange scalable passage sections such that the ratio of the flow of residual cold air over the passage area remains substantially constant . This results in better cooling of the walls of the blade. As shown in FIGS. 4 and 5, the blade has rows of perforators 18 on the leading edge, of perforations 19 on the lower surface, near the leading edge and near the internal partition, of perforations 20 on the upper surface near the leading edge. According to a feature of invent.icn, the diameter of these perforations is very small, of the order of 0.3 mm. Preferably a staggered arrangement will be adopted.

Ces deux particularités des perforations apportent en effet des avantages importants sur le plan des échanges thermiques. Le fait de pouvoir loger un maximum de perforations rapprochées sur la surface traitée a pour conséquence que le film se stabilise rapidement, alors que des perforations plus grandes entraîneraient des hétérogénéités dans les échanges. On obtient ainsi un maximum d'efficacité avec un minimum de débit.These two peculiarities of the perforations indeed bring significant advantages in terms of heat exchange. The fact of being able to accommodate a maximum of close perforations on the treated surface has the consequence that the film stabilizes quickly, while larger perforations would lead to heterogeneities in the exchanges. This gives maximum efficiency with minimum flow.

La disposition de la chemise 12 dans la chambre principale est telle qu'elle divise ladite chambre en trois zones A, B, C indépendantes (voir figure 5).The arrangement of the jacket 12 in the main bedroom is such that it divides said bedroom into three independent zones A, B, C (see FIG. 5).

L'air arrive par la tête de la zone A traverse le verrou 17 par les orifices 17a, remplit la zone A', vient au contact du bord d'attaque et s'échappe par les perforations 18. A la partie supérieure l'entrée de la chambre A (figure 5) est plus faible qu'à la base (figure 4) et il en résulte que le nombre de Mach diminue à mesure qu'on se rapproche du pied de l'aube, la pression variant en sens inverse. De cette manière, on équilibre en grande partie l'évolution radiale des températures sur le bord d'attaque.The air arrives through the head of the zone A passes through the latch 17 through the orifices 17a, fills the zone A ', comes into contact from the leading edge and escapes through the perforations 18. At the upper part the entrance to chamber A (figure 5) is lower than at the base (figure 4) and it follows that the Mach number decreases as we get closer to the foot of dawn, the pressure varying in opposite directions. In this way, the radial evolution of temperatures on the leading edge is largely balanced.

L'air qui arrive par la tête 7 de l'aube 2 se répartit aussi d'une part dans la zone B, traverse les ailettes 15 et s'échappe par les perforations 19, et d'autre part dans la zone C, traverse les plots 14 et s'échappe par les perforations 20.The air which arrives through the head 7 of the blade 2 is also distributed on the one hand in zone B, passes through the fins 15 and escapes through the perforations 19, and on the other hand in zone C, passes through the studs 14 and escapes through the perforations 20.

L'espace dans la zone B entre la chemise 12 et les ailettes 15 et dans la zone C entre la chemise 12 et les plots 14 est faible ; ceci permet un nombre de Mach élevé et un faible débit d'alimentation ce qui est favorable au refroidissement par convection.The space in zone B between the sleeve 12 and the fins 15 and in zone C between the sleeve 12 and the studs 14 is small; this allows a high Mach number and a low feed rate which is favorable for convection cooling.

Le coefficient d'échange externe (apport de calories) étant plus fort sur l'extrados que sur l'intrados, on utilise des ailettes sur l'intrados et des plots sur l'extrados.The external exchange coefficient (intake of calories) being stronger on the upper surface than on the lower surface, we use fins on the lower surface and studs on the upper surface.

Ce refroidissement par ailettes est moins efficace mais fournit une perte de charge plus faible.This cooling by fins is less effective but provides a lower pressure drop.

Les plots 14 ont une surface mouillée plus importante et créent une turbulence favorable aux échanges.The pads 14 have a larger wetted surface and create a turbulence favorable to exchanges.

Les zones B d'alimentation des ailettes 15 et C d'alimentation des plots 14 diminuent au fur et à mesure qu'on se rapproche du pied de l'aube. Inversement, la longueur des ailettes ou des rangées de plots augmente, ce qui permet d'équilibrer en grande partie les échanges sur toute la surface de l'aube.The zones B for supplying the fins 15 and C for supplying the studs 14 decrease as one approaches the foot of the dawn. Conversely, the length of the fins or rows of studs increases, which makes it possible to largely balance the exchanges over the entire surface of the blade.

La chambre intermédiaire 9 comporte du côté intrados (figure 2) une partie lisse 21 qui occupe un triangle rectangle dont la base est constituée par la partie supérieure de la chambre et le sommet par le coin inférieur interne. Sur la même paroi côté intrados, il est prévu des rangées de plots 22 venus de fonderie réparties sur un triangle rectangle dont le sommet occupe le coin supérieur aval de la chambre 9.The intermediate chamber 9 comprises on the lower surface side (FIG. 2) a smooth part 21 which occupies a right triangle whose base is constituted by the upper part of the chamber and the top by the internal lower corner. On the same wall on the lower side, rows of studs 22 from the foundry are provided, distributed over a right triangle whose apex occupies the upper downstream corner of the chamber 9.

Du côté extrados, il est prévu quatre nervures longitudinales 23 disposées également suivant une zone en forme de triangle rectangle ; dans l'espace libre des rangées de plots 24 sont réparties en quinconce suivant une zone en forme de triangle rectangle. Il n'y a pas d'émission thermique à l'arrière de l'extrados car, sur le dernier tiers de l'aube, les coefficients d'échange s'inversent (alimentés par la chambre 9).On the upper surface side, four longitudinal ribs 23 are also provided, arranged in an area in the shape of a right triangle; in the free space, rows of studs 24 are staggered in an area in the shape of a right triangle. There is no thermal emission at the rear of the upper surface because, on the last third of dawn, the exchange coefficients reverse (supplied by chamber 9).

Il est donc prévu trois rangées de perforations 25 (figure 4) sur l'intrados qui sont alimentées par la chambre intermédiaire 9. Comme pour les perforations 18, 19, 20, le diamètre des perforations 25 est très faible, de l'ordre de 0,3 mm et une disposition en quinconce est de préférence adoptée.There are therefore three rows of perforations 25 (FIG. 4) on the lower surface which are supplied by the intermediate chamber 9. As for the perforations 18, 19, 20, the diameter of the perforations 25 is very small, of the order of 0.3 mm and a staggered arrangement is preferably adopted.

Les nervures longitudinales 23 et les rangées de plots 24 suffisent au refroidissement de l'extrados. Il faut noter également que, dans cette zone la densité des ailettes diminue et que la densité des plots augmente lorsqu'on se rapproche du pied de l'aube. La chambre intermédiaire 9 débouche dans une rainure 26 (figure 4, 5) occupant toute la longueur du bord de fuite, par des fentes 27 séparées par des pontets 28 venus de fonderie.The longitudinal ribs 23 and the rows of studs 24 are sufficient for cooling the upper surface. It should also be noted that, in this zone, the density of the fins decreases and that the density of the studs increases when one approaches the foot of the dawn. The intermediate chamber 9 opens into a groove 26 (FIG. 4, 5) occupying the entire length of the trailing edge, by slots 27 separated by bridges 28 from the foundry.

Les fentes 27 sont divisées en couloirs 29, 30, 31 délimités par deux rangées de plots 32, 33 solidaires de l'intrados comme de l'extrados.The slots 27 are divided into passages 29, 30, 31 delimited by two rows of studs 32, 33 secured to the lower surface as well as the upper surface.

Bien que l'on ait représenté un verrou 17 constitué par une plaque perforée pour maintenir les bords de la chemise 12 en position d'ouverture, il est également possible de maintenir les plaques ouvertes en engageant les extrémités des plaques 12a et 12b dans des fentes ménagées dans les nervures 16, 16a.Although a latch 17 has been shown consisting of a perforated plate to hold the edges of the jacket 12 in the open position, it is also possible to keep the plates open by engaging the ends of the plates 12a and 12b in slots formed in the ribs 16, 16a.

Bien entendu, la description n'est pas limitative et l'homme de l'art pourra y apporter des modifications sans pour cela sortir du domaine de l'invention.Of course, the description is not limiting and those skilled in the art may make modifications to it without departing from the scope of the invention.

Claims (9)

1. Aube de distributeur de turbine du type comportant au moins une cavité interne dans laquelle une chemise en tôle est maintenue en appui contre les parois par l'intermédiaire d'éléments en saillie, caractérisée en ce que les éléments en saillie (14, 15) contre lesquels la chemise (12) est en appui sont disposés pour les parois d'intrados et d'extrados suivant une zone s'étendant sensiblement sur toute la hauteur et dont la largeur qui est maximale à la base évolue progressivement sur toute la hauteur pour devenir minimale à la partie supérieure, ladite cavité (8) présentant une ouverture (7) à sa partie supérieure par laquelle pénètre le fluide de refroidissement.1. A turbine distributor vane of the type comprising at least one internal cavity in which a sheet metal jacket is held in abutment against the walls by means of projecting elements, characterized in that the projecting elements (14, 15 ) against which the liner (12) is supported are arranged for the lower and upper surfaces in an area extending substantially over the entire height and the width of which is maximum at the base progressively evolves over the entire height to become minimal at the top, said cavity (8) having an opening (7) at its top through which penetrates the cooling fluid. 2. Aube de distributeur de turbine présentant intérieurement une chambre principale s'étendant derrière le bord d'attaque et une chambre intermédiaire séparée par une cloison de la chambre principale et débouchant dans une rainure occupant toute la longueur du bord de fuite suivant la revendication 1, caractérisée en ce que la chambre principale (8) et la chambre auxiliaire (9) comportent sur leurs parois d'intrados et d'extrados des éléments en saillie (14, 15, 22, 23, 24) qui sont disposés suivant des zones triangulaires différentes pour l'intrados et l'extrados.2. Turbine distributor vane having internally a main chamber extending behind the leading edge and an intermediate chamber separated by a partition from the main chamber and opening into a groove occupying the entire length of the trailing edge according to claim 1 , characterized in that the main chamber (8) and the auxiliary chamber (9) have projecting elements (14, 15, 22, 23, 24) on their lower and upper surfaces which are arranged in zones different triangles for the lower and upper surfaces. 3. Aube de distributeur de turbine suivant les revendications 1 et 2, caractérisée en ce que la chemise (12) prend appui côté extrados sur des plots (14) et côté intrados sur des ailettes (15).3. Turbine distributor blade according to claims 1 and 2, characterized in that the jacket (12) bears on the upper side on the studs (14) and on the lower side on the fins (15). 4. Aube de distributeur de turbine suivant les revendications 1 et 2, caractérisée en ce que la chemise (12)' en forme de U est constituée de deux plaques dont l'une (12a) s'étend sur toute la largeur de la chambre principale (8) et dont l'autre (12b) qui est fixée sur la première s'étend sensiblement suivant la largeur des éléments en saillie (15) contre lesquels elle est en appui.4. Turbine distributor blade according to claims 1 and 2, characterized in that the jacket (12) ' U-shaped consists of two plates, one of which (12a) extends over the entire width of the chamber main (8) and the other (12b) which is fixed on the first extends substantially along the width of the projecting elements (15) against which it is supported. 5. Aube de distributeur de turbine suivant l'une quelconque des revendications 1, 2 et 4, caractérisée en ce que la chemise ouverte (12) est en appui de façon étanche par l'une de ses plaques (12a) contre la cloison centrale (13) et elle est en appui par ses deux plaques (12a, 12b) contre les parois d'intrados et d'extrados sous l'action d'un verrou longitudinal (17) engagé dans des rainures prévues dans les bords des deux plaques (12a, 12b) de la chemise, ledit verrou étant constitué par une plaque (17) présentant des ouvertures (17a) débouchant en direction du bord d'attaque de telle sorte que la chemise (12) sépare la chambre principale (8) en trois zones (A, B, C) d'alimentation indépendantes.5. Turbine distributor blade according to any one of claims 1, 2 and 4, characterized in that the open jacket (12) is sealingly supported by one of its plates (12a) against the central partition (13) and it is supported by its two plates (12a, 12b) against the lower and upper surfaces under the action of a longitudinal lock (17) engaged in grooves provided in the edges of the two plates (12a, 12b) of the jacket, said latch being constituted by a plate (17) having openings (17a) opening towards the leading edge so that the jacket (12) separates the main chamber (8) in three independent feeding zones (A, B, C). 6. Aube de distributeur de turbine suivant la revendication 5, caractérisée en ce que l'aube comporte des rangées de perforations (18) sur le bord d'attaque (11), des rangées de perforations (19) sur l'intrados à proximité du bord d'attaque et à proximité de la cloison interne (13), des rangées de perforations (20) sur l'extrados à proximité du bord d'attaque.6. Turbine distributor vane according to claim 5, characterized in that the blade has rows of perforations (18) on the leading edge (11), rows of perforations (19) on the intrados nearby from the leading edge and near the internal partition (13), rows of perforations (20) on the upper surface near the leading edge. 7. Aube de distributeur de turbine suivant la revendication 6, caractérisée en ce que les rangées de perforations (18, 19, 20) sont décalées de manière à réaliser une disposition en quinconce, le diamètre des perforations étant de l'ordre de 0,3 mm.7. A turbine distributor blade according to claim 6, characterized in that the rows of perforations (18, 19, 20) are offset so as to make a staggered arrangement, the diameter of the perforations being of the order of 0, 3 mm. 8. Aube de distributeur de turbine suivant la revendication 2, caractérisée en ce que la chambre intermédiaire (9) débouche dans la rainure (26) occupant toute la longueur du bord de fuite par des fentes (27) séparées par des pontets (28),chacune des fentes (26) étant divisées en couloirs (29, 30, 31) délimités par des rangées de plots (32, 33) solidaires de l'intrados et de l'extrados.8. A turbine distributor blade according to claim 2, characterized in that the intermediate chamber (9) opens into the groove (26) occupying the entire length of the trailing edge by slots (27) separated by bridges (28) , each of the slots (26) being divided into passages (29, 30, 31) delimited by rows of studs (32, 33) integral with the lower surface and the upper surface. 9. Aube de distributeur de turbine suivant les revendications 1 et 4, caractérisée en ce que les extrémités des deux plaques de la chemise (12) sont engagées dans des fentes ménagées dans des nervures prévues sur les faces internes de l'extrados et de l'intrados.9. A turbine distributor blade according to claims 1 and 4, characterized in that the ends of the two plates of the jacket (12) are engaged in slots made in ribs provided on the inner faces of the upper surface and of the '' lower surface.
EP80401849A 1980-01-10 1980-12-23 Turbine guide vane Expired EP0032646B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8000458 1980-01-10
FR8000458A FR2473621A1 (en) 1980-01-10 1980-01-10 DAWN OF TURBINE DISPENSER

Publications (2)

Publication Number Publication Date
EP0032646A1 true EP0032646A1 (en) 1981-07-29
EP0032646B1 EP0032646B1 (en) 1984-06-13

Family

ID=9237402

Family Applications (1)

Application Number Title Priority Date Filing Date
EP80401849A Expired EP0032646B1 (en) 1980-01-10 1980-12-23 Turbine guide vane

Country Status (5)

Country Link
US (1) US4403917A (en)
EP (1) EP0032646B1 (en)
JP (1) JPS56138403A (en)
DE (1) DE3068276D1 (en)
FR (1) FR2473621A1 (en)

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Cited By (10)

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GB2119028A (en) * 1982-04-27 1983-11-09 Rolls Royce Aerofoil for a gas turbine engine
EP0140257A1 (en) * 1983-10-28 1985-05-08 Westinghouse Electric Corporation Cooling arrangement for airfoil stator vane trailing edge
FR2653171A1 (en) * 1989-10-18 1991-04-19 Snecma TURBOMACHINE COMPRESSOR CASING PROVIDED WITH A DEVICE FOR DRIVING ITS INTERNAL DIAMETER.
EP0424253A1 (en) * 1989-10-18 1991-04-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbomachine compressor casing with device for controlling its internal diameter
GB2261032A (en) * 1991-08-23 1993-05-05 Mitsubishi Heavy Ind Ltd Gas turbine blade with skin and core construction
GB2261032B (en) * 1991-08-23 1995-04-05 Mitsubishi Heavy Ind Ltd Rotor blade for a gas turbine
EP1849960A2 (en) * 2006-04-27 2007-10-31 Hitachi, Ltd. Turbine blade having internal cooling passage
EP1849960A3 (en) * 2006-04-27 2010-03-10 Hitachi, Ltd. Turbine blade having internal cooling passage
EP3023586A1 (en) * 2014-11-21 2016-05-25 Siemens Aktiengesellschaft Hollow blade body, inserted fin and hollow blade
WO2016078851A1 (en) * 2014-11-21 2016-05-26 Siemens Aktiengesellschaft Hollow blade body, insertion rib, and hollow blade

Also Published As

Publication number Publication date
FR2473621B1 (en) 1983-05-13
JPS6148609B2 (en) 1986-10-24
JPS56138403A (en) 1981-10-29
FR2473621A1 (en) 1981-07-17
US4403917A (en) 1983-09-13
DE3068276D1 (en) 1984-07-19
EP0032646B1 (en) 1984-06-13

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