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EP3587743A1 - Cooling device for a turbine-engine housing - Google Patents

Cooling device for a turbine-engine housing Download PDF

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Publication number
EP3587743A1
EP3587743A1 EP19182042.2A EP19182042A EP3587743A1 EP 3587743 A1 EP3587743 A1 EP 3587743A1 EP 19182042 A EP19182042 A EP 19182042A EP 3587743 A1 EP3587743 A1 EP 3587743A1
Authority
EP
European Patent Office
Prior art keywords
casing
sheet
edges
turbomachine
reliefs
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
EP19182042.2A
Other languages
German (de)
French (fr)
Other versions
EP3587743B1 (en
Inventor
Jacques Marcel Arthur Bunel
Etienne Gérard Joseph CANELLE
Emeric Christian Amaury D'herbigny
Pierrick Bernard Jean
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
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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3587743A1 publication Critical patent/EP3587743A1/en
Application granted granted Critical
Publication of EP3587743B1 publication Critical patent/EP3587743B1/en
Active 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium

Definitions

  • the subject of the invention is a device for cooling a turbomachine casing by a flow of gas.
  • a widely used method for adjusting the clearances in turbomachines, between the fixed and movable vanes on the one hand, the rotor and the stator to which they are fixed on the other hand, consists in blowing a flow of fresh gas on the stator casing to produce a thermal shrinkage of its diameter.
  • the flow is generally a small part of the flow of gases from the vein of the turbomachine, which is drawn off in compressors where the gas is at high pressure and still fresh, which is allowed to circulate in conduits along the vein and that we blow on the much hotter turbines of the machine.
  • the device traditionally comprises annular ramps surrounding the stator casing at a distance from it and provided with blowing orifices directed towards the casing.
  • the document US 6,149,074 A describes such a cooling device.
  • a device in which the ramps are assembled to the housing is the subject of the document EP 2236772 A2 .
  • the ramps are composed of an inner sheet provided with the blowing orifices, an outer sheet delimiting a blowing chamber with the inner sheet, and an intermediate sheet allowing an equalization of the air flows towards the blowing orifices. These sheets are provided with overlapping flanges and screwed to retaining tabs on the housing.
  • the structure is relatively complex, and positional faults, sufficiently large in this area where very high precision is desired, risk appearing in the absence of special precautions during assembly.
  • a device for cooling a turbomachine revolution casing by a gas flow comprising: a sheet metal surrounding a circular band of the casing, having edges fixed to the casing and a foraminated main part parallel to the casing , the sheet and the casing defining a gas blowing chamber provided with discharge openings; a collecting box surrounding the sheet, and delimiting with the sheet a gas distribution chamber by covering the main part of the sheet; a gas supply capacity remote from the housing; and at least one connection conduit connecting the capacitor to the housing; and the device is characterized in that the position of the sheet on the casing is ensured by protruding reliefs from the latter, to serve as supports or stops at the edges of the sheet; and that the reliefs provide a stop in axial direction of the casing at a first of the edges of the sheet and a support in radial direction of the casing at a second of the edges of the sheet.
  • the invention is therefore mainly based on the connection to the housing of the end of the blowing device, that is to say the sheet through which the gas is blown, which is parallel to the housing and kept at a constant distance and well determined from the housing, thanks to the two abutment supports obtained in perpendicular directions.
  • the geometrical blowing conditions thus remain uniform whatever the operating evolutions of the machine and the deformations undergone by the various parts, which do not affect this roughly non-deformable junction of the casing and of the end of the blowing device.
  • the protruding reliefs on the casing can be provided with discharge openings.
  • the manifold housing includes edges respectively parallel to the edges of the sheet and placed on them; this arrangement, especially if the sheet includes a first essentially planar edge and a second edge essentially perpendicular to the first edge, makes it easy to assemble the manifold housing to the sheet.
  • the connector is bent and sliding through a wall of the housing, a wall of the capacity or both, which makes it possible to compensate for differential expansions in the directions of the sliding movement, or possibly any direction.
  • Another aspect of the invention is a turbomachine comprising such a cooling device, the sheet then advantageously being able to be located around a portion of the casing which is provided with a circular rib.
  • the cooling device can also comprise a plurality of sheets and manifold boxes respectively associated with the sheets, the sheets and boxes form successive rings around the casing in the axial direction of the casing.
  • a turbomachine turbine comprises a casing 1 around an axial direction X.
  • the casing 1 comprises a skin 2 of conical shape regularly reinforced by circular ribs 3 and which therefore define more rigid annular portions of the casing 1.
  • a cooling device comprises rings 4 surrounding the casing 1, resting on circular strips of the skin 2 and preferably mounted in front of the ribs 3.
  • the rings 4 are connected to a fresh gas capacity, here an air supply box 5, which extends some distance from them, by fittings 6 having a bent shape.
  • the figure 2 represents in detail one of the rings 4 of the device. It comprises a sheet 7 of annular and conical shape, unitary in the axial direction X (possibly composed of angular sectors assembled together) placed on the skin 2 while being mounted around it and a collecting box 8 covering the sheet 7.
  • the figure 3 shows that the sheet 7 comprises a main part 9, foraminated (crossed by multiple bores) and two lateral edges 10 and 11.
  • the sheet 7 has the same conicity as the portion of the skin 2 on which it extends, so that the main part 9 is parallel to the skin 2 and separated from it by a blowing chamber 12 with a constant depth of a few millimeters (for example 2 millimeters).
  • a first lateral edge 10 is essentially plane and extends perpendicular to the axial direction X , while the second lateral edge 11 (at a larger diameter of the sheet 7) is essentially cylindrical.
  • Skin 2 ( figure 4 ) is provided with two rigid reliefs 13 and 14, annular and protrusions in the form of ribs, intended to receive the lateral edges 10 and 11 respectively to establish support or stop states.
  • the first lateral edge 10 abuts against a lateral face of the relief 13 which is plane and oriented in the axial direction X, while the second lateral edge 11 is supported on an outer face, cylindrical and of the same diameter as it and oriented in the direction radial R, of the other relief 14.
  • the latter is provided with evacuation slots 15 regularly distributed over its circumference to allow the evacuation of the blowing chamber 12.
  • the collecting box 8 is also of annular shape and comprises ( figure 5 ) a first lateral edge 16 plane perpendicular to the axial direction X and a second lateral edge 17, opposite, directed in this axial direction X and cylindrical or slightly conical.
  • the side edges 16 and 17 respectively have the same directions as the side edges 10 and 11 of the sheet 7, and they can be placed on them and fixed to them by soldering, welding or otherwise.
  • the lateral edges 10 and 11 of the sheet 7 are likewise fixed to the reliefs 13 and 14 by brazing, welding or otherwise.
  • the manifold housing 8 is also formed of a continuous sheet between the lateral edges 16 and 17, which is curved outward in the radial direction R and opens only on the inner radial side, at the place where the manifold housing 8 covers the main part 9 of the sheet 7. The latter therefore separates the blowing chamber 12 from a distribution chamber 18 located radially to it externally and delimited by the manifold housing 8.
  • the wall of the manifold housing 8 is however pierced at the location of the connector 6.
  • the latter passes through it through an axial branch 19 and is connected to the supply housing 5 by crossing its wall by another oblique branch 20 separated from the previous by a bend 21.
  • the ends of the branches 19 and 20 penetrate into the collecting box 8 and the supply box 5 by junctions which allow them to slide through their walls, in order to accommodate the device at variations in positions, due for example to thermal expansion in the machine, in particular between the casing 1 and the power supply unit 5.
  • connection 6 has been shown between the power supply unit 5 and each of the rings 4.
  • connections 6 could be provided for each of the rings 4, distributed around their circumference. It would then be advisable to compartmentalize the interior of the manifold boxes 8 by partitions, in order to ensure equal flows therein.
  • the supply unit 5, common to all the connections 6, is connected to the compressor of the machine, or possibly to another source of compressed air, by a pipe 22 which has only been outlined here.
  • compressed air withdrawn from the compressors arrives in the supply box 5 through the pipe 22, then is distributed by the fittings 6 in the manifold boxes 8 and is distributed in angular direction in their distribution chambers 18, then passes through the sheets 7 through their holes to enter the blowing chambers and lick the skin 2 at the location of the stiffeners 3, before being discharged outside through the slots 15.
  • the uniform depth of the blowing chambers 12 guarantees that the air flows lick each portion of the skin 2 invariably, which makes it possible to predict the thermal retractions that are imposed with good precision.
  • the value of the flow rate can conventionally be adjusted by a valve placed for example on the pipe 22.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La rétraction thermique d'un carter (2) pour régler au mieux les jeux intérieurs entre le rotor et le stator est effectuée par un anneau (4) fixé sur la peau (2) plutôt que par une rampe circulaire à distance de lui. L'anneau (4) comprend, entre un boîtier collecteur (8) et la peau (2), une tôle (7) foraminée, placée sur une ouverture du boîtier (8) parallèlement à la peau (2) et à petite distance, afin d'imposer des conditions de ventilations invariables et connues.The thermal shrinkage of a casing (2) to best adjust the internal clearances between the rotor and the stator is carried out by a ring (4) fixed on the skin (2) rather than by a circular ramp remote from it. The ring (4) comprises, between a collecting box (8) and the skin (2), a foraminous sheet (7), placed on an opening of the box (8) parallel to the skin (2) and at a small distance, in order to impose invariable and known ventilation conditions.

Description

Le sujet de l'invention est un dispositif de refroidissement d'un carter de turbomachine par un écoulement de gaz.The subject of the invention is a device for cooling a turbomachine casing by a flow of gas.

Un procédé très employé pour régler les jeux dans les turbomachines, entre les aubes fixes et mobiles d'une part, le rotor et le stator auxquels elles sont fixées d'autre part, consiste à souffler un écoulement de gaz frais sur le carter du stator pour produire une rétraction thermique de son diamètre. L'écoulement est généralement une petite partie de l'écoulement des gaz de la veine de la turbomachine, qu'on soutire aux compresseurs où le gaz est à haute pression et encore frais, qu'on laisse circuler dans des conduits longeant la veine et qu'on souffle sur les turbines beaucoup plus chaudes, de la machine. Le dispositif comprend traditionnellement des rampes annulaires entourant le carter du stator à distance de lui et pourvues d'orifices de soufflage dirigés vers le carter. Le document US 6 149 074 A décrit un tel dispositif de refroidissement.A widely used method for adjusting the clearances in turbomachines, between the fixed and movable vanes on the one hand, the rotor and the stator to which they are fixed on the other hand, consists in blowing a flow of fresh gas on the stator casing to produce a thermal shrinkage of its diameter. The flow is generally a small part of the flow of gases from the vein of the turbomachine, which is drawn off in compressors where the gas is at high pressure and still fresh, which is allowed to circulate in conduits along the vein and that we blow on the much hotter turbines of the machine. The device traditionally comprises annular ramps surrounding the stator casing at a distance from it and provided with blowing orifices directed towards the casing. The document US 6,149,074 A describes such a cooling device.

Un inconvénient de ce dispositif est un manque de précision. La position de la rampe ne peut pas toujours être maintenue optimale en raison des déformations, notamment des dilatations thermiques différentielles dues à des échauffements différents, subies par la machine au cours du fonctionnement et des tolérances de fabrication du dispositif de soufflage comprenant les rampes. Ces déformations et dilatations différentielles peuvent revenir à déplacer les rampes aussi bien en direction axiale qu'en direction radiale du carter, d'autant plus que celui-ci est généralement conique. Les rampes peuvent ainsi se trouver à côté des endroits du carter qui étaient supposés subir le soufflage (normalement les parties les plus rigides, autour des nervures circulaires qui le raidissent, et qui détermine bien ces dimensions), et leur distance au carter peut aussi être déréglée, et même disparaître dans certaines situations. Or, une très grande précision de position est nécessaire pour obtenir une bonne qualité de réglage des jeux dans les moteurs contemporains, et des erreurs de position ou des déplacements de l'ordre du millimètre peuvent compromettre la qualité du soufflage. Et si le carter entre en contact avec les rampes, elles peuvent éclater s'il se dilate davantage.One drawback of this device is a lack of precision. The position of the ramp cannot always be maintained optimal due to deformations, in particular differential thermal expansions due to different overheating, undergone by the machine during operation and the manufacturing tolerances of the blowing device comprising the ramps. These deformations and differential expansions can amount to displacing the ramps both in the axial direction and in the radial direction of the casing, all the more so since the latter is generally conical. The ramps can thus be located near the places of the casing which were supposed to undergo blowing (normally the most rigid parts, around the circular ribs which stiffen it, and which well determines these dimensions), and their distance from the casing can also be deregulated, and even disappear in certain situations. However, very high position accuracy is necessary to obtain a good quality of clearance adjustment in contemporary engines, and position errors or displacements of the order of millimeter can compromise the quality of the blowing. And if the housing comes into contact with the ramps, they may burst if it expands further.

Les inconvénients d'erreurs de position au montage du dispositif sur le carter ou pendant le fonctionnement peuvent être réduits si les rampes sont unies au carter par des dispositifs de liaison, au lieu d'être complètement séparées de lui dans le brevet mentionné ci-dessus, mais les déformations et dilatations thermiques différentielles contraignent fortement alors l'assemblage, et des ruptures sont aussi possibles.The disadvantages of position errors when mounting the device on the housing or during operation can be reduced if the ramps are joined to the housing by connecting devices, instead of being completely separated from it in the patent mentioned above , but the differential thermal distortions and expansions strongly constrain the assembly, and ruptures are also possible.

Le maintien des rampes de refroidissement par soufflage à une position bien définie, aussi bien axiale que radiale, par rapport au carter qui subit le soufflage d'air n'est donc pas résolu de façon satisfaisante aujourd'hui.Maintaining the blast cooling ramps in a well-defined position, both axially and radially, with respect to the casing which is subjected to the blowing of air is therefore not satisfactorily resolved today.

Un dispositif dans lequel les rampes sont assemblées au carter est le sujet du document EP 2236772 A2 . Les rampes sont composées d'une tôle intérieure munie des orifices de soufflage, d'une tôle extérieure délimitant une chambre de soufflage avec la tôle intérieure, et d'une tôle intermédiaire permettant une égalisation des flux d'air vers les orifices de soufflage. Ces tôles sont munies de rebords superposés et vissés à des pattes de maintien sur le carter. La structure est relativement complexe, et des défauts de position, suffisamment importants dans ce domaine où une très grande précision est souhaitée, risquent d'apparaître en l'absence de précautions particulières au montage.A device in which the ramps are assembled to the housing is the subject of the document EP 2236772 A2 . The ramps are composed of an inner sheet provided with the blowing orifices, an outer sheet delimiting a blowing chamber with the inner sheet, and an intermediate sheet allowing an equalization of the air flows towards the blowing orifices. These sheets are provided with overlapping flanges and screwed to retaining tabs on the housing. The structure is relatively complex, and positional faults, sufficiently large in this area where very high precision is desired, risk appearing in the absence of special precautions during assembly.

C'est pour obvier à cet inconvénient d'imprécision du refroidissement que l'invention fut conçue. Sous une forme générale, elle concerne un dispositif de refroidissement d'un carter de révolution de turbomachine par un écoulement de gaz, comprenant : une tôle entourant une bande circulaire du carter, ayant des bords fixés au carter et une partie principale foraminée parallèle au carter, la tôle et le carter délimitant une chambre de soufflage de gaz dotée d'ouvertures d'évacuation ; un boîtier collecteur entourant la tôle, et délimitant avec la tôle une chambre de distribution de gaz en coiffant la partie principale de la tôle ; une capacité d'alimentation en gaz à distance du boîtier ; et au moins un conduit de raccord reliant la capacité au boîtier ; et le dispositif est caractérisé en ce que La position de la tôle sur le carter est assurée par des reliefs saillant de ce dernier, pour servir d'appuis ou de butées aux bords de la tôle ; et que les reliefs procurent une butée en direction axiale du carter à un premier des bords de la tôle et un appui en direction radiale du carter à un second des bords de la tôle.It is to overcome this drawback of imprecision of cooling that the invention was conceived. In general form, it relates to a device for cooling a turbomachine revolution casing by a gas flow, comprising: a sheet metal surrounding a circular band of the casing, having edges fixed to the casing and a foraminated main part parallel to the casing , the sheet and the casing defining a gas blowing chamber provided with discharge openings; a collecting box surrounding the sheet, and delimiting with the sheet a gas distribution chamber by covering the main part of the sheet; a gas supply capacity remote from the housing; and at least one connection conduit connecting the capacitor to the housing; and the device is characterized in that the position of the sheet on the casing is ensured by protruding reliefs from the latter, to serve as supports or stops at the edges of the sheet; and that the reliefs provide a stop in axial direction of the casing at a first of the edges of the sheet and a support in radial direction of the casing at a second of the edges of the sheet.

L'invention repose donc principalement sur la liaison au carter de l'extrémité du dispositif de soufflage, c'est-à-dire la tôle à travers laquelle le gaz est soufflé, qui est parallèle au carter et maintenue à une distance constante et bien déterminée du carter, grâce aux deux appuis de butée obtenues dans des directions perpendiculaires. Les conditions géométriques de soufflage restent ainsi uniformes quelles que soient les évolutions de fonctionnement de la machine et les déformations subies par les différentes pièces, qui n'affectent pas cette jonction à peu près indéformable du carter et de l'extrémité du dispositif de soufflage.The invention is therefore mainly based on the connection to the housing of the end of the blowing device, that is to say the sheet through which the gas is blown, which is parallel to the housing and kept at a constant distance and well determined from the housing, thanks to the two abutment supports obtained in perpendicular directions. The geometrical blowing conditions thus remain uniform whatever the operating evolutions of the machine and the deformations undergone by the various parts, which do not affect this roughly non-deformable junction of the casing and of the end of the blowing device.

Les reliefs saillants sur le carter peuvent être munis d'ouvertures d'évacuation.The protruding reliefs on the casing can be provided with discharge openings.

Dans une variante préférée de réalisation, le boîtier collecteur comprend des bords respectivement parallèles aux bords de la tôle et posés sur eux ; cette disposition, surtout si la tôle comprend un premier bord essentiellement plan et un second bord essentiellement perpendiculaire au premier bord, permet d'assemblerfacilement le boîtier collecteur à la tôle.In a preferred embodiment, the manifold housing includes edges respectively parallel to the edges of the sheet and placed on them; this arrangement, especially if the sheet includes a first essentially planar edge and a second edge essentially perpendicular to the first edge, makes it easy to assemble the manifold housing to the sheet.

Selon une disposition préférée, le raccord est coudé et coulissant à travers une paroi du boîtier, une paroi de la capacité ou les deux, ce qui permet de compenser des dilatations différentielles dans les directions du mouvement coulissant, ou éventuellement toute direction.According to a preferred arrangement, the connector is bent and sliding through a wall of the housing, a wall of the capacity or both, which makes it possible to compensate for differential expansions in the directions of the sliding movement, or possibly any direction.

Un autre aspect de l'invention est une turbomachine comprenant un tel dispositif de refroidissement, la tôle pouvant alors avantageusement être située autour d'une portion du carter qui est pourvue d'une nervure circulaire. Le dispositif de refroidissement peut encore comprendre une pluralité de tôles et de boîtiers collecteurs respectivement associés aux tôles, les tôles et boîtiers forment des anneaux se succédant autour du carter en direction axiale du carter.Another aspect of the invention is a turbomachine comprising such a cooling device, the sheet then advantageously being able to be located around a portion of the casing which is provided with a circular rib. The cooling device can also comprise a plurality of sheets and manifold boxes respectively associated with the sheets, the sheets and boxes form successive rings around the casing in the axial direction of the casing.

Les différents aspects, caractéristiques et avantages de l'invention seront maintenant décrits en détail en liaison aux figures suivantes, qui en représentent un mode de réalisation préféré, donné à titre purement illustratif :

  • la figure 1 est une vue d'ensemble du dispositif en coupe longitudinale de la machine ;
  • la figure 2 est en agrandissement d'une unité du dispositif ;
  • la figure 3 illustre la tôle foraminée ;
  • la figure 4 illustre le carter ;
  • la figure 5 illustre le boîtier collecteur ;
  • et la figure 6 illustre l'écoulement de soufflage.
The various aspects, characteristics and advantages of the invention will now be described in detail in connection with the following figures, which represent a preferred embodiment thereof, given purely by way of illustration:
  • the figure 1 is an overview of the device in longitudinal section of the machine;
  • the figure 2 is enlarging one unit of the device;
  • the figure 3 illustrates foraminous sheet;
  • the figure 4 illustrates the housing;
  • the figure 5 illustrates the manifold;
  • and the figure 6 illustrates the blowing flow.

Une vue générale du dispositif et de son environnement est donnée à la figure 1. Une turbine de turbomachine comprend un carter 1 autour d'une direction axiale X. Le carter 1 comprend une peau 2 de forme conique régulièrement renforcée par des nervures 3 circulaires et qui définissent donc des portions annulaires plus rigides du carter 1. Un dispositif de refroidissement comprend des anneaux 4 entourant le carter 1, s'appuyant sur des bandes circulaires de la peau 2 et montés de préférence devant les nervures 3. Les anneaux 4 sont reliés à une capacité de gaz frais, ici un boîtier d'alimentation d'air 5, qui s'étend à quelque distance d'eux, par des raccords 6 ayant une forme coudée.A general view of the device and its environment is given in the figure 1 . A turbomachine turbine comprises a casing 1 around an axial direction X. The casing 1 comprises a skin 2 of conical shape regularly reinforced by circular ribs 3 and which therefore define more rigid annular portions of the casing 1. A cooling device comprises rings 4 surrounding the casing 1, resting on circular strips of the skin 2 and preferably mounted in front of the ribs 3. The rings 4 are connected to a fresh gas capacity, here an air supply box 5, which extends some distance from them, by fittings 6 having a bent shape.

La figure 2 représente en détail un des anneaux 4 du dispositif. Il comprend une tôle 7 de forme annulaire et conique, unitaire dans la direction axiale X (éventuellement composée de secteurs angulaires assemblés entre eux) posée sur la peau 2 en étant montée autour d'elle et un boîtier collecteur 8 coiffant la tôle 7. La figure 3 montre que la tôle 7 comprend une partie principale 9, foraminée (traversée de perçages multiples) et de deux bords latéraux 10 et 11. La tôle 7 a la même conicité que la portion de la peau 2 sur laquelle elle s'étend, de sorte que la partie principale 9 est parallèle à la peau 2 et séparée d'elle par une chambre de soufflage 12 d'une profondeur constante de quelques millimètres (par exemple 2 millimètres). Elle est supposée rester rigide pendant l'assemblage et le fonctionnement, pour maintenir cette profondeur invariable et uniforme sur toute l'étendue de la chambre de soufflage 12. Un premier bord latéral 10 est essentiellement plan et s'étend perpendiculairement à la direction axiale X, alors que le second bord latéral 11 (à un plus grand diamètre de la tôle 7) est essentiellement cylindrique. La peau 2 (figure 4) est munie de deux reliefs 13 et 14 rigides, annulaires et saillants en forme de nervures, destinés à recevoir respectivement les bords latéraux 10 et 11 pour établir des états d'appui ou de butée. Le premier bord latéral 10 bute contre une face latérale du relief 13 qui est plane et orientée dans la direction axiale X, alors que le second bord latéral 11 s'appuie sur une face extérieure, cylindrique et de même diamètre que lui et orientée en direction radiale R, de l'autre relief 14. Ce dernier est muni de fentes d'évacuation 15 régulièrement réparties sur sa circonférence pour permettre l'évacuation de la chambre de soufflage 12. Le boîtier collecteur 8 est également de forme annulaire et comprend (figure 5) un premier bord latéral 16 plan perpendiculaire à la direction axiale X et un second bord latéral 17, opposé, dirigé dans cette direction axiale X et cylindrique ou légèrement conique. Les bords latéraux 16 et 17 ont respectivement les mêmes directions que les bords latéraux 10 et 11 de la tôle 7, et ils peuvent être posés sur eux et fixés à eux par brasage, soudage ou autrement. Les bords latéraux 10 et 11 de la tôle 7 sont de même fixés aux reliefs 13 et 14 par brasage, soudage ou autrement. Les appuis ou butées dans des directions essentiellement perpendiculaires entre les bords 10 et 11 de la tôle 7 d'une part, les reliefs 13 et 14 ou les bords 16 et 17 du boîtier collecteur d'autre part, offrent un montage simple à établir et peu contraint mécaniquement. Le boîtier collecteur 8 est par ailleurs formé d'une tôle continue entre les bords latéraux 16 et 17, qui est bombée vers l'extérieur en direction radiale R et s'ouvre seulement du côté radial intérieur, à l'endroit où le boîtier collecteur 8 coiffe la partie principale 9 de la tôle 7. Cette dernière sépare donc la chambre de soufflage 12 d'une chambre de distribution 18 située extérieurement radialement à elle et délimitée par le boîtier collecteur 8.The figure 2 represents in detail one of the rings 4 of the device. It comprises a sheet 7 of annular and conical shape, unitary in the axial direction X (possibly composed of angular sectors assembled together) placed on the skin 2 while being mounted around it and a collecting box 8 covering the sheet 7. The figure 3 shows that the sheet 7 comprises a main part 9, foraminated (crossed by multiple bores) and two lateral edges 10 and 11. The sheet 7 has the same conicity as the portion of the skin 2 on which it extends, so that the main part 9 is parallel to the skin 2 and separated from it by a blowing chamber 12 with a constant depth of a few millimeters (for example 2 millimeters). It is supposed to remain rigid during assembly and operation, to maintain this invariable and uniform depth over the entire extent of the blowing chamber 12. A first lateral edge 10 is essentially plane and extends perpendicular to the axial direction X , while the second lateral edge 11 (at a larger diameter of the sheet 7) is essentially cylindrical. Skin 2 ( figure 4 ) is provided with two rigid reliefs 13 and 14, annular and protrusions in the form of ribs, intended to receive the lateral edges 10 and 11 respectively to establish support or stop states. The first lateral edge 10 abuts against a lateral face of the relief 13 which is plane and oriented in the axial direction X, while the second lateral edge 11 is supported on an outer face, cylindrical and of the same diameter as it and oriented in the direction radial R, of the other relief 14. The latter is provided with evacuation slots 15 regularly distributed over its circumference to allow the evacuation of the blowing chamber 12. The collecting box 8 is also of annular shape and comprises ( figure 5 ) a first lateral edge 16 plane perpendicular to the axial direction X and a second lateral edge 17, opposite, directed in this axial direction X and cylindrical or slightly conical. The side edges 16 and 17 respectively have the same directions as the side edges 10 and 11 of the sheet 7, and they can be placed on them and fixed to them by soldering, welding or otherwise. The lateral edges 10 and 11 of the sheet 7 are likewise fixed to the reliefs 13 and 14 by brazing, welding or otherwise. The supports or stops in essentially perpendicular directions between the edges 10 and 11 of the sheet metal 7 on the one hand, the reliefs 13 and 14 or the edges 16 and 17 of the manifold housing on the other hand, offer a mounting that is simple to establish and little mechanical stress. The manifold housing 8 is also formed of a continuous sheet between the lateral edges 16 and 17, which is curved outward in the radial direction R and opens only on the inner radial side, at the place where the manifold housing 8 covers the main part 9 of the sheet 7. The latter therefore separates the blowing chamber 12 from a distribution chamber 18 located radially to it externally and delimited by the manifold housing 8.

La paroi du boîtier collecteur 8 est toutefois percée à l'endroit du raccord 6. Celui-ci la traverse par une branche 19 axiale et se raccorde au boîtier d'alimentation 5 en traversant sa paroi par une autre branche 20 oblique et séparée de la précédente par un coude 21. Il est avantageux que les extrémités des branches 19 et 20 pénètrent dans le boîtier collecteur 8 et le boîtier d'alimentation 5 par des jonctions qui permettent de coulisser à travers leurs parois, afin d'accommoder le dispositif à des variations de positions, dues par exemple aux dilatations thermiques dans la machine, en particulier entre le carter 1 et le boîtier d'alimentation 5.The wall of the manifold housing 8 is however pierced at the location of the connector 6. The latter passes through it through an axial branch 19 and is connected to the supply housing 5 by crossing its wall by another oblique branch 20 separated from the previous by a bend 21. It is advantageous that the ends of the branches 19 and 20 penetrate into the collecting box 8 and the supply box 5 by junctions which allow them to slide through their walls, in order to accommodate the device at variations in positions, due for example to thermal expansion in the machine, in particular between the casing 1 and the power supply unit 5.

On a représenté un seul raccord 6 entre le boîtier d'alimentation 5 et chacun des anneaux 4. Plusieurs raccords 6 pourraient être prévus pour chacun des anneaux 4, répartis autour de leur circonférence. Il serait alors indiqué de compartimenter l'intérieur des boîtiers collecteurs 8 par des cloisons, afin d'y assurer des écoulements égaux. Le boîtier d'alimentation 5, commun à tous les raccords 6, est relié au compresseur de la machine, où éventuellement à une autre source d'air comprimé, par une canalisation 22 qu'on a seulement ébauchée ici.A single connection 6 has been shown between the power supply unit 5 and each of the rings 4. Several connections 6 could be provided for each of the rings 4, distributed around their circumference. It would then be advisable to compartmentalize the interior of the manifold boxes 8 by partitions, in order to ensure equal flows therein. The supply unit 5, common to all the connections 6, is connected to the compressor of the machine, or possibly to another source of compressed air, by a pipe 22 which has only been outlined here.

En fonctionnement (figure 6), de l'air comprimé soutiré des compresseurs arrive dans le boîtier d'alimentation 5 par la canalisation 22, puis est distribué par les raccords 6 dans les boîtiers collecteurs 8 et se répartit en direction angulaire dans leurs chambres de distribution 18, puis franchit les tôles 7 par leurs perçages pour entrer dans les chambres de soufflage et lécher la peau 2 à l'endroit des raidisseurs 3, avant d'être évacué à l'extérieur par les fentes 15. La profondeur uniforme des chambres de soufflage 12 garantit que les débits d'air lèchent chaque portion de la peau 2 de façon invariable, ce qui permet de prévoir les rétractions thermiques qu'on impose avec une bonne précision. La valeur du débit peut classiquement être réglée par une vanne placée par exemple sur la canalisation 22.Operating ( figure 6 ), compressed air withdrawn from the compressors arrives in the supply box 5 through the pipe 22, then is distributed by the fittings 6 in the manifold boxes 8 and is distributed in angular direction in their distribution chambers 18, then passes through the sheets 7 through their holes to enter the blowing chambers and lick the skin 2 at the location of the stiffeners 3, before being discharged outside through the slots 15. The uniform depth of the blowing chambers 12 guarantees that the air flows lick each portion of the skin 2 invariably, which makes it possible to predict the thermal retractions that are imposed with good precision. The value of the flow rate can conventionally be adjusted by a valve placed for example on the pipe 22.

Claims (8)

Dispositif de refroidissement d'un carter de révolution de turbomachine par un écoulement de gaz, comprenant : une tôle (7) entourant une bande circulaire du carter, ayant des bords (10, 11) fixés au carter (1) et une partie principale (9) foraminée parallèle au carter (7), la tôle et le carter (1) délimitant une chambre de soufflage de gaz (12) dotée d'ouvertures d'évacuation (15) ; un boîtier collecteur (8) entourant la tôle, et délimitant avec la tôle (7) une chambre de distribution (18) de gaz en coiffant la partie principale de la tôle ; une capacité (5) d'alimentation en gaz de refroidissement à distance du boîtier collecteur ; et au moins un conduit de raccord (6) reliant la capacité au boîtier, caractérisé en ce qu'il comprend des reliefs (13, 14) saillant sur le carter pour servir d'appuis aux bords (10, 11) de la tôle (7), et les reliefs (13, 14) procurent une butée en direction axiale (X) du carter à un premier des bords (10) de la tôle et un appui en direction radiale (R) du carter à un second des bords (11) de la tôle (7).Device for cooling a turbomachine revolution casing by a gas flow, comprising: a sheet (7) surrounding a circular band of the casing, having edges (10, 11) fixed to the casing (1) and a main part ( 9) foraminated parallel to the casing (7), the sheet and the casing (1) delimiting a gas blowing chamber (12) provided with discharge openings (15); a manifold box (8) surrounding the sheet, and delimiting with the sheet (7) a distribution chamber (18) of gas by covering the main part of the sheet; a capacity (5) for supplying cooling gas remotely from the manifold; and at least one connection duct (6) connecting the capacity to the housing, characterized in that it includes reliefs (13, 14) projecting from the casing to serve as supports for the edges (10, 11) of the sheet ( 7), and the reliefs (13, 14) provide a stop in the axial direction (X) of the casing at a first of the edges (10) of the sheet and a support in the radial direction (R) of the casing at a second of the edges ( 11) of the sheet (7). Dispositif selon la revendication précédente1, caractérisé en ce que les bords de la tôle sont essentiellement perpendiculaires l'un à l'autre.Device according to the preceding claim1, characterized in that the edges of the sheet are essentially perpendicular to each other. Dispositif selon la revendication 1 ou 2, caractérisé en ce que les bords (16, 17) du boîtier collecteur (8) sont respectivement parallèles aux bords (10, 11) de la tôle, posés sur eux et fixés à eux.Device according to claim 1 or 2, characterized in that the edges (16, 17) of the collecting box (8) are respectively parallel to the edges (10, 11) of the sheet, placed on them and fixed to them. Dispositif selon la revendication 3, caractérisé en ce que l'un des reliefs (14) au moins est muni des ouvertures d'évacuation (15).Device according to claim 3, characterized in that at least one of the reliefs (14) is provided with the discharge openings (15). Dispositif selon l'une quelconque des revendications 1 à 4, caractérisé en ce que le conduit de raccord (6) est coudé et coulissant à travers soit une paroi du boîtier collecteur, soit une paroi de la capacité, soit lesdites deux parois.Device according to any one of claims 1 to 4, characterized in that the connecting duct (6) is bent and sliding through either a wall of the collecting box, or a wall of the container, or said two walls. Turbomachine, caractérisée en ce qu'elle comprend un dispositif selon l'une quelconque des revendications précédentes.Turbomachine, characterized in that it comprises a device according to any one of the preceding claims. Turbomachine selon la revendication 6, caractérisée en ce que la tôle est située autour d'une portion du carter qui est pourvue d'une nervure circulaire.Turbomachine according to claim 6, characterized in that the sheet is located around a portion of the casing which is provided with a circular rib. Turbomachine selon la revendication 6 ou 7, caractérisée en ce que le dispositif de refroidissement comprend une pluralité de tôles et de boîtiers collecteurs respectivement associés aux tôles, les tôles et boîtiers formant des anneaux (4) se succédant autour du carter en direction axiale du carter.Turbomachine according to claim 6 or 7, characterized in that the cooling device comprises a plurality of sheets and manifolds respectively associated with the sheets, the sheets and housings forming rings (4) succeeding each other around the casing in the axial direction of the casing.
EP19182042.2A 2018-06-25 2019-06-24 Cooling device for a turbine-engine housing Active EP3587743B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1855680A FR3082872B1 (en) 2018-06-25 2018-06-25 TURBOMACHINE CASE COOLING SYSTEM

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EP3587743A1 true EP3587743A1 (en) 2020-01-01
EP3587743B1 EP3587743B1 (en) 2021-06-16

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EP (1) EP3587743B1 (en)
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CN110630343A (en) 2019-12-31
EP3587743B1 (en) 2021-06-16
US20190390569A1 (en) 2019-12-26
FR3082872B1 (en) 2021-06-04
US11047259B2 (en) 2021-06-29
CN110630343B (en) 2023-03-28
FR3082872A1 (en) 2019-12-27

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