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EP2307738B1 - Compressor cover for turbine engine having axial abutment - Google Patents

Compressor cover for turbine engine having axial abutment Download PDF

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Publication number
EP2307738B1
EP2307738B1 EP09766040.1A EP09766040A EP2307738B1 EP 2307738 B1 EP2307738 B1 EP 2307738B1 EP 09766040 A EP09766040 A EP 09766040A EP 2307738 B1 EP2307738 B1 EP 2307738B1
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EP
European Patent Office
Prior art keywords
cover
casing
downstream
downstream end
edge
Prior art date
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EP09766040.1A
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German (de)
French (fr)
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EP2307738A2 (en
Inventor
Philippe Joubert
Patrice Laborde
Yann Mouze
Philippe Perot
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 Helicopter Engines SAS
Original Assignee
Safran Helicopter Engines SAS
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Application filed by Safran Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Priority to PL09766040T priority Critical patent/PL2307738T3/en
Publication of EP2307738A2 publication Critical patent/EP2307738A2/en
Application granted granted Critical
Publication of EP2307738B1 publication Critical patent/EP2307738B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/162—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of a centrifugal flow wheel

Definitions

  • the present invention relates to the field of gas turbines, especially those found in turbomachines, for example but not only helicopter turboshaft engines or turbojet engines for aircraft.
  • the present invention more specifically relates to the compression stage of such gas turbines which constitute the main engine of a flying machine.
  • the compressor is disposed between a fresh air intake and a combustion chamber, the role of the compressor being to compress the fresh air entering the gas turbine and to bring this compressed air into the combustion chamber to be mixed with fuel.
  • the impeller comprises a plurality of blades extending generally radially from a wheel hub, which is fixed to a rotary shaft of the gas turbine.
  • the flow of gas firstly enters the compressor casing through an upstream inlet and then flows into the gas stream delimited between its outer surface defined by the cover and its inner surface defined by a surface.
  • the hub of the wheel while being compressed and rotated about the axis of the wheel, before being discharged through a downstream outlet of the compressor, it being specified that the terms "upstream” and "downstream” are taken with reference to the meaning of gas circulation in the gas stream of the compressor.
  • the stream of compressed gas exiting the impeller then enters a diffuser before entering the combustion chamber.
  • the cover defines the outer surface of the vein, the inner surface thereof being formed by a surface of the wheel hub from which the blades extend.
  • This configuration makes it possible to avoid a hyperstatic fixing of the cover which would be potentially harmful to the control of the games between the impeller and the lid.
  • An object of the invention is therefore to provide a cover for avoiding contact with the impeller blades during degraded operation of the compressor.
  • WO 00/34628 discloses a turbine containment system for containing the explosion of a turbine or one or more of its blades which would detach from the hub.
  • the invention achieves its goal by the fact that the cover further comprises a stop intended to limit the axial displacement of the downstream end of the cover with respect to the downstream edge of the casing during operation of the compressor.
  • the stop is disposed at the downstream end of the cover.
  • the axial displacement of the downstream end of the cover is limited.
  • the downstream end of the cover and the downstream edge of the casing are arranged in such a way that when the downstream end of the cover abuts against the downstream edge of the casing, there is still a clearance between the impeller blades and the cover, As a result, contact is advantageously avoided.
  • the cover is mounted while leaving a calibrated axial clearance between the downstream end of the cover and the downstream edge of the housing.
  • the abutment preferably annular, forms a radial extension extending from the downstream end of the cover. It therefore extends orthogonally with respect to an axis of the wheel when the lid is mounted.
  • the abutment consists of a plurality of radial tabs.
  • the stop thus covers radially a circumferential portion of the edge of the housing.
  • downstream end of the cover further comprises an axial extension forming an annular rib capable of almost touching the downstream edge of the housing when the cover is mounted.
  • a small calibrated radial clearance is thus provided between the downstream end of the cover and an inner end of the downstream edge of the casing so as to limit the accidents of shape in the air stream, which are detrimental to the efficiency of the compressor.
  • the present invention finally relates to a gas turbine, in particular a helicopter, comprising one or more compressors in accordance with the present invention.
  • the Figure 1A is an overall sectional view of a helicopter turbine engine 10 known elsewhere.
  • the turbine engine 10 consists of a gas turbine which comprises a compressor 12 , also called compression stage, an air inlet 14 for the admission of fresh air into the compressor 12 and a chamber combustion system 16 in which takes place the combustion of a mixture of fuel and compressed air by the compressor 12 .
  • the turbine engine 10 further comprises a turbine 18 fixed to a rotor wheel 20 of the compressor 12 via a shaft 22 , which turbine 18 , set in motion by the flow of flue gas leaving the combustion chamber 16 , rotates the wheel 20 .
  • the turbine engine 10 further comprises a free turbine 24 which is rotated by the flow of gas leaving the turbine 18 , said free turbine allowing in turn to rotate the rotors of the helicopter (not shown here). ).
  • the impeller with blades 20 of the centrifugal impeller type, is well known elsewhere. It comprises a hub 26 from which radially extend a plurality of blades 28 which may have curved shapes, whose radial ends are contained in a geometrical envelope which has the shape of a hyperboloid of revolution.
  • the wheel 20 also has an axis of rotation A and the term "axial" will be considered with reference to this axis.
  • the compressor 12 comprises a casing 30 which preferably forms a constituent part of the casing of the turbine engine 10 .
  • the casing 30 is the structure that holds the elements of the compressor; as such, the wheel 20 is rotatably mounted in the casing 30 .
  • This casing 30 has an upstream edge 32 and a downstream edge 34 , it being specified that the terms "upstream” and “downstream” are considered as references.
  • the flow direction of the gas flow inside the compressor 20 is illustrated by the arrows F in the different figures.
  • vein 38 is delimited between a surface 26a constituted by the hub 26 , from which the blades 28 extend and a cover 40 defining an outer surface of the vein 38 .
  • the cover 40 covers the blades 28 of the impeller 20 so that it extends between the upstream edge 32 of the casing and the downstream edge 34 of the casing 30 while substantially matching the shape of the geometric envelope mentioned above. above. In other words, there is a small clearance between each of the blades 28 and the lid 40 .
  • the cover 40 has an upstream end 40a and a downstream end 40b , the upstream end 40a being fixed to the upstream edge 32 of the casing via a fastener 42 , while the downstream end 40b is free.
  • downstream end 40b of the cover 40 is not attached to the downstream edge 34 of the housing 30 .
  • downstream edge 34 of the casing 30 is in continuity with the downstream end 40b of the cover 40 .
  • FIG. 2 which illustrates a detail of a turbine engine according to the invention, will now be described a cover 100 of a centrifugal compressor 200 according to the present invention, the other components of the turbine engine 10 being identical to those described above and bearing the same numerical references.
  • downstream end 100b of the cover 100 further comprises a stop 102 forming a radial extension which extends orthogonally with respect to the axis A of the wheel 20 .
  • This stop 102 which is preferably annular, is intended to limit the axial displacement of the downstream end 100b of the cover 100 .
  • the abutment 102 has a contact face 103 adapted to bear against the downstream edge 34 of the casing 30 if the downstream end 100b of the cover 100 bends towards the blades 28 of the impeller, so that the cover 100 can be further deformed, whereby it is advantageously avoided contact between the cover 100 and the blades 28 of the wheel 20 .
  • an axial clearance Ja is provided between the contact face 103 and the downstream edge 34 of the casing 30 .
  • the downstream end 100b of the cover 100 also comprises an axial bulge 104 extending in a direction opposite to that of the contact face 103 .
  • This axial bulge has an annular shape and its role is to reinforce the mechanical strength of the abutment 102 on which mechanical stresses are exerted when it comes into contact with the downstream edge 34 of the casing 30 .
  • downstream end 100b further comprises an axial extension 106 in the form of an annular rib, which is intended to come almost touching the downstream edge 34 of the casing 30 . More specifically, a small radial clearance Jr is provided between this annular rib 106 and the downstream edge 34 so as to prevent the flow of gas being disturbed in the gap between the downstream end 100b of the cover 100 and the downstream edge. 34 of the housing 30 .
  • the annular rib 106 is arranged so that it has a radial height greater than that of the trailing edge of the blades.
  • the inner surface of the cover 100 , wheel side is covered with an abradable material, known moreover, in order to avoid damage to the cover and the blades during possible contacts between them.

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

Description

La présente invention a trait au domaine des turbines à gaz, notamment celles que l'on trouve dans les turbomachines, par exemple mais pas uniquement les turbomoteurs d'hélicoptères ou les turboréacteurs pour avions.The present invention relates to the field of gas turbines, especially those found in turbomachines, for example but not only helicopter turboshaft engines or turbojet engines for aircraft.

La présente invention concerne plus précisément l'étage de compression de telles turbines à gaz qui constituent la motorisation principale d'un engin volant.The present invention more specifically relates to the compression stage of such gas turbines which constitute the main engine of a flying machine.

Plus précisément encore, la présente invention concerne un compresseur centrifuge d'un turbomoteur comprenant :

  • un couvercle comportant une extrémité amont et une extrémité aval,
  • un carter présentant un bord amont et un bord aval,
  • un rouet à pales monté rotatif dans ledit carter,
ledit couvercle étant destiné à couvrir les pales du rouet de façon à définir une surface extérieure d'une veine de gaz s'étendant entre les bords amont et aval du carter, tout en étant fixé au bord amont du carter par son extrémité amont tandis que son extrémité aval demeure libre.More specifically, the present invention relates to a centrifugal compressor of a turbine engine comprising:
  • a cover having an upstream end and a downstream end,
  • a casing having an upstream edge and a downstream edge,
  • a rotor with rotatably mounted blades in said casing,
said cover being intended to cover the impeller blades so as to define an outer surface of a gas stream extending between the upstream and downstream edges of the casing, while being attached to the upstream edge of the casing by its upstream end; its downstream end remains free.

Classiquement, le compresseur est disposé entre une entrée d'air frais et une chambre de combustion, le rôle du compresseur étant de comprimer l'air frais entrant dans la turbine à gaz et d'amener cet air comprimé dans la chambre de combustion pour y être mélangé avec du carburant.Conventionally, the compressor is disposed between a fresh air intake and a combustion chamber, the role of the compressor being to compress the fresh air entering the gas turbine and to bring this compressed air into the combustion chamber to be mixed with fuel.

Par ailleurs, il est connu que le rouet comporte une pluralité de pales s'étendant globalement radialement depuis un moyeu du rouet, lequel est fixé à un arbre rotatif de la turbine à gaz.Furthermore, it is known that the impeller comprises a plurality of blades extending generally radially from a wheel hub, which is fixed to a rotary shaft of the gas turbine.

Ainsi le flux de gaz entre-t-il tout d'abord dans le carter du compresseur par une entrée amont, puis s'écoule dans la veine de gaz délimitée entre sa surface extérieure définie par le couvercle et sa surface intérieure définie par une surface du moyeu du rouet tout en étant comprimé et entraîné en rotation autour de l'axe du rouet, avant d'être évacué par une sortie aval du compresseur, étant précisé que les termes « amont » et « aval » sont pris en référence au sens de circulation du gaz dans la veine de gaz du compresseur.Thus, the flow of gas firstly enters the compressor casing through an upstream inlet and then flows into the gas stream delimited between its outer surface defined by the cover and its inner surface defined by a surface. the hub of the wheel while being compressed and rotated about the axis of the wheel, before being discharged through a downstream outlet of the compressor, it being specified that the terms "upstream" and "downstream" are taken with reference to the meaning of gas circulation in the gas stream of the compressor.

Généralement, le flux de gaz comprimé sortant du rouet pénètre ensuite dans un diffuseur avant d'entrer dans la chambre de combustion.Generally, the stream of compressed gas exiting the impeller then enters a diffuser before entering the combustion chamber.

On comprend donc que le couvercle définit la surface extérieure de la veine, la surface intérieure de celle-ci étant quant à elle formée par une surface du moyeu du rouet d'où s'étendent les pales.It is therefore understood that the cover defines the outer surface of the vein, the inner surface thereof being formed by a surface of the wheel hub from which the blades extend.

Dans un souci de maîtrise du comportement thermo-mécanique du couvercle, son extrémité aval demeure généralement libre, c'est-à-dire qu'elle peut ne pas être fixée au bord aval du carter.In order to control the thermo-mechanical behavior of the cover, its downstream end remains generally free, that is to say that it can not be attached to the downstream edge of the housing.

Cette configuration permet en effet d'éviter une fixation hyperstatique du couvercle qui serait potentiellement dommageable à la maîtrise des jeux entre le rouet et le couvercle.This configuration makes it possible to avoid a hyperstatic fixing of the cover which would be potentially harmful to the control of the games between the impeller and the lid.

Cependant, cette solution n'est pas optimale : certains comportements dégradés du compresseur, tel par exemple le pompage ou d'autres phénomènes instables peuvent apparaître et conduire à des variations brutales de pression dans le rouet du compresseur.However, this solution is not optimal: some degraded behavior of the compressor, such as for example pumping or other unstable phenomena can occur and lead to sudden changes in pressure in the compressor wheel.

Dans la mesure où l'extrémité aval du couvercle est libre, on comprend que ce dernier peut se déformer légèrement du fait des variations de pression dans le compresseur, une telle déformation pouvant conduire le couvercle à venir en contact avec les pales du rouet. En effet, lorsque la pression dans le compresseur devient inférieure à celle existant à l'extérieur du couvercle, ce dernier tend à se déformer et à venir en contact des pales du rouet. Cette déformation peut également être due aux vibrations.Insofar as the downstream end of the cover is free, it is understood that the latter can deform slightly due to pressure variations in the compressor, such deformation can lead the cover to come into contact with the impeller blades. Indeed, when the pressure in the compressor becomes lower than that existing outside the cover, the latter tends to deform and come into contact with the impeller blades. This deformation can also be due to vibrations.

Bien évidemment, il est tout à fait néfaste tant pour le couvercle que pour le rouet, que le couvercle vienne toucher les pales du rouet, un tel contact pouvant en effet endommager sérieusement le compresseur.Of course, it is quite harmful for both the lid and the wheel, the cover comes touching the impeller blades, such contact can indeed seriously damage the compressor.

Un tel phénomène peut également se rencontrer lors du fonctionnement en conditions extrêmes de la turbine à gaz.Such a phenomenon can also be encountered during operation in extreme conditions of the gas turbine.

Une solution à ce problème est d'augmenter le jeu existant entre le couvercle et les pales du rouet. Cependant, une telle solution présente l'inconvénient de baisser le rendement du compresseur et, par voie de conséquence, de diminuer les performances de la turbine à gaz.One solution to this problem is to increase the existing clearance between the cover and the impeller blades. However, such a solution has the disadvantage of reducing the efficiency of the compressor and, consequently, of reducing the performance of the gas turbine.

Un but de l'invention est donc de proposer un couvercle permettant d'éviter le contact avec les pales du rouet lors d'un fonctionnement dégradé du compresseur.An object of the invention is therefore to provide a cover for avoiding contact with the impeller blades during degraded operation of the compressor.

WO 00/34628 divulgue un système de confinement pour turbine destiné à contenir l'explosion d'une turbine ou de l'une ou plusieurs de ses pales qui se détacheraient du moyeu. WO 00/34628 discloses a turbine containment system for containing the explosion of a turbine or one or more of its blades which would detach from the hub.

L'invention atteint son but par le fait que le couvercle comporte en outre une butée destinée à limiter le déplacement axial de l'extrémité aval du couvercle par rapport au bord aval du carter lors du fonctionnement du compresseur.The invention achieves its goal by the fact that the cover further comprises a stop intended to limit the axial displacement of the downstream end of the cover with respect to the downstream edge of the casing during operation of the compressor.

De préférence, la butée est disposée à l'extrémité aval du couvercle.Preferably, the stop is disposed at the downstream end of the cover.

Grâce à la butée conforme à l'invention, le déplacement axial de l'extrémité aval du couvercle est limité.Thanks to the abutment according to the invention, the axial displacement of the downstream end of the cover is limited.

L'extrémité aval du couvercle et le bord aval du carter sont arrangés de telle sorte que lorsque l'extrémité aval du couvercle vient en butée contre le bord aval du carter, il existe encore un jeu entre les pales du rouet et le couvercle, en conséquence de quoi le contact est avantageusement évité.The downstream end of the cover and the downstream edge of the casing are arranged in such a way that when the downstream end of the cover abuts against the downstream edge of the casing, there is still a clearance between the impeller blades and the cover, As a result, contact is advantageously avoided.

De préférence, on monte le couvercle tout en laissant un jeu axial calibré entre l'extrémité aval du couvercle et le bord aval du carter.Preferably, the cover is mounted while leaving a calibrated axial clearance between the downstream end of the cover and the downstream edge of the housing.

Avantageusement, la butée, de préférence annulaire, forme une extension radiale s'étendant depuis l'extrémité aval du couvercle. Elle s'étend donc orthogonalement par rapport à un axe du rouet lorsque le couvercle est monté. Selon une variante, la butée est constituée d'une pluralité de languettes radiales.Advantageously, the abutment, preferably annular, forms a radial extension extending from the downstream end of the cover. It therefore extends orthogonally with respect to an axis of the wheel when the lid is mounted. According to one variant, the abutment consists of a plurality of radial tabs.

La butée recouvre donc radialement une portion circonférentielle du bord du carter.The stop thus covers radially a circumferential portion of the edge of the housing.

De préférence, l'extrémité aval du couvercle comporte en outre une extension axiale formant une nervure annulaire apte à venir presque effleurer le bord aval du carter lorsque le couvercle est monté.Preferably, the downstream end of the cover further comprises an axial extension forming an annular rib capable of almost touching the downstream edge of the housing when the cover is mounted.

Un intérêt de cette extension axiale est de mieux guider l'écoulement de l'air en aval du rouet.An advantage of this axial extension is to better guide the flow of air downstream of the impeller.

On prévoit donc un faible jeu radial calibré entre l'extrémité aval du couvercle et une extrémité intérieure du bord aval du carter de manière à limiter les accidents de forme dans la veine d'air, néfastes pour le rendement du compresseur.A small calibrated radial clearance is thus provided between the downstream end of the cover and an inner end of the downstream edge of the casing so as to limit the accidents of shape in the air stream, which are detrimental to the efficiency of the compressor.

La présente invention concerne enfin une turbine à gaz, notamment d'hélicoptère, comportant un ou plusieurs compresseurs conformes à la présente invention.The present invention finally relates to a gas turbine, in particular a helicopter, comprising one or more compressors in accordance with the present invention.

L'invention sera mieux comprise et ses avantages apparaîtront mieux à la lecture de la description qui suit, d'un mode de réalisation indiqué à titre d'exemple non limitatif. La description se réfère aux dessins annexés sur lesquels :

  • la figure 1A est une vue en coupe d'un turbomoteur d'hélicoptère comportant un compresseur muni d'un couvercle de l'art antérieur ;
  • la figure 1B est une vue de détail du couvercle de la figure 1A ; et
  • la figure 2 représente l'extrémité aval d'un couvercle conforme à la présente invention.
The invention will be better understood and its advantages will appear better on reading the description which follows, of an embodiment indicated by way of non-limiting example. The description refers to the accompanying drawings in which:
  • the Figure 1A is a sectional view of a helicopter turbine engine comprising a compressor provided with a cover of the prior art;
  • the Figure 1B is a detail view of the lid of the Figure 1A ; and
  • the figure 2 represents the downstream end of a lid according to the present invention.

La figure 1A est une vue d'ensemble en coupe d'un turbomoteur d'hélicoptère 10 connu par ailleurs.The Figure 1A is an overall sectional view of a helicopter turbine engine 10 known elsewhere.

Dans cet exemple, le turbomoteur 10 est constitué d'une turbine à gaz qui comporte un compresseur 12, également appelé étage de compression, une entrée d'air 14 pour l'admission d'air frais dans le compresseur 12 ainsi qu'une chambre de combustion 16 dans laquelle a lieu la combustion d'un mélange de carburant et d'air comprimé par le compresseur 12.In this example, the turbine engine 10 consists of a gas turbine which comprises a compressor 12 , also called compression stage, an air inlet 14 for the admission of fresh air into the compressor 12 and a chamber combustion system 16 in which takes place the combustion of a mixture of fuel and compressed air by the compressor 12 .

Le turbomoteur 10 comporte en outre une turbine 18 fixée à un rouet à pales 20 du compresseur 12 par l'entremise d'un arbre 22, laquelle turbine 18, mise en mouvement par le flux de gaz brûlés sortant de la chambre de combustion 16, entraîne en rotation le rouet 20.The turbine engine 10 further comprises a turbine 18 fixed to a rotor wheel 20 of the compressor 12 via a shaft 22 , which turbine 18 , set in motion by the flow of flue gas leaving the combustion chamber 16 , rotates the wheel 20 .

Enfin, le turbomoteur 10 comprend en outre une turbine libre 24 qui est entraînée en rotation par le flux de gaz sortant de la turbine 18, ladite turbine libre permettant quant à elle d'entraîner en rotation les rotors de l'hélicoptère (non représenté ici).Finally, the turbine engine 10 further comprises a free turbine 24 which is rotated by the flow of gas leaving the turbine 18 , said free turbine allowing in turn to rotate the rotors of the helicopter (not shown here). ).

Le rouet à pales 20, du type rouet centrifuge, est bien connu par ailleurs. Il comporte un moyeu 26 d'où s'étendent radialement une pluralité de pales 28 pouvant présenter des formes courbes, dont les extrémités radiales sont contenues dans une enveloppe géométrique qui présente la forme d'un hyperboloïde de révolution. Le rouet 20 présente par ailleurs un axe de rotation A et le terme "axial" sera considéré en référence à cet axe.The impeller with blades 20 , of the centrifugal impeller type, is well known elsewhere. It comprises a hub 26 from which radially extend a plurality of blades 28 which may have curved shapes, whose radial ends are contained in a geometrical envelope which has the shape of a hyperboloid of revolution. The wheel 20 also has an axis of rotation A and the term "axial" will be considered with reference to this axis.

Par ailleurs, le compresseur 12 comporte un carter 30 qui forme de préférence une partie constitutive du carter du turbomoteur 10.Furthermore, the compressor 12 comprises a casing 30 which preferably forms a constituent part of the casing of the turbine engine 10 .

Le carter 30 est la structure qui maintient les éléments du compresseur ; à ce titre, le rouet 20 est monté rotatif dans le carter 30.The casing 30 is the structure that holds the elements of the compressor; as such, the wheel 20 is rotatably mounted in the casing 30 .

Ce carter 30 présente un bord amont 32 et un bord aval 34, étant précisé que les termes « amont » et « aval » sont considérés en référence au sens d'écoulement du flux de gaz à l'intérieur du compresseur 20. Le sens d'écoulement est illustré par les flèches F sur les différentes figures.This casing 30 has an upstream edge 32 and a downstream edge 34 , it being specified that the terms "upstream" and "downstream" are considered as references. in the flow direction of the gas flow inside the compressor 20 . The direction of flow is illustrated by the arrows F in the different figures.

À l'aide de la figure 1B , on comprend que le flux de gaz F entre axialement dans le rouet à pales 20 par une entrée amont 33 et en sort radialement par une sortie 35 proche du bord aval 34 du carter 30 avant de pénétrer dans un diffuseur 36. Le bord aval 34 du carter 30 est constitué ici par un bord amont du diffuseur 36.Using the Figure 1B , It is understood that the flow F of gas axially between the impeller blades 20 through an inlet 33 upstream and radially out through an outlet 35 near the downstream edge 34 of housing 30 prior to entering a diffuser 36. The downstream edge 34 of the casing 30 is constituted here by an upstream edge of the diffuser 36 .

On comprend que le flux de gaz circule entre les pales 28 du rouet 20 dans une veine de gaz 38 s'étendant entre le bord amont 32 et le bord aval 34 du carter 30.It is understood that the flow of gas flows between the blades 28 of the wheel 20 in a gas stream 38 extending between the upstream edge 32 and the downstream edge 34 of the casing 30 .

On constate également que la veine 38 est délimitée entre une surface 26a constituée par le moyeu 26, de laquelle s'étendent les pales 28 et un couvercle 40 définissant une surface extérieure de la veine 38.It is also noted that the vein 38 is delimited between a surface 26a constituted by the hub 26 , from which the blades 28 extend and a cover 40 defining an outer surface of the vein 38 .

Autrement dit, le couvercle 40 couvre les pales 28 du rouet 20 de sorte qu'il s'étend entre le bord amont 32 du carter et le bord aval 34 du carter 30 tout en épousant sensiblement la forme de l'enveloppe géométrique mentionnée ci-dessus. Autrement dit, il existe un faible jeu entre chacune des pales 28 et ce couvercle 40.In other words, the cover 40 covers the blades 28 of the impeller 20 so that it extends between the upstream edge 32 of the casing and the downstream edge 34 of the casing 30 while substantially matching the shape of the geometric envelope mentioned above. above. In other words, there is a small clearance between each of the blades 28 and the lid 40 .

Plus précisément, le couvercle 40 comporte une extrémité amont 40a et une extrémité aval 40b, l'extrémité amont 40a étant fixée au bord amont 32 du carter par l'intermédiaire d'un organe de fixation 42, tandis que l'extrémité aval 40b est libre.More specifically, the cover 40 has an upstream end 40a and a downstream end 40b , the upstream end 40a being fixed to the upstream edge 32 of the casing via a fastener 42 , while the downstream end 40b is free.

En d'autres termes, l'extrémité aval 40b du couvercle 40 n'est pas fixée au bord aval 34 du carter 30.In other words, the downstream end 40b of the cover 40 is not attached to the downstream edge 34 of the housing 30 .

En revanche, on constate que le bord aval 34 du carter 30 est dans la continuité de l'extrémité aval 40b du couvercle 40.On the other hand, it can be seen that the downstream edge 34 of the casing 30 is in continuity with the downstream end 40b of the cover 40 .

Dans la mesure où le couvercle 40 n'est fixé au carter que par le bord amont 32, on comprend qu'il est susceptible de se déformer, essentiellement au niveau de son extrémité aval libre 40b.Insofar as the cover 40 is fixed to the housing only by the upstream edge 32 , it is understood that it is likely to deform, essentially at its free downstream end 40b .

A l'aide de la figure 2 , qui illustre un détail d'un turbomoteur selon l'invention, on va maintenant décrire un couvercle 100 d'un compresseur centrifuge 200 conforme à la présente invention, les autres pièces constitutives du turbomoteur 10 étant identiques à celles décrites précédemment et portant les mêmes références numériques.Using the figure 2 , which illustrates a detail of a turbine engine according to the invention, will now be described a cover 100 of a centrifugal compressor 200 according to the present invention, the other components of the turbine engine 10 being identical to those described above and bearing the same numerical references.

Comme on le voit sur la figure 2 , par rapport à celle de l'art antérieur, l'extrémité aval 100b du couvercle 100 selon l'invention, comporte en outre, une butée 102 formant une extension radiale qui s'étend orthogonalement par rapport à l'axe A du rouet 20.As we see on the figure 2 , compared to that of the prior art, the downstream end 100b of the cover 100 according to the invention further comprises a stop 102 forming a radial extension which extends orthogonally with respect to the axis A of the wheel 20 .

Cette butée 102, qui est préférentiellement annulaire, est destinée à limiter le déplacement axial de l'extrémité aval 100b du couvercle 100.This stop 102 , which is preferably annular, is intended to limit the axial displacement of the downstream end 100b of the cover 100 .

Pour ce faire, la butée 102 comporte une face de contact 103 apte à venir en appui contre le bord aval 34 du carter 30 si l'extrémité aval 100b du couvercle 100 fléchit vers les pales 28 du rouet, en sorte que le couvercle 100 ne puisse se déformer davantage, grâce à quoi on évite avantageusement tout contact entre le couvercle 100 et les pales 28 du rouet 20.To do this, the abutment 102 has a contact face 103 adapted to bear against the downstream edge 34 of the casing 30 if the downstream end 100b of the cover 100 bends towards the blades 28 of the impeller, so that the cover 100 can be further deformed, whereby it is advantageously avoided contact between the cover 100 and the blades 28 of the wheel 20 .

En fonctionnement normal, on prévoit un jeu axial Ja entre la face de contact 103 et le bord aval 34 du carter 30.In normal operation, an axial clearance Ja is provided between the contact face 103 and the downstream edge 34 of the casing 30 .

Comme on le voit sur la figure 2 , l'extrémité aval 100b du couvercle 100 comporte également un renflement axial 104 s'étendant dans un sens opposé à celui de la face de contact 103. Ce renflement axial présente une forme annulaire et a pour rôle de renforcer la tenue mécanique de la butée 102 sur laquelle s'exercent des contraintes mécaniques lorsqu'elle vient en contact avec le bord aval 34 du carter 30.As we see on the figure 2 , the downstream end 100b of the cover 100 also comprises an axial bulge 104 extending in a direction opposite to that of the contact face 103 . This axial bulge has an annular shape and its role is to reinforce the mechanical strength of the abutment 102 on which mechanical stresses are exerted when it comes into contact with the downstream edge 34 of the casing 30 .

Par ailleurs, l'extrémité aval 100b comporte en outre une extension axiale 106 présentant la forme d'une nervure annulaire, qui est destinée à venir quasiment effleurer le bord aval 34 du carter 30. Plus précisément, on prévoit un faible jeu radial Jr entre cette nervure annulaire 106 et le bord aval 34 de manière à éviter que le flux de gaz ne soit perturbé dans l'interstice existant entre l'extrémité aval 100b du couvercle 100 et le bord aval 34 du carter 30.Furthermore, the downstream end 100b further comprises an axial extension 106 in the form of an annular rib, which is intended to come almost touching the downstream edge 34 of the casing 30 . More specifically, a small radial clearance Jr is provided between this annular rib 106 and the downstream edge 34 so as to prevent the flow of gas being disturbed in the gap between the downstream end 100b of the cover 100 and the downstream edge. 34 of the housing 30 .

De préférence, la nervure annulaire 106 est arrangée de telle sorte qu'elle présente une hauteur radiale supérieure à celle du bord de fuite des pales.Preferably, the annular rib 106 is arranged so that it has a radial height greater than that of the trailing edge of the blades.

De préférence, la surface interne du couvercle 100, côté rouet, est recouverte d'un matériau abradable, connu par ailleurs, afin d'éviter d'endommager le couvercle et les pales lors d'éventuels contacts entre eux.Preferably, the inner surface of the cover 100 , wheel side, is covered with an abradable material, known moreover, in order to avoid damage to the cover and the blades during possible contacts between them.

Claims (6)

  1. A centrifugal compressor of a turboshaft engine comprising:
    • a cover including an upstream end (40a) and a downstream end (100b);
    • a casing (30) presenting an upstream edge (32) and a downstream edge (34); and
    • a bladed impeller (20) mounted to rotate in said casing;
    said cover being designed to cover the blades (28) of the impeller so as to define an outside surface of a gas-flow passage (39) extending between the upstream and downstream edges of the casing, being fastened to the upstream edge (32) of the casing via its upstream end while its downstream end (100b) remains free, characterized in that the cover further includes an abutment (102) for limiting the axial movement of its downstream end (100b) relative to the downstream edge (34) of the casing while the compressor is in operation.
  2. A centrifugal compressor according to claim 1, characterized in that the abutment (102) forms a radial extension extending from the downstream end of the cover.
  3. A centrifugal compressor according to claim 1 or 2, characterized in that the abutment (102) is annular.
  4. A centrifugal compressor according to any one of claims 1 to 3, characterized in that the abutment (102) is constituted by a plurality of radial tongues.
  5. A centrifugal compressor according to any one of claims 1 to 4, characterized in that the downstream end (100b) of the cover further includes an axial extension (106) forming an annular rim.
  6. A gas turbine including a centrifugal compressor (200) according to any one of claims 1 to 5.
EP09766040.1A 2008-05-26 2009-05-20 Compressor cover for turbine engine having axial abutment Active EP2307738B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL09766040T PL2307738T3 (en) 2008-05-26 2009-05-20 Compressor cover for turbine engine having axial abutment

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0853394A FR2931521B1 (en) 2008-05-26 2008-05-26 AXIS COMPRESSOR COVER.
PCT/FR2009/050939 WO2009153478A2 (en) 2008-05-26 2009-05-20 Compressor cover for turbine engine having axial abutment

Publications (2)

Publication Number Publication Date
EP2307738A2 EP2307738A2 (en) 2011-04-13
EP2307738B1 true EP2307738B1 (en) 2018-10-10

Family

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Application Number Title Priority Date Filing Date
EP09766040.1A Active EP2307738B1 (en) 2008-05-26 2009-05-20 Compressor cover for turbine engine having axial abutment

Country Status (11)

Country Link
US (1) US8721261B2 (en)
EP (1) EP2307738B1 (en)
JP (1) JP5497012B2 (en)
KR (1) KR101629524B1 (en)
CN (1) CN102046984B (en)
CA (1) CA2726905C (en)
ES (1) ES2695902T3 (en)
FR (1) FR2931521B1 (en)
PL (1) PL2307738T3 (en)
RU (1) RU2509232C2 (en)
WO (1) WO2009153478A2 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3008750B1 (en) * 2013-07-18 2015-07-17 Snecma TURBOMACHINE CENTRIFUGAL COMPRESSOR COVER FIXED BY THE DOWNSTAIR NEAR ITS UPSTREAM EDGE, TURBOMACHINE HAVING THIS COVER.
CN111120656B (en) * 2019-12-25 2022-05-27 中国航空工业集团公司西安飞机设计研究所 Fireproof sealing structure for air inlet channel

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Publication number Priority date Publication date Assignee Title
US2656096A (en) * 1946-01-04 1953-10-20 Rateau Soc Centrifugal pump and compressor
US3613360A (en) * 1969-10-30 1971-10-19 Garrett Corp Combustion chamber construction
US4264271A (en) * 1979-03-15 1981-04-28 Avco Corporation Impeller shroud of a centrifugal compressor
US4687412A (en) * 1985-07-03 1987-08-18 Pratt & Whitney Canada Inc. Impeller shroud
FR2698666B1 (en) * 1992-11-30 1995-02-17 Europ Propulsion High performance centrifugal pump with open impeller.
US6224321B1 (en) * 1998-12-07 2001-05-01 Pratt & Whitney Canada Inc. Impeller containment system
JP2003120591A (en) 2001-10-12 2003-04-23 Mitsubishi Heavy Ind Ltd Turbo-machine
US7908869B2 (en) * 2006-09-18 2011-03-22 Pratt & Whitney Canada Corp. Thermal and external load isolating impeller shroud
RU2352826C2 (en) * 2007-04-03 2009-04-20 Открытое акционерное общество "Производственное объединение "Северное машиностроительное предприятие" Centrifugal hydraulic and air pump-compressor

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Also Published As

Publication number Publication date
CN102046984B (en) 2014-04-30
JP2011521172A (en) 2011-07-21
FR2931521B1 (en) 2017-06-23
KR20110016954A (en) 2011-02-18
US20110076141A1 (en) 2011-03-31
CA2726905A1 (en) 2009-12-23
PL2307738T3 (en) 2019-01-31
KR101629524B1 (en) 2016-06-13
ES2695902T3 (en) 2019-01-11
RU2509232C2 (en) 2014-03-10
CN102046984A (en) 2011-05-04
RU2010153329A (en) 2012-07-10
JP5497012B2 (en) 2014-05-21
EP2307738A2 (en) 2011-04-13
US8721261B2 (en) 2014-05-13
CA2726905C (en) 2016-10-25
FR2931521A1 (en) 2009-11-27
WO2009153478A3 (en) 2010-05-27
WO2009153478A2 (en) 2009-12-23

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