EP0273790A1 - Compressor housing adapted for active regulated thermal dilatation, and method for its production - Google Patents

Compressor housing adapted for active regulated thermal dilatation, and method for its production Download PDF

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Publication number
EP0273790A1
EP0273790A1 EP87402660A EP87402660A EP0273790A1 EP 0273790 A1 EP0273790 A1 EP 0273790A1 EP 87402660 A EP87402660 A EP 87402660A EP 87402660 A EP87402660 A EP 87402660A EP 0273790 A1 EP0273790 A1 EP 0273790A1
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EP
European Patent Office
Prior art keywords
skin
compressor housing
housing according
skins
compressor
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
EP87402660A
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German (de)
French (fr)
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EP0273790B1 (en
Inventor
Alain Marie Joseph Lardellier
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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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 EP0273790A1 publication Critical patent/EP0273790A1/en
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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
    • 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
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • F01D25/145—Thermally insulated casings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine

Definitions

  • the invention relates to an axial type compressor casing suitable for the active control of its expansions and its manufacturing process.
  • An axial compressor of a turbomachine generally comprises several stages of blades joined together to form a rotor as well as interposed stages of stator blades which are integral with an external casing forming the compressor casing.
  • FR-A-2 482 661 provides an example of such an embodiment according to which a compressor stator comprises a double-casing casing, an internal casing supporting the stator vanes, axially continuous, consisting of peripheral segments and an annular external casing, the two envelopes being connected by radial flanges.
  • the vanes are connected at their other end by an internal ferrule.
  • the stator assembly is surrounded by several tubes for cooling air.
  • FR-A-2 534 982 and FR-A-2 535 795 are given by FR-A-2 534 982 and FR-A-2 535 795, according to which the cylindrical segments of an inner casing are kept hooked to an outer casing by supports, forming a housing compressor.
  • FR-A-2 577 282 provides a multiplicity of radial rods arranged between the yokes of the inner and outer casings constituting the turbomachine casing and articulated by means of a system of pins.
  • a compressor casing of the aforementioned type and in accordance with the invention is characterized in that the face of the inner skin situated opposite the outer skin has circumferential undulations and the crests of the undulations carry rows of flexible columns also integral with the outer skin and located alternately, in the longitudinal direction, in line with a leading edge and a trailing edge of the stator vanes which are integral with the radially inner side of said inner skin.
  • the inner skin and the inner shell are made up of a multiplicity of assembled sectors and each sector has inter-skin connecting elements made up of a solid block forming a fixed point around which the expansions are distributed and two strips for taking up the couples exercising in operation.
  • the outer skin can be of generally planar shape or include circumferential undulations homothetic to those of the inner skin.
  • the method of manufacturing the casing according to the invention comprises a casting operation of the known type with lost wax, making it possible to obtain either a one-piece casing or two half-shells.
  • a compressor 1 of the axial type of a kind intended to provide the compression function in a turbomachine which may in particular be for aeronautical use is shown in Figure 1 and consists, on the one hand, of a rotating part of revolution constituting a rotor 2, shown in thin lines and which is not part of the invention, composed of several discs 3a, 3b, 3c , 3d, four in number in the example shown, forming a rotor drum 3 and each carrying a stage of movable vanes, respectively 4a, 4b, 4c and 4d and, on the other hand, of a fixed cooperating part constituting a stator or compressor casing 5, object of the present invention.
  • the compressor casing 5 has an outer skin 6 and radially spaced in the direction of the axis of rotation of the compressor, an inner skin 7.
  • the outer skin 6 is in one piece or, alternatively, it can be formed of two half-shells 6a and 6b assembled longitudinally by flanges 6c and 6d, as shown in FIG. 1a.
  • the inner skin 7 and an internal ferrule 8 delimiting the gas circulation stream consist of sectors assembled to form an annular structure.
  • a sector 5a is shown for example in FIG. 3 and the annular structure in this case consists of eight sectors, such as 5a, for example and comprises two rows of stator vanes 9a and 9b.
  • the annular structure in this case consists of eight sectors, such as 5a, for example and comprises two rows of stator vanes 9a and 9b.
  • the cooperating edges 5b and 5c of the sectors 5a have respective profiles in Z as shown in FIG. 3.
  • the inner skin 7, as shown in figures 1 and 4 has a corrugated profile on its radially outer face.
  • the recess 7a of a corrugation is located approximately at the middle of a stage of blades and the crest 7b of a corrugation is located approximately at the edge of a blade.
  • Rows of flexible balusters 10 connect the inner skin 7 and the outer skin 6 and join them together, each baluster being located on the crest 7b of an undulation of the inner skin 7 and a baluster being for example placed at each stator vane , as shown in FIG. 3. It follows that each sector 5a comprising in this case two rows of stator vanes also carries four rows of balusters 10. Each sector 5a also includes connecting elements 11 and 12 arranged between the inner skin 7 and outer skin 6.
  • the outer skin 6 is preferably in one piece. It can have a smooth, ordinary wall shape. According to the embodiment shown in Figures 1 to 4, the outer skin 6 also has a profile wavy in the longitudinal direction, the successive corrugations being circumferential.
  • the columns 10 described above are located on the radially inner face of the outer skin 6 in the hollow 6a of a corrugation.
  • the respective undulations of the outer skin 6 and of the radially outer wall of the inner skin 7 are located in the same transverse plane, perpendicular to the axis of rotation of the compressor.
  • the radially inner face of the outer skin 6 is reinforced by longitudinal ribs 13 visible for example in Figure 2, in section.
  • the outer skin 6 is limited by a casing flange, respectively 14 and 15, connecting the compressor casing 5 to the adjacent turbomachine housings at the level of cooperating flanges 16 and 17 respectively.
  • the space between the two skins 6 and 7 of the casing 5 is filled with a ceramic-type material 18 which provides thermal insulation and also fulfills a sealing function between the sectors 5a by preventing recirculation of gas between the skins 6 and 7 of the casing 5 coming from the main gas stream.
  • this ceramic material 18 can come from a foundry core used in the manufacture of the compressor casing 5 during casting in a foundry manufacturing process.
  • a perforated tube 19a, 19b, 19c, 19d, 19e, 19f, 19g circumferentially surrounding the casing 5, supplied with air in a known manner and placed at a distance allowing the impact of air jets on the external surface of the casing 5.
  • the entire casing 5 consisting of the outer skin 6, the inner skin 7, the balusters 10 and the connecting elements 11 and 12, the stator vanes 9a, 9b can be obtained in one piece by a casting type casting process lost wax.
  • the wax models of skins 6 and 7 are then separated by a ceramic-type core.
  • This core comprises radial channels, arranged for the passage of the molten metal intended to constitute the stator vanes.
  • the metal solidified in these channels must constitute the columns 10 and the connecting elements 11 and 12 between the inner skin 7 and the outer skin 6.
  • the usual known techniques for implementing a method of casting with lost wax, coating in a shell of refractory material then removal of the wax, are applied.
  • cuts into sectors 5a are carried out at the level of the inner skin 7 and of the internal ferrule 8 joining the ends of stator vanes. These cuts can for example be carried out according to a wire cutting process by electro-erosion, by applying techniques known per se.

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

Abstract

Un carter (5) de compresseur du genre à double peau (6,7) comporte une face radialement externe de la peau intérieure (7) à profil ondulé dans le sens longitudinal et des colonnettes (10) flexibles situées sur la crête (7b) d'une ondulation, alternativement au niveau d'un bord d'attaque et d'un bord de fuite des aubes de stator (9a à 9d) disposées entre ladite peau intérieure (7) et une virole interne (8), et solidarisant les deux peaux (6,7). Un tel carter (5) est obtenu monobloc par un procédé de fabrication en fonderie à la cire perdue. La peau intérieure (7) et la virole (8) sont découpées pour former des secteurs (5a).A compressor casing (5) of the double skin type (6,7) has a radially outer face of the inner skin (7) with a corrugated profile in the longitudinal direction and flexible balusters (10) located on the crest (7b) a ripple, alternately at a leading edge and a trailing edge of the stator vanes (9a to 9d) disposed between said inner skin (7) and an internal ferrule (8), and joining the two skins (6,7). Such a casing (5) is obtained in one piece by a lost wax foundry manufacturing process. The inner skin (7) and the ferrule (8) are cut to form sectors (5a).

Description

L'invention concerne un carter de compresseur de type axial adapté pour le pilotage actif de ses dilatations et son procédé de fabrication.The invention relates to an axial type compressor casing suitable for the active control of its expansions and its manufacturing process.

Un compresseur axial de turbomachine comporte généralement plusieurs étages d'aubes réunis pour former un rotor ainsi que des étages intercalés d'aubes statoriques qui sont solidaires d'une enveloppe externe formant le carter de compresseur.An axial compressor of a turbomachine generally comprises several stages of blades joined together to form a rotor as well as interposed stages of stator blades which are integral with an external casing forming the compressor casing.

FR-A-2 482 661 fournit un exemple d'une telle réalisation selon laquelle un stator de compresseur comporte un carter à double enveloppe, une enveloppe interne supportant les aubes statoriques, axialement continue, constituée de segments périphériques et une enveloppe externe annulaire, les deux enveloppes étant reliées par des brides radiales. Les aubes sont reliées à leur autre extrémité par une virole interne. L'ensemble de stator est entouré de plusieurs tubes pour l'air de refroidissement.FR-A-2 482 661 provides an example of such an embodiment according to which a compressor stator comprises a double-casing casing, an internal casing supporting the stator vanes, axially continuous, consisting of peripheral segments and an annular external casing, the two envelopes being connected by radial flanges. The vanes are connected at their other end by an internal ferrule. The stator assembly is surrounded by several tubes for cooling air.

D'autres exemples de réalisation sont donnés par FR-A-2 534 982 et FR-A-2 535 795, selon lesquels les segments cylindriques d'une enveloppe intérieure sont maintenus accrochés à une enveloppe extérieure par des supports, formant un carter de compresseur. Ou encore, FR-A-2 577 282 prévoit une multiplicité de biellettes radiales disposées entre des chapes des enveloppes intérieure et extérieure constituant le carter de turbomachine et articulées au moyen d'un système de broches.Other embodiments are given by FR-A-2 534 982 and FR-A-2 535 795, according to which the cylindrical segments of an inner casing are kept hooked to an outer casing by supports, forming a housing compressor. Or, FR-A-2 577 282 provides a multiplicity of radial rods arranged between the yokes of the inner and outer casings constituting the turbomachine casing and articulated by means of a system of pins.

Ces solutions antérieures visent également à maintenir un jeu constant et faible entre rotor et stator, quelles que soient les conditions de fonctionnement de la turbomachine et en particulier durant les phases transitoires (accélération ou décélération) car ce facteur concourt à l'amélioration des performances, du rendement et de la consommation spécifique. Elles présentent toutefois des inconvénients, sans même considérer plus en détails la qualité des résultats obtenus par chacune, car leur mise en oeuvre nécessite en effet la réalisation et l'assemblage d'une multiplicité de pièces et cette complexité a également des répercussions sur les coûts et sur la masse.These prior solutions also aim to maintain a constant and low clearance between rotor and stator, whatever the operating conditions of the turbomachine and in particular during the transient phases. (acceleration or deceleration) because this factor contributes to the improvement of performance, efficiency and specific consumption. However, they have drawbacks, without even considering in more detail the quality of the results obtained by each, because their implementation indeed requires the production and assembly of a multiplicity of parts and this complexity also has repercussions on costs. and on the mass.

L'invention vise par conséquent à obtenir ces résultats sans encourir les inconvénients résultant des solutions connues antérieures. Un carter de compresseur du genre précité et conforme à l'invention est caractérisé en ce que la face de la peau intérieure située en regard de la peau extérieure comporte des ondulations circonférentielles et les crêtes des ondulations portent des rangées de colonnettes flexibles solidaires également de la peau extérieure et situées alternativement, dans le sens longitudinal, au droit d'un bord d'attaque et d'un bord de fuite des aubes de stator qui sont solidaires du côté radialement interne de ladite peau intérieure.The invention therefore aims to obtain these results without incurring the disadvantages resulting from prior known solutions. A compressor casing of the aforementioned type and in accordance with the invention is characterized in that the face of the inner skin situated opposite the outer skin has circumferential undulations and the crests of the undulations carry rows of flexible columns also integral with the outer skin and located alternately, in the longitudinal direction, in line with a leading edge and a trailing edge of the stator vanes which are integral with the radially inner side of said inner skin.

Avantageusement, la peau intérieure et la virole interne sont constituées d'une multiplicité de secteurs assemblés et chaque secteur comporte des éléments de liaison entre­peaux constitués d'un bloc massif formant un point fixe autour duquel se répartissent les dilatations et de deux lamelles de reprise des couples s'exerçant en fonctionnement. Selon le mode de réalisation, la peau extérieure peut être de forme générale plane ou comporter des ondulations circonférentielles homothétiques de celles de la peau intérieure.Advantageously, the inner skin and the inner shell are made up of a multiplicity of assembled sectors and each sector has inter-skin connecting elements made up of a solid block forming a fixed point around which the expansions are distributed and two strips for taking up the couples exercising in operation. According to the embodiment, the outer skin can be of generally planar shape or include circumferential undulations homothetic to those of the inner skin.

Dans la mise en oeuvre de l'invention, le procédé de fabrication du carter conforme à l'invention comporte une opération de coulée du type connu à la cire perdue permettant d'obtenir soit un carter monobloc, soit deux demi-coquilles.In the implementation of the invention, the method of manufacturing the casing according to the invention comprises a casting operation of the known type with lost wax, making it possible to obtain either a one-piece casing or two half-shells.

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 d'un carter de compresseur conforme à l'invention et de ses variantes, en référence aux dessins annexés sur lesquels :

  • - la figure 1 représente une vue en coupe longitudinale par un plan passant par l'axe de rotation du compresseur d'un carter de compresseur selon un mode de réalisation de l'invention ;
    • - la figure 1a représente une variante de réalisation du carter de compresseur en deux demi-coquilles,représentée en vue perspective ;
  • - la figure 2 représente une coupe selon la ligne II-II du carter de compresseur représenté à la figure 1 ;
  • - la figure 3 représente une coupe selon la ligne III-III du carter de compresseur représenté à la figure 2 ;
  • - la figure 4 représente une vue en perspective d'une partie de carter de compresseur représenté aux figures 1 à 3.
Other characteristics and advantages of the invention will be better understood on reading the description which follows of an embodiment of a compressor casing according to the invention and its variants, with reference to the accompanying drawings on which :
  • - Figure 1 shows a longitudinal sectional view through a plane passing through the axis of rotation of the compressor of a compressor housing according to an embodiment of the invention;
    • - Figure 1a shows an alternative embodiment of the compressor housing in two half-shells, shown in perspective view;
  • - Figure 2 shows a section along line II-II of the compressor housing shown in Figure 1;
  • - Figure 3 shows a section along line III-III of the compressor housing shown in Figure 2;
  • FIG. 4 represents a perspective view of a part of the compressor casing shown in FIGS. 1 to 3.

Un compresseur 1 de type axial d'un genre destiné à assurer la fonction de compression dans une turbomachine qui peut être notamment à destination aéronautique est représenté à la figure 1 et se compose, d'une part, d'une partie tournante de révolution constituant un rotor 2, représenté en traits fins et qui ne fait pas partie de l'invention, composé de plusieurs disques 3a, 3b, 3c, 3d, au nombre de quatre dans l'exemple représenté, formant un tambour 3 de rotor et portant chacun un étage d'aubes mobiles, respectivement 4a, 4b,4c et 4d et, d'autre part, d'une partie fixe coopérante constituant un stator ou carter 5 de compresseur, objet de la présente invention.A compressor 1 of the axial type of a kind intended to provide the compression function in a turbomachine which may in particular be for aeronautical use is shown in Figure 1 and consists, on the one hand, of a rotating part of revolution constituting a rotor 2, shown in thin lines and which is not part of the invention, composed of several discs 3a, 3b, 3c , 3d, four in number in the example shown, forming a rotor drum 3 and each carrying a stage of movable vanes, respectively 4a, 4b, 4c and 4d and, on the other hand, of a fixed cooperating part constituting a stator or compressor casing 5, object of the present invention.

Le carter 5 de compresseur comporte une peau extérieure 6 et radialement espacée en direction de l'axe de rotation du compresseur, une peau intérieure 7. La peau extérieure 6 est monobloc ou, en variante, elle peut être formée de deux demi-coquilles 6a et 6b assemblées longitudinalement par des brides 6c et 6d, comme représenté sur la figure 1a.The compressor casing 5 has an outer skin 6 and radially spaced in the direction of the axis of rotation of the compressor, an inner skin 7. The outer skin 6 is in one piece or, alternatively, it can be formed of two half-shells 6a and 6b assembled longitudinally by flanges 6c and 6d, as shown in FIG. 1a.

La peau intérieure 7 et une virole interne 8 délimitant la veine de circulation des gaz sont constituées de secteurs assemblés pour former une structure annulaire. Un tel secteur 5a est représenté par exemple à la figure 3 et la structure annulaire se compose dans ce cas de huit secteurs, tels que 5a, par exemple et comporte deux rangées d'aubes statoriques 9a et 9b. Dans l'exemple représenté, comportant quatre étages d'aubes statoriques 9a, 9b, 9c et 9d, il y aura par conséquent deux rangées de chacune huit secteurs d'aubes, juxtaposées longitudinalement pour former le carter 5 de compresseur et les étages d'aubes statoriques 9a, 9b, 9c et 9d sont disposés entre la peau intérieure 7 et la virole interne 8. Les bords coopérants 5b et 5c des secteurs 5a ont des profils respectifs en Z tels que représentés à la figure 3. La peau intérieure 7, comme visible sur les figures 1 et 4 présente un profil ondulé sur sa face radialement externe. Le creux 7a d'une ondulation est situé approximativement au niveau du milieu d'un étage d'aubes et la crête 7b d'une ondulation est située approximativement au niveau d'un bord d'aubes. Des rangées de colonnettes flexibles 10 relient la peau intérieure 7 et la peau extérieure 6 et les solidarisent, chaque colonnette étant implantée sur la crête 7b d'une ondulation de la peau intérieure 7 et une colonnette étant par exemple placée au niveau de chaque aube statorique, comme cela est représenté sur la figure 3. Il en résulte que chaque secteur 5a comportant dans ce cas deux rangées d'aubes statoriques porte également quatre rangées de colonnettes 10. Chaque secteur 5a comporte également des éléments de liaison 11 et 12 disposés entre la peau intérieure 7 et la peau extérieure 6. Deux éléments constitués de lamelles 11a et 11b, orientées l'une dans le sens périphérique et l'autre dans le sens perpendiculaire, longitudinal ou axial par rapport au compresseur assurent une reprise des couples créés par les efforts s'exerçant en fonctionnement et un élément formé d'un bloc massif 12, disposé approximativement au centre du secteur 5a, constitue un point fixe à partir duquel se développent les dilatations en fonctionnement. La peau extérieure 6 est de préférence monobloc. Elle peut présenter une forme de paroi lisse, ordinaire. Selon le mode de réalisation représenté sur les figures 1 à 4, la peau extérieure 6 présente également un profil ondulé dans le sens longitudinal, les ondulations successives étant circonférentielles. Les colonnettes 10 décrites ci-dessus sont implantées sur la face radialement interne de la peau extérieure 6 dans le creux 6a d'une ondulation. Les ondulations respectives de la peau extérieure 6 et de la paroi radialement externe de la peau intérieure 7 sont situées dans un même plan transversal, perpendiculaire à l'axe de rotation du compresseur. La face radialement interne de la peau extérieure 6 est renforcée par des nervures longitudinales 13 visibles par exemple sur la figure 2, en coupe. Côté amont et côté aval, la peau extérieure 6 est limitée par une bride de carter, respectivement 14 et 15, raccordant le carter 5 de compresseur aux carters adjacents de turbomachine au niveau de brides coopérantes 16 et 17 respectivement. L'espace situé entre les deux peaux 6 et 7 du carter 5 est rempli d'un matériau de type céramique 18 qui procure une isolation thermique et remplit également une fonction d'étanchéité entre les secteurs 5a en empêchant des recirculations de gaz entre les peaux 6 et 7 du carter 5 provenant de la veine principale des gaz.The inner skin 7 and an internal ferrule 8 delimiting the gas circulation stream consist of sectors assembled to form an annular structure. Such a sector 5a is shown for example in FIG. 3 and the annular structure in this case consists of eight sectors, such as 5a, for example and comprises two rows of stator vanes 9a and 9b. In the example shown, comprising four stages of stator vanes 9a, 9b, 9c and 9d, there will therefore be two rows of each eight sectors of blades, juxtaposed longitudinally to form the compressor casing 5 and the stages of stator vanes 9a, 9b, 9c and 9d are arranged between the inner skin 7 and the inner ferrule 8. The cooperating edges 5b and 5c of the sectors 5a have respective profiles in Z as shown in FIG. 3. The inner skin 7, as shown in figures 1 and 4 has a corrugated profile on its radially outer face. The recess 7a of a corrugation is located approximately at the middle of a stage of blades and the crest 7b of a corrugation is located approximately at the edge of a blade. Rows of flexible balusters 10 connect the inner skin 7 and the outer skin 6 and join them together, each baluster being located on the crest 7b of an undulation of the inner skin 7 and a baluster being for example placed at each stator vane , as shown in FIG. 3. It follows that each sector 5a comprising in this case two rows of stator vanes also carries four rows of balusters 10. Each sector 5a also includes connecting elements 11 and 12 arranged between the inner skin 7 and outer skin 6. Two elements made up of lamellae 11a and 11b, one oriented in the peripheral direction and the other in the perpendicular, longitudinal or axial direction relative to the compressor, ensure that the torques created by the forces exerted during operation and an element formed of a solid block 12, disposed approximately at the center of sector 5a, constitutes a fixed point from which develop the expansions in operation. The outer skin 6 is preferably in one piece. It can have a smooth, ordinary wall shape. According to the embodiment shown in Figures 1 to 4, the outer skin 6 also has a profile wavy in the longitudinal direction, the successive corrugations being circumferential. The columns 10 described above are located on the radially inner face of the outer skin 6 in the hollow 6a of a corrugation. The respective undulations of the outer skin 6 and of the radially outer wall of the inner skin 7 are located in the same transverse plane, perpendicular to the axis of rotation of the compressor. The radially inner face of the outer skin 6 is reinforced by longitudinal ribs 13 visible for example in Figure 2, in section. Upstream side and downstream side, the outer skin 6 is limited by a casing flange, respectively 14 and 15, connecting the compressor casing 5 to the adjacent turbomachine housings at the level of cooperating flanges 16 and 17 respectively. The space between the two skins 6 and 7 of the casing 5 is filled with a ceramic-type material 18 which provides thermal insulation and also fulfills a sealing function between the sectors 5a by preventing recirculation of gas between the skins 6 and 7 of the casing 5 coming from the main gas stream.

Comme il sera décrit plus loin, ce matériau céramique 18 peut provenir d'un noyau de fonderie utilisé dans la fabrication du carter de compresseur 5 lors de la coulée dans un procédé de fabrication en fonderie. Au droit de chaque creux d'ondulation de la face externe de la peau extérieure 6, est disposé un tube perforé 19a, 19b, 19c, 19d, 19e, 19f, 19g entourant circonférentiellement le carter 5, alimenté en air de manière connue et placé à une distance permettant l'impact de jets d'air sur la surface externe du carter 5.As will be described later, this ceramic material 18 can come from a foundry core used in the manufacture of the compressor casing 5 during casting in a foundry manufacturing process. In line with each undulation hollow of the external face of the external skin 6, is arranged a perforated tube 19a, 19b, 19c, 19d, 19e, 19f, 19g circumferentially surrounding the casing 5, supplied with air in a known manner and placed at a distance allowing the impact of air jets on the external surface of the casing 5.

On va maintenant décrire un procédé de fabrication selon l'invention, adapté pour la réalisation du carter de compresseur 5 qui vient d'être décrit. L'ensemble du carter 5 constitué par la peau extérieure 6, la peau intérieure 7, les colonnettes 10 et les éléments de liaison 11 et 12, les aubes statoriques 9a, 9b peut être obtenu monobloc par un procédé de fonderie du type coulée à la cire perdue. Les modèles en cire des peaux 6 et 7 sont alors séparés par un noyau de type céramique. Ce noyau comporte des canaux radiaux, ménagés pour le passage du métal fondu destiné à constituer les aubes statoriques. Le métal solidifié dans ces canaux doit constituer les colonnettes 10 et les éléments de liaison 11 et 12 entre la peau intérieure 7 et la peau extérieure 6. Les techniques connues habituelles de mise en oeuvre d'un procédé de coulée à la cire perdue, enrobage dans une carapace de matériau réfractaire puis élimination de la cire, sont appliquées.We will now describe a manufacturing process according to the invention, suitable for producing the compressor housing 5 which has just been described. The entire casing 5 consisting of the outer skin 6, the inner skin 7, the balusters 10 and the connecting elements 11 and 12, the stator vanes 9a, 9b can be obtained in one piece by a casting type casting process lost wax. The wax models of skins 6 and 7 are then separated by a ceramic-type core. This core comprises radial channels, arranged for the passage of the molten metal intended to constitute the stator vanes. The metal solidified in these channels must constitute the columns 10 and the connecting elements 11 and 12 between the inner skin 7 and the outer skin 6. The usual known techniques for implementing a method of casting with lost wax, coating in a shell of refractory material then removal of the wax, are applied.

Lorsqu'un ensemble monobloc est obtenu en fonderie, des découpes longitudinales sont effectuées en vue d'obtenir deux demi-coquilles pour l'assemblage final du compresseur entre rotor et stator. En variante du procédé de fabrication, l'ensemble peut être obtenu par fonderie en deux demi-coquilles.When a one-piece assembly is obtained in foundry, longitudinal cuts are made in order to obtain two half-shells for the final assembly of the compressor between rotor and stator. As a variant of the manufacturing process, the assembly can be obtained by foundry in two half-shells.

Dans tous les cas, des découpes en secteurs 5a sont effectuées au niveau de la peau intérieure 7 et de la virole interne 8 réunissant les extrémités d'aubes statoriques. Ces découpes peuvent par exemple être effectuées selon un procédé de découpe au fil par électro-­érosion, en appliquant des techniques connues en soi.In all cases, cuts into sectors 5a are carried out at the level of the inner skin 7 and of the internal ferrule 8 joining the ends of stator vanes. These cuts can for example be carried out according to a wire cutting process by electro-erosion, by applying techniques known per se.

Claims (10)

1. - Carter de compresseur de type axial adapté pour le pilotage actif de ses dilatations d'un genre à double peau et portant des étages d'aubes statoriques dans une veine de circulation des gaz délimitée par une virole interne (8), associé à des rampes extérieures (19a à 19g) de refroidissement par jets d'air, caractérisé en ce que la face de la peau intérieure (7), située en regard de la peau extérieure (6) comporte des ondulations circonférentielles disposées dans le sens longitudinal et les crêtes (7b) des ondulations portent des rangées de colonnettes (10) flexibles solidaires également de la peau extérieure (6) et situées alternativement, dans le sens longitudinal, au droit d'un bord d'attaque et d'un bord de fuite des aubes (9a à 9d) de stator qui sont solidaires du côté radialement interne de ladite peau intérieure (7).1. - Axial type compressor casing suitable for the active control of its expansions of a double skin type and carrying stages of stator vanes in a gas circulation stream delimited by an internal ferrule (8), associated with external ramps (19a to 19g) of cooling by air jets, characterized in that the face of the internal skin (7), located opposite the external skin (6) comprises circumferential undulations arranged in the longitudinal direction and the crests (7b) of the corrugations carry rows of flexible columns (10) also integral with the outer skin (6) and located alternately, in the longitudinal direction, in line with a leading edge and a trailing edge stator vanes (9a to 9d) which are integral with the radially inner side of said inner skin (7). 2. - Carter de compresseur selon la revendication 1 caractérisé en ce que la peau intérieure (7) et la virole interne (8) sont constituées d'une multiplicité de secteurs (5a) assemblés, et en ce que chaque secteur (5a) comporte en plus desdites colonnettes (10), des éléments de liaison entre peau intérieure (7) et peau extérieure (6) constitués d'un bloc massif (12) disposé approximativement à son centre, de manière à former un point fixe autour duquel se répartissent les dilatations en fonctionnement et d'une première lamelle (11b) orientée dans le sens périphérique et d'une seconde lamelle (11a) orientée dans le sens longitudinal par rapport au carter (5), de manière à ce que les efforts résultant des couples s'exerçant en fonctionnement passent par lesdites lamelles (11a,11b).2. - Compressor housing according to claim 1 characterized in that the inner skin (7) and the inner shell (8) consist of a multiplicity of sectors (5a) assembled, and in that each sector (5a) comprises in addition to the said balusters (10), connecting elements between the inner skin (7) and the outer skin (6) consisting of a solid block (12) disposed approximately at its center, so as to form a fixed point around which are distributed the expansions in operation and of a first strip (11b) oriented in the peripheral direction and of a second strip (11a) oriented in the longitudinal direction relative to the casing (5), so that the forces resulting from the torques exerted in operation pass through said strips (11a, 11b). 3. - Carter de compresseur selon l'une des revendications 1 ou 2 caractérisé en ce que la peau extérieure (6) présente une forme géométrique régulière obtenue à partir d'une génératrice qui est une droite.3. - compressor housing according to one of claims 1 or 2 characterized in that the outer skin (6) has a regular geometric shape obtained from a generator which is a straight line. 4. - Carter de compresseur selon l'une des revendications 1 ou 2 caractérisé en ce que la peau extérieure (6) comporte également des ondulations circonférentielles dont le profil est homothétique de celui de la face ondulée de la peau intérieure (7) et sa face radialement interne comporte des nervures longitudinales (13), les colonnettes (10) de liaison étant implantées sur la peau extérieure (6) dans le creux des ondulations.4. - Compressor housing according to one of claims 1 or 2 characterized in that the outer skin (6) also comprises circumferential undulations whose profile is homothetic to that of the corrugated face of the inner skin (7) and its radially inner face has longitudinal ribs (13), the connecting columns (10) being located on the outer skin (6) in the hollow of the corrugations. 5. - Carter de compresseur selon l'une quelconque des revendications 1 à 4 caractérisé en ce que l'espace ménagé entre les peaux intérieure (7) et extérieure (6) est rempli d'un matériau isolant (18).5. - Compressor housing according to any one of claims 1 to 4 characterized in that the space formed between the inner skins (7) and outer (6) is filled with an insulating material (18). 6. - Procédé de fabrication d'un carter de compresseur conforme à l'une des revendications 1 à 5 caractérisé en ce que l'ensemble du carter (5) constitué des deux peaux, (6,7) des colonnettes (10) et éléments de liaison (11a,11b,12) et des aubes (9a à 9d) statoriques est obtenu monobloc en fonderie par un procédé du type coulée à la cireperdue, connu en soi, le noyau céramique (18) qui est utilisé pour la séparation des deux peaux (6,7) comportant des canaux radiaux préfigurant lesdites colonnettes (10) et éléments de liaison (11a,11b,12).6. - A method of manufacturing a compressor housing according to one of claims 1 to 5 characterized in that the entire housing (5) consisting of two skins, (6,7) columns (10) and connecting elements (11a, 11b, 12) and stator vanes (9a to 9d) is obtained as a single piece in foundry by a process of the lost-wax type, known per se, the ceramic core (18) which is used for separation two skins (6,7) comprising radial channels foreshadowing said columns (10) and connecting elements (11a, 11b, 12). 7. - Procédé de fabrication d'un carter de compresseur conforme à l'une des revendications 1 à 5 caractérisé en ce que l'ensemble du carter constitué des deux peaux (6,7), des colonnettes (10) et éléments de liaison (11a 11b,12) et des aubes (9a à 9d) statoriques est obtenu en deux parties séparées longitudinalement sous forme de deux demi-coquilles (6a,6b) obtenues en fonderie par un procédé du type coulée à la cire perdue, connu en soi, le noyau céramique (18) qui est utilisé pour la séparation des deux peaux (6,7) comportant des canaux radiaux préfigurant lesdites colonnettes (10) et éléments de liaison (11a,11b,12).7. - A method of manufacturing a compressor housing according to one of claims 1 to 5 characterized in that the entire housing consisting of two skins (6,7), balusters (10) and connecting elements (11a 11b, 12) and stator vanes (9a to 9d) is obtained in two parts separated longitudinally in the form of two half-shells (6a, 6b) obtained in foundry by a process of the lost wax casting type, known per se, the ceramic core (18) which is used for the separation of the two skins (6,7) comprising channels radials prefiguring said columns (10) and connecting elements (11a, 11b, 12). 8. - Carter de compresseur selon la revendication 5 caractérisé en ce que ledit matériau isolant (18) est constitué par ledit noyau céramique utilisé dans le procédé de fabrication selon l'une des revendications 6 ou 7.8. - compressor housing according to claim 5 characterized in that said insulating material (18) consists of said ceramic core used in the manufacturing process according to one of claims 6 or 7. 9. - Procédé de fabrication d'un carter de compresseur selon la revendication 6 caractérisé en ce que le carter monobloc (5) obtenu est coupé longitudinalement en deux parties puis des coupes délimitant une multiplicité de secteurs (5a) sont effectuées sur la peau intérieure (7) et sur la virole interne (8).9. - A method of manufacturing a compressor housing according to claim 6 characterized in that the one-piece housing (5) obtained is cut longitudinally into two parts and then cuts defining a multiplicity of sectors (5a) are made on the inner skin (7) and on the internal shell (8). 10 - Procédé de fabrication d'un carter de compresseur selon la revendication 7 caractérisé en ce que sur chaque demi-coquille (6a,6b) des coupes délimitant une multiplicité de secteurs (5a) sont effectuées sur la peau intérieure (7) et sur la virole interne (8).10 - A method of manufacturing a compressor housing according to claim 7 characterized in that on each half-shell (6a, 6b) cuts defining a multiplicity of sectors (5a) are made on the inner skin (7) and on the internal ferrule (8).
EP87402660A 1986-11-26 1987-11-25 Compressor housing adapted for active regulated thermal dilatation, and method for its production Expired - Lifetime EP0273790B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8616448 1986-11-26
FR8616448A FR2607198B1 (en) 1986-11-26 1986-11-26 COMPRESSOR HOUSING SUITABLE FOR ACTIVE PILOTAGE OF ITS EXPANSIONS AND MANUFACTURING METHOD THEREOF

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EP0273790A1 true EP0273790A1 (en) 1988-07-06
EP0273790B1 EP0273790B1 (en) 1990-01-24

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EP (1) EP0273790B1 (en)
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Also Published As

Publication number Publication date
EP0273790B1 (en) 1990-01-24
US4762462A (en) 1988-08-09
FR2607198B1 (en) 1990-05-04
DE3761493D1 (en) 1990-03-01
FR2607198A1 (en) 1988-05-27

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