EP0273790B1 - Kompressorgehäuse, dessen Ausdehnung sich thermisch steuern lässt und seine Herstellungsweise - Google Patents

Kompressorgehäuse, dessen Ausdehnung sich thermisch steuern lässt und seine Herstellungsweise Download PDF

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Publication number
EP0273790B1
EP0273790B1 EP87402660A EP87402660A EP0273790B1 EP 0273790 B1 EP0273790 B1 EP 0273790B1 EP 87402660 A EP87402660 A EP 87402660A EP 87402660 A EP87402660 A EP 87402660A EP 0273790 B1 EP0273790 B1 EP 0273790B1
Authority
EP
European Patent Office
Prior art keywords
casing
skin
accordance
columns
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.)
Expired - Lifetime
Application number
EP87402660A
Other languages
English (en)
French (fr)
Other versions
EP0273790A1 (de
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
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0273790A1 publication Critical patent/EP0273790A1/de
Application granted granted Critical
Publication of EP0273790B1 publication Critical patent/EP0273790B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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.
  • 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 located 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 an axial type of a kind intended to provide the compression function in a turbomachine which may be in particular for aeronautical use is shown in FIG. 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 casing 5 of compressor, 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.
  • stator vanes 9a, 9b, 9c and 9d there will therefore be two rows of each eight sectors of blades, juxtaposed longitu ultimately to form the compressor casing 5 and the stator vane stages 9a, 9b, 9c and 9d are arranged between the inner skin 7 and the inner shell 8.
  • the cooperating edges 5b and 5c of the sectors 5a have respective profiles in Z as shown in Figure 3.
  • 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, 19th, 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 whole of the casing 5 constituted by 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 foundry process of the casting type. 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)

Claims (10)

1. Doppelwandiges, eine aktive Steuerung seiner Ausdehnungen ermöglichendes Axialverdichtergehäuse, das in einem von einem inneren Ring (8) begrenzten Gaszirkulationsstrom Stufen von Statorschaufeln trägt, wobei dem inneren Ring (8) äußere Rampen (19a bis 19g) zur Kühlung durch Luftströme zugeordnet sind, dadurch gekennzeichnet, daß die der Außenwandung (6) zugewandte Seite der Innenwandung (7) ein Profil in Form von in Umfangrichtung verlaufenden Wellen aufweist, die in Längsrichtung angeordnet sind, wobei die Scheitel (7b) dieser Wellen Reihen von flexiblen Säulen (10) tragen, die auch mit der Außenwandung (6) fest verbunden sind und in Längsrichtung abwechselnd an der Stelle einer Vorderkante und einer Hinterkante der Statorschaufeln (9a bis 9d) angeordnet sind, wobei letztere mit der radial innenliegenden Seite der genannten Innenwandung (7) fest verbunden sind.
2. Verdichtergehäuse nach Anspruch 1, dadurch gekennzeichnet, daß die Innenwandung (7) und der innere Ring (8) aus einer Vielzahl von zusammengefügten Sektoren (5a) besteht, und daß jeder Sektor (5a) zusätzlich zu den genannten Säulen (10) Elemente zur Verbindung der Innenwandung (7) und der Außenwandung (6) aufweist, die aus einem massiven Block (12) bestehen, der annähernd im Zentrum des betreffenden Sektors angeordnet ist, so daß er einen festen Punkt bildet, um den sich die Ausdehnungen im Betrieb verteilen, ferner aus einer ersten, in Umfangsrichtung des Gehäuses orientierten Lamelle (11 b) und einer zweiten in Längsrichtung des Gehäuses orientierten Lamelle (11 a), so daß die aus dem im Betrieb auftretenden Momenten resultierenden Kräfte durch diese Lamellen (11 a, 11 b) verlaufen.
3. Verdichtergehäuse nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, daß die Außenwandung (6) eine regelmäßige geometrische Form hat, die aus einer von einer Geraden gebildeten Erzeugenden hervorgeht.
4. Verdichtergehäuse nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, daß die Außenwandung (6) ebenfalls ein zu dem Profil der wellenförmigen Seite der Innenwandung (7) homothetisches Profil mit umlaufenden Wellen aufweist und ihre radial innere Seite Längsrippen (13) aufweist und daß die Verbindungssäulen (10) an der Außenwandung (6) in den Vertiefungen der Wellen eingesetzt sind.
5. Verdichtergehäuse nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß der Raum zwischen der Innenwandung (7) und der Außenwandung (6) mit einem lsolierwerkstoff (18) ausgefüllt ist.
6. Verfahren zur Herstellung eines Verdichtergehäuses nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß die aus den beiden Wandungen (6, 7), den Säulen (10), den Verbindungselementen (11 a, 11 b, 12) und den Statorschaufeln (9a bis 9d) bestehende Gehäuseeinheit als einstückiger Gußblock durch ein an sich bekanntes Gießverfahren mit verlorener Wachsform hergestellt wird, wobei ein für die Trennung der beiden Wandungen (6, 7) verwendeter Keramikkern (18) radiale Kanäle zur Bildung der Säulen (10) und der Verbindungselemente (11 a, 11 b, 12) aufweist.
7. Verfahren zur Herstellung eines Verdichtergehäuses nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß die aus den beiden Wandungen (6, 7), den Säulen (10), den Verbindungselementen (11 a, 11 b, 12) und den Statorschaufeln (9a bis 9d) bestehende Gehäuseeinheit durch ein an sich bekanntes Gießverfahren mit verlorener Wachsform in zwei in Längsrichtung geteilten Teilen in Form von Halbschalen (6a, 6b) hergestellt wird, wobei ein für die Trennung der beiden Wandungen (6, 7) verwendeter Keramikkern (18) radiale Kanäle zur Bildung der Säulen (10) und der Verbindungselemente (11 a, 11 b, 12) aufweist.
8. Verdichtergehäuse nach Anspruch 5, dadurch gekennzeichnet, daß der Isolierwerkstoff (18) von dem Keramikkern gebildet ist, der bei dem Herstellungsverfahren nach einem der Ansprüche 6 oder 7 verwendet wird.
9. Verfahren zur Herstellung eines Verdichtergehäuses nach Anspruch 6, dadurch gekennzeichnet, daß das als einstückiger Block (5) hergestellte Gehäuse in Längsrichtung in zwei Teile getrennt wird und daß dann durch die Innenwandung (7) und den inneren Ring (8) verlaufende Schnitte ausgeführt werden, die eine Mehrzahl von Sektoren (5a) begrenzen.
10. Verfahren zur Herstellung eines Verdichtergehäuses nach Anspruch 7, dadurch gekennzeichnet, daß an jeder Halbschale (6a, 6b) Schnitte durch die Innenwandung (7) und den inneren Ring (8) ausgeführt werden, die eine Mehrzahl von Sektoren (5a) begrenzen.
EP87402660A 1986-11-26 1987-11-25 Kompressorgehäuse, dessen Ausdehnung sich thermisch steuern lässt und seine Herstellungsweise Expired - Lifetime EP0273790B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8616448A FR2607198B1 (fr) 1986-11-26 1986-11-26 Carter de compresseur adapte pour le pilotage actif de ses dilatations et son procede de fabrication
FR8616448 1986-11-26

Publications (2)

Publication Number Publication Date
EP0273790A1 EP0273790A1 (de) 1988-07-06
EP0273790B1 true EP0273790B1 (de) 1990-01-24

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EP87402660A Expired - Lifetime EP0273790B1 (de) 1986-11-26 1987-11-25 Kompressorgehäuse, dessen Ausdehnung sich thermisch steuern lässt und seine Herstellungsweise

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Country Link
US (1) US4762462A (de)
EP (1) EP0273790B1 (de)
DE (1) DE3761493D1 (de)
FR (1) FR2607198B1 (de)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4442157A1 (de) * 1994-11-26 1996-05-30 Abb Management Ag Verfahren und Vorrichtung zur Beeinflussung des Radialspieles der Beschaufelung in axialdurchströmten Verdichtern

Also Published As

Publication number Publication date
DE3761493D1 (de) 1990-03-01
US4762462A (en) 1988-08-09
EP0273790A1 (de) 1988-07-06
FR2607198A1 (fr) 1988-05-27
FR2607198B1 (fr) 1990-05-04

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