EP0273790A1 - 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
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
Authority
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
Other languages
English (en)
French (fr)
Other versions
EP0273790B1 (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
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 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/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.
  • 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.

Landscapes

  • 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)
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
FR8616448 1986-11-26
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

Publications (2)

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

Family

ID=9341216

Family Applications (1)

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

Country Status (4)

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

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US5180281A (en) * 1990-09-12 1993-01-19 United Technologies Corporation Case tying means for gas turbine engine
US5224824A (en) * 1990-09-12 1993-07-06 United Technologies Corporation Compressor case construction
US5238365A (en) * 1991-07-09 1993-08-24 General Electric Company Assembly for thermal shielding of low pressure turbine
US5174714A (en) * 1991-07-09 1992-12-29 General Electric Company Heat shield mechanism for turbine engines
US5201847A (en) * 1991-11-21 1993-04-13 Westinghouse Electric Corp. Shroud design
US5540547A (en) * 1994-06-23 1996-07-30 General Electric Company Method and apparatus for damping vibrations of external tubing of a gas turbine engine
DE4442157A1 (de) * 1994-11-26 1996-05-30 Abb Management Ag Verfahren und Vorrichtung zur Beeinflussung des Radialspieles der Beschaufelung in axialdurchströmten Verdichtern
US5655876A (en) * 1996-01-02 1997-08-12 General Electric Company Low leakage turbine nozzle
US5735671A (en) * 1996-11-29 1998-04-07 General Electric Company Shielded turbine rotor
KR20010072537A (ko) 1997-11-03 2001-07-31 칼 하인쯔 호르닝어 터빈 하우징 및 그 제조 방법
US6185925B1 (en) * 1999-02-12 2001-02-13 General Electric Company External cooling system for turbine frame
US6589600B1 (en) * 1999-06-30 2003-07-08 General Electric Company Turbine engine component having enhanced heat transfer characteristics and method for forming same
GB2365926B (en) * 2000-08-12 2004-12-08 Rolls Royce Plc A gas turbine engine blade containment assembly
GB0116988D0 (en) 2000-08-11 2001-09-05 Rolls Royce Plc A gas turbine engine blade containment assembly
GB2365925B (en) * 2000-08-11 2005-02-23 Rolls Royce Plc A gas turbine engine blade containment assembly
US6530744B2 (en) * 2001-05-29 2003-03-11 General Electric Company Integral nozzle and shroud
US6896483B2 (en) * 2001-07-02 2005-05-24 Allison Advanced Development Company Blade track assembly
DE10343049B3 (de) * 2003-09-16 2005-04-14 Eads Space Transportation Gmbh Brennkammer mit Kühleinrichtung und Verfahren zur Herstellung der Brennkammer
US8197186B2 (en) 2007-06-29 2012-06-12 General Electric Company Flange with axially extending holes for gas turbine engine clearance control
US8393855B2 (en) 2007-06-29 2013-03-12 General Electric Company Flange with axially curved impingement surface for gas turbine engine clearance control
US8434997B2 (en) * 2007-08-22 2013-05-07 United Technologies Corporation Gas turbine engine case for clearance control
DE102008043605B4 (de) * 2007-11-16 2015-05-07 Alstom Technology Ltd. Verfahren zur Herstellung eines Turbinengehäuses
EP2159384A1 (de) * 2008-08-27 2010-03-03 Siemens Aktiengesellschaft Leitschaufelträger für eine Gasturbine
US20110097199A1 (en) * 2009-10-27 2011-04-28 Ballard Jr Henry G System and method to insulate turbines and associated piping
US9115600B2 (en) * 2011-08-30 2015-08-25 Siemens Energy, Inc. Insulated wall section
US9157331B2 (en) * 2011-12-08 2015-10-13 Siemens Aktiengesellschaft Radial active clearance control for a gas turbine engine
ITTO20120519A1 (it) * 2012-06-14 2013-12-15 Avio Spa Turbina a gas per motori aeronautici
JP5306532B1 (ja) * 2012-10-24 2013-10-02 三菱電機株式会社 内燃機関の制御装置および制御方法
ITFI20130118A1 (it) * 2013-05-21 2014-11-22 Nuovo Pignone Srl "compressor with a thermal shield and methods of operation"
US10202870B2 (en) 2013-11-14 2019-02-12 United Technologies Corporation Flange relief for split casing
US20160326915A1 (en) * 2015-05-08 2016-11-10 General Electric Company System and method for waste heat powered active clearance control
EP3153671A1 (de) 2015-10-08 2017-04-12 MTU Aero Engines GmbH Schutzvorrichtung für eine strömungsmaschine
US10683772B2 (en) * 2016-06-21 2020-06-16 Rolls-Royce North American Technologies Inc. Intercooling for an axial compressor with radially outer annulus
US10822991B2 (en) * 2016-08-01 2020-11-03 General Electric Company Method and apparatus for active clearance control on gas turbine engines
EP3712380A1 (de) * 2019-03-19 2020-09-23 MTU Aero Engines GmbH Komponente für ein flugzeugtriebwerk, ein modul eines flugzeugtriebwerks mit einer solchen komponente und fertigungsverfahren für diese komponente mittels additiver fertigung

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Publication number Priority date Publication date Assignee Title
FR975879A (fr) * 1948-12-06 1951-03-12 Const Et D Equipements Mecaniq Perfectionnement dans la construction des cylindres pour turbines à gaz
US3319930A (en) * 1961-12-19 1967-05-16 Gen Electric Stator assembly for turbomachines
FR2167837A1 (de) * 1972-01-12 1973-08-24 Rolls Royce
US4131388A (en) * 1977-05-26 1978-12-26 United Technologies Corporation Outer air seal
FR2422026A1 (fr) * 1978-04-04 1979-11-02 Rolls Royce Carter du turbomoteur
FR2482661A1 (fr) * 1980-05-16 1981-11-20 United Technologies Corp Assemblage directeur d'ecoulement pour une turbine a gaz
FR2482662A1 (fr) * 1980-05-16 1981-11-20 Mtu Muenchen Gmbh Carter exterieur pour compresseur axial ou turbine axiale d'une machine fluidique
FR2516980A1 (fr) * 1981-11-26 1983-05-27 Rolls Royce Carters pour rotors de turbomachines
GB2115487A (en) * 1982-02-19 1983-09-07 Gen Electric Double wall compressor casing
US4411594A (en) * 1979-06-30 1983-10-25 Rolls-Royce Limited Support member and a component supported thereby
FR2534982A1 (fr) * 1982-10-22 1984-04-27 Snecma Dispositif de controle des jeux d'un compresseur haute pression

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US3335483A (en) * 1961-12-19 1967-08-15 Gen Electric Method of manufacturing a stator assembly for turbomachines
US3892497A (en) * 1974-05-14 1975-07-01 Westinghouse Electric Corp Axial flow turbine stationary blade and blade ring locking arrangement
GB1501916A (en) * 1975-06-20 1978-02-22 Rolls Royce Matching thermal expansions of components of turbo-machines
GB1553038A (en) * 1977-04-28 1979-09-19 Snecma Drum for an axial flow compressor rotor and process for its manufacture
US4426191A (en) * 1980-05-16 1984-01-17 United Technologies Corporation Flow directing assembly for a gas turbine engine
US4431373A (en) * 1980-05-16 1984-02-14 United Technologies Corporation Flow directing assembly for a gas turbine engine
US4522559A (en) * 1982-02-19 1985-06-11 General Electric Company Compressor casing
FR2535795B1 (fr) * 1982-11-08 1987-04-10 Snecma Dispositif de suspension d'aubes statoriques de compresseur axial pour le controle actif des jeux entre rotor et stator
FR2577282B1 (fr) * 1985-02-13 1987-04-17 Snecma Carter de turbomachine associe a un dispositif pour ajuster le jeu entre rotor et stator

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR975879A (fr) * 1948-12-06 1951-03-12 Const Et D Equipements Mecaniq Perfectionnement dans la construction des cylindres pour turbines à gaz
US3319930A (en) * 1961-12-19 1967-05-16 Gen Electric Stator assembly for turbomachines
FR2167837A1 (de) * 1972-01-12 1973-08-24 Rolls Royce
US4131388A (en) * 1977-05-26 1978-12-26 United Technologies Corporation Outer air seal
FR2422026A1 (fr) * 1978-04-04 1979-11-02 Rolls Royce Carter du turbomoteur
US4411594A (en) * 1979-06-30 1983-10-25 Rolls-Royce Limited Support member and a component supported thereby
FR2482661A1 (fr) * 1980-05-16 1981-11-20 United Technologies Corp Assemblage directeur d'ecoulement pour une turbine a gaz
FR2482662A1 (fr) * 1980-05-16 1981-11-20 Mtu Muenchen Gmbh Carter exterieur pour compresseur axial ou turbine axiale d'une machine fluidique
FR2516980A1 (fr) * 1981-11-26 1983-05-27 Rolls Royce Carters pour rotors de turbomachines
GB2115487A (en) * 1982-02-19 1983-09-07 Gen Electric Double wall compressor casing
FR2534982A1 (fr) * 1982-10-22 1984-04-27 Snecma Dispositif de controle des jeux d'un compresseur haute pression

Also Published As

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

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