EP0378943A1 - Kompressorgehäuse mit regelbarem Innendurchmesser für eine Turbomaschine - Google Patents

Kompressorgehäuse mit regelbarem Innendurchmesser für eine Turbomaschine Download PDF

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Publication number
EP0378943A1
EP0378943A1 EP89403573A EP89403573A EP0378943A1 EP 0378943 A1 EP0378943 A1 EP 0378943A1 EP 89403573 A EP89403573 A EP 89403573A EP 89403573 A EP89403573 A EP 89403573A EP 0378943 A1 EP0378943 A1 EP 0378943A1
Authority
EP
European Patent Office
Prior art keywords
casing
bellows
turbomachine
compressor
shells
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
EP89403573A
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English (en)
French (fr)
Other versions
EP0378943B1 (de
Inventor
Gilles Lucien Eugène Delrieu
Carmen Miraucourt
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 EP0378943A1 publication Critical patent/EP0378943A1/de
Application granted granted Critical
Publication of EP0378943B1 publication Critical patent/EP0378943B1/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
    • 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
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/21—Utilizing thermal characteristic, e.g., expansion or contraction, etc.

Definitions

  • the present invention relates to a turbomachine compressor casing provided with a device for controlling its internal diameter in order to ensure minimum objective radial clearance between rotor and compressor stator.
  • Adjustments of clearances in operation can thus be obtained by the use of thermal means, calling in particular on circulations of hot or cold air flows with adjustable flow rates as a function of determined parameters of operation of the turbomachine or of measurements. direct, these air flows are usually used to control the expansion / retraction of mechanical parts. Examples of these solutions are given by FR-A-2,534,982, FR-A-2,535,795 or FR-A-2,540,560.
  • mechanical means are used to vary the diameter of the housings or fixed parts located opposite the rotors or rotating parts of the turbomachine. This principle is for example applied by FR-A-2 577 282 or FR-A-2 591 674.
  • the object of the invention is to solve the problems mentioned above without incurring the drawbacks of the known prior solutions and in particular by allowing an advantageous application to the turbomachine compressor casings in two half-shells.
  • said complementary flexible connection means consist of a number N of flexible connection elements, each flexible element being associated with a bellows, being moreover hingedly fixed at each of its ends respectively on each casing half-shell. , on either side of the assembly flanges and forming a C element spanning said bellows.
  • said complementary flexible connection means consist of N pairs of lever arms, each articulated at a first end on a casing half-shell in the vicinity of the assembly flange and its second end being secured to a radially outer casing by means of an elastic flange.
  • a turbomachine compressor casing 1, schematically represented in FIG. 1, comprises, on the one hand, a radially external casing 2 comprising at each end of the radial flanges, respectively 3 and 4 , oriented towards the outside and assembled by any known means, such as bolts 5 and 6, with the flanges 7 and 8 of an adjacent casing and, on the other hand, an internal envelope 9, radially spaced from the previous one and which supports, according to a method of construction known per se in the production of axial compressors, a number of circular rows of fixed blades forming stator stages 10, 11, 12 which are three in number in the example shown in the Figure 1 and between which are interposed stages of movable blades 13, 14, 15 of the compressor rotor.
  • the external 2 and internal 9 envelopes are connected together, in a manner also known, by telescopic devices 16 with pins and grooves, at the level of radial lugs such as 17 and 18.
  • These connecting devices 16 are regularly distributed and six in number , for example in the embodiment shown in Figure 1, are arranged in two longitudinally spaced series.
  • the inner casing 9 of the casing consists of two half-shells 19 and 20 assembled together by remarkable means in accordance with the invention, constituting a device for controlling the internal diameter of the casing 1 of the compressor and shown in detail in the figures. 2 to 5.
  • Each half-shell 19 and 20 comprises, at each end, a longitudinal flange, respectively 21 and 22, located in the compressor assembled in a horizontal plane.
  • the flanges 21 and 22 of the half-shells are slightly spaced and in the space thus provided, a bellows 23 is arranged, as shown in the detail. enlarged in Figure 4.
  • the bellows 23 is secured at each end, respectively to one of the flanges 21 and 22 of the half-shells 19 and 20 of the housing. Spanning the bellows 23 and the flanges 21 and 22, a flexible connecting element 24, having the general shape of a C is further articulated at each of its ends 25 and 26, directly on a half-shell, respectively 19 and 20
  • the bellows 23 and the flexible elements 24 in the same number are, for example, four in number, in the embodiment shown in FIGS. 1 to 5.
  • An air supply duct, symbolized at 27, supplies each bellows 23 in air taken downstream of the compressor. As shown in Figure 4, the air inlet into the bellows 23 can be through an orifice 28 drilled in the flange 21 and through a chamber 29 formed at the inlet.
  • the seal between the two half-shells 19 and 20 is ensured by longitudinal tongues 30 arranged in the grooves provided in the thickness of the half-shells at their connection. Furthermore, safety devices each comprising a rod 31 forming a spacer between the flanges 21 and 22, and visible in FIGS. 4 and 5 are arranged so as to ensure a minimum internal diameter of the compressor housing.
  • the operating mode of the device for controlling the internal diameter of the casing according to the invention is as follows. Between the outer 2 and inner 9 casing casings, an air sampling carried out, for example, upstream of the casing 1 ensures a pressure P1. In each bellows 23, the supply 25 brings an air pressure P2. Each increase in flow pressure at the outlet of the compressor activates the control device and increases the internal diameter of the casing 1. The deformation and the elongation of the bellows 23 in fact exert moments on each flange 21 or 22 of the internal casing 9 of housing.
  • the half-shells 19 and 20 are deformed only in bending and an increase in diameter is obtained without ovalization, the half-shells 19 and 20 being separated by the bellows 23 while the flexible elements 24 retain them. Furthermore, in the telescopic connections 16 between the inner casing 9 and the outer casing 2 of the casing, a clearance is provided between the pins and the grooves, to allow non-radial movement of the pins in the grooves.
  • Figures 6 to 10 show a second embodiment of the invention for which , references increased by a hundred compared to those which were used in the description of the first mode will be given to designate parts or elements identical or of function analogous to those of the first mode.
  • the casing 101 of the turbomachine compressor is composed of an external casing 102, between two flanges 103 and 104, connected to the flanges 107 and 108 by bolts 105 and 106 and an internal casing 109 in two half-shells 119 and 120, carrying stator stages of fixed blades 110, 111, 112 and 112a between rotor stages of movable blades 113, 114, 115, 115a and 115b.
  • the two half-shells 119 and 120 also include the longitudinal flanges 121 and 122 slightly spaced and connected by bellows 123, supplied with air taken downstream from the compressor by a pipe 127.
  • the variant applied in this second embodiment relates to the complementary flexible connection means between the two flanges 121 and 122 of the two half-shells 119 and 120 of the internal envelope 109 of the compressor housing according to the invention.
  • said flexible connection means are constituted at each bellows 123, two lever arms 124a and 124b.
  • Each lever-arm 124a or 124b has one of its ends, respectively 125 and 126, articulated directly on a half-shell, respectively 119 and 120 and their other end 125a or 126a is secured to the outer casing 102 of the casing by a flange elastic 32.
  • the bellows 123 and the pairs associated with the same number of lever arms 124a and 124b are six in number.
  • the operating mode of the device for controlling the internal diameter of the casing is the same as that which was previously described for the first embodiment, with reference to FIGS. 1 to 5.
  • Another particularity of the second embodiment concerning the assembly of the assembly As shown in the detail in FIG. 10, elements 33 are used to hold the lever arms 124a or 124b in the docking position during the positioning of the elastic flange 32, these elements 33 then being eliminated.
  • the device for controlling the internal diameter of the compressor casing according to the invention can be combined with additional arrangements.
  • watertight walls, respectively 34 and 35 or 134 and 135, are arranged at each end of the casing, between the internal envelopes 9 or 109 and the external 2 or 102, thus forming a sealed enclosure between the two envelopes.
  • the air pressure P1 prevailing in this enclosure can then also be controlled by adding a valve to the air sample taken upstream of the casing and which supplies the enclosure, the control device for this valve, not shown in drawing, which can, for example, be controlled by an operating parameter of the turbomachine or a measurement of the real clearance in operation between the rotor and the compressor stator.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP89403573A 1988-12-21 1989-12-20 Kompressorgehäuse mit regelbarem Innendurchmesser für eine Turbomaschine Expired - Lifetime EP0378943B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8816888 1988-12-21
FR8816888A FR2640687B1 (fr) 1988-12-21 1988-12-21 Carter de compresseur de turbomachine a pilotage de son diametre interne

Publications (2)

Publication Number Publication Date
EP0378943A1 true EP0378943A1 (de) 1990-07-25
EP0378943B1 EP0378943B1 (de) 1992-06-10

Family

ID=9373220

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89403573A Expired - Lifetime EP0378943B1 (de) 1988-12-21 1989-12-20 Kompressorgehäuse mit regelbarem Innendurchmesser für eine Turbomaschine

Country Status (4)

Country Link
US (1) US5017088A (de)
EP (1) EP0378943B1 (de)
DE (1) DE68901768T2 (de)
FR (1) FR2640687B1 (de)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2653171B1 (fr) * 1989-10-18 1991-12-27 Snecma Carter de compresseur de turbomachine muni d'un dispositif de pilotage de son diametre interne.
US6691519B2 (en) 2000-02-18 2004-02-17 Siemens Westinghouse Power Corporation Adaptable modular gas turbine power plant
US7125223B2 (en) * 2003-09-30 2006-10-24 General Electric Company Method and apparatus for turbomachine active clearance control
US7260892B2 (en) * 2003-12-24 2007-08-28 General Electric Company Methods for optimizing turbine engine shell radial clearances
DE102004058487A1 (de) * 2004-12-04 2006-06-14 Mtu Aero Engines Gmbh Gasturbine
US10190499B2 (en) 2012-12-28 2019-01-29 United Technologies Corporation Axial tension system for a gas turbine engine case
US10309409B2 (en) * 2016-05-26 2019-06-04 Rolls-Royce Corporation Impeller shroud with pneumatic piston for clearance control in a centrifugal compressor
US10458429B2 (en) * 2016-05-26 2019-10-29 Rolls-Royce Corporation Impeller shroud with slidable coupling for clearance control in a centrifugal compressor
KR20190042071A (ko) * 2016-09-01 2019-04-23 애딕티브 로켓 코포레이션 적층 제조 연소 엔진
US10704560B2 (en) 2018-06-13 2020-07-07 Rolls-Royce Corporation Passive clearance control for a centrifugal impeller shroud
US10962024B2 (en) 2019-06-26 2021-03-30 Rolls-Royce Corporation Clearance control system for a compressor shroud assembly

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2458676A1 (fr) * 1979-06-06 1981-01-02 Mtu Muenchen Gmbh Dispositif d'etancheite pour l'intervalle peripherique d'une turbomachine a flux axial
GB2050527A (en) * 1979-05-29 1981-01-07 Gen Motors Corp Turbine blade tip seal assembly
FR2509373A1 (fr) * 1981-07-11 1983-01-14 Rolls Royce Couronne enveloppante reglable pour aubes mobiles de moteur a turbine a gaz
GB2169962A (en) * 1985-01-22 1986-07-23 Rolls Royce Blade tip clearance control
GB2195715A (en) * 1986-10-08 1988-04-13 Rolls Royce Plc Rotor blade tip-shroud

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1339482A (fr) * 1961-11-28 1963-10-04 Licentia Gmbh Joint de rotor à segments annulaires d'étanchéité radialement mobiles, notammentpour turbo-moteurs
GB2024336A (en) * 1978-05-30 1980-01-09 Rolls Royce Gas turbine rotor tip clearance control apparatus
JPS5820904A (ja) * 1981-07-29 1983-02-07 Hitachi Ltd ガスタ−ビン動翼先端シ−ル構造
FR2534982A1 (fr) * 1982-10-22 1984-04-27 Snecma Dispositif de controle des jeux d'un compresseur haute pression
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
FR2540560B1 (fr) * 1983-02-03 1987-06-12 Snecma Dispositif d'etancheite d'aubages mobiles de turbomachine
JPS61152907A (ja) * 1984-12-27 1986-07-11 Toshiba Corp タ−ビンのシ−ル部隙間調整装置
FR2577282B1 (fr) * 1985-02-13 1987-04-17 Snecma Carter de turbomachine associe a un dispositif pour ajuster le jeu entre rotor et stator
JPS62142808A (ja) * 1985-12-18 1987-06-26 Toshiba Corp ガスタ−ビンの間隙制御装置
FR2591674B1 (fr) * 1985-12-18 1988-02-19 Snecma Dispositif de reglage des jeux radiaux entre rotor et stator d'un compresseur

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2050527A (en) * 1979-05-29 1981-01-07 Gen Motors Corp Turbine blade tip seal assembly
FR2458676A1 (fr) * 1979-06-06 1981-01-02 Mtu Muenchen Gmbh Dispositif d'etancheite pour l'intervalle peripherique d'une turbomachine a flux axial
FR2509373A1 (fr) * 1981-07-11 1983-01-14 Rolls Royce Couronne enveloppante reglable pour aubes mobiles de moteur a turbine a gaz
GB2169962A (en) * 1985-01-22 1986-07-23 Rolls Royce Blade tip clearance control
GB2195715A (en) * 1986-10-08 1988-04-13 Rolls Royce Plc Rotor blade tip-shroud

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 10, no. 353 (M-539)(2409) 28 novembre 1986, & JP-A-61 152907 (TOSHIBA) 11 juillet 1986, *
PATENT ABSTRACTS OF JAPAN vol. 7, no. 98 (M-210)(1243) 26 avril 1983, & JP-A-58 20904 (HITACHI SEISAKUSHO) 07 février 1983, *

Also Published As

Publication number Publication date
EP0378943B1 (de) 1992-06-10
DE68901768D1 (de) 1992-07-16
US5017088A (en) 1991-05-21
FR2640687B1 (fr) 1991-02-08
FR2640687A1 (fr) 1990-06-22
DE68901768T2 (de) 1993-01-14

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