EP0795681A1 - Antriebsvorrichtung für verstellbare Leitschaufeln eines Turbomaschinenkompressors - Google Patents

Antriebsvorrichtung für verstellbare Leitschaufeln eines Turbomaschinenkompressors Download PDF

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Publication number
EP0795681A1
EP0795681A1 EP97400549A EP97400549A EP0795681A1 EP 0795681 A1 EP0795681 A1 EP 0795681A1 EP 97400549 A EP97400549 A EP 97400549A EP 97400549 A EP97400549 A EP 97400549A EP 0795681 A1 EP0795681 A1 EP 0795681A1
Authority
EP
European Patent Office
Prior art keywords
platform
pivot
manifold
hollow
control device
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
EP97400549A
Other languages
English (en)
French (fr)
Other versions
EP0795681B1 (de
Inventor
Frédéric Paul Eichstadt
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 EP0795681A1 publication Critical patent/EP0795681A1/de
Application granted granted Critical
Publication of EP0795681B1 publication Critical patent/EP0795681B1/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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/60—Shafts
    • F05D2240/61—Hollow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/74—Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line

Definitions

  • the invention relates to a pivot control device integrated in a manifold. It applies in particular in the field of aeronautics, to turbomachinery comprising an air intake guide vane with variable pitch vanes.
  • Some turbomachines have variable-pitch guide vanes that regulate the air flow supplying the compressor stages located downstream.
  • the blades have pivots which extend through an envelope delimiting a flow vein.
  • Each pivot is driven in rotation by means of a link connected to a control mechanism such as a ring whose movement causes all the links to tilt in unison.
  • the object of the invention is to solve this problem and to produce a control device for a pivot integrated in a manifold allowing the defrosting of the moving blades and simultaneously ensuring the orientation of the moving blades.
  • the control device comprises means for fixing and articulation of the pivot mounted in a bore of a platform fixed to the manifold by upstream flanges and downstream.
  • the pivot fixing and articulation means comprise a hollow friction sleeve provided with a circumferential slot in which is inserted an upstream part of a link.
  • Means for controlling the orientation of the movable blades are mounted outside the manifold and connected to a downstream part of the link.
  • Corresponding lights are arranged in the manifold and in the platform so as to ensure the maneuverability of the variable-timing control device by means of the link.
  • the upstream part of the rod is inserted into the bore of the platform by the lights of the manifold and of the platform and comprises an eye in which the hollow pivot is inserted.
  • the lights of the collector and of the platform are arranged opposite the slot of the hollow socket.
  • downstream part of the link is arranged outside the manifold and connected on the one hand to the upstream part of the link and on the other hand to the means for controlling the orientation of the movable blades.
  • Defrosting of the movable blade is ensured by means of the hollow pivot which allows the circulation of hot air between the manifold and the interior of the blades.
  • the flange-to-flange fastenings between the manifold and the platform provide sealing between the interior and exterior of the manifold.
  • the control device for a pivot integrated in an air manifold in which the pivot of a movable blade with variable setting is driven in rotation by means of a connecting rod connected to means for controlling the orientation of the movable blade and comprising means for fixing and pivot articulation mounted in a bore of a platform fixed to the air collector by upstream and downstream flanges is characterized in that the fixing means and pivot articulation comprise a hollow friction sleeve fixed in the bore of the platform, the hollow socket having a circumferential slot in which is inserted an upstream part of the link.
  • the air intake of the turbojet engine is provided with fixed arms 1 and guide vanes 2 movable around a radial axis XX 'passing through pivots 3 located at the upper ends movable blades 2.
  • the fixed arms 1, the movable vanes 2 and the pivots 3 are hollow so as to allow the circulation of the hot defrost air taken at the outlet of the high pressure compressor not shown.
  • the fixed arms 1 and the pivots 3 of the movable vanes 2 are mounted in external platforms 4 brought into contact with one another, and are capped by an air manifold 5 secured to an external ferrule 6.
  • the platforms 4 comprise two upstream 7 and downstream 8 side flanges which are fixed to corresponding flanges of the manifold 5 for example by means of a screw and nut system.
  • the platforms 4 form with the manifold 5 a toroidal enclosure which receives, contains and distributes the deicing air from the fixed arms 1 and the movable vanes 2.
  • the seal between the inside and the outside of the manifold is ensured by the flange against flange fixings between the manifold 5 and the platforms 4.
  • Each platform 4 has on its external face, between the two lateral flanges 7,8, a thick transverse region traversed by two bores 9, 10 , respectively upstream and downstream oriented radially.
  • the fixed arms 1 are embedded and bolted in the first upstream bore 9 of the thickened region of the platform 4.
  • the pivots 3 of the movable blades 2 are mounted in the second downstream bore 10 and pivot in this second bore via a hollow friction sleeve 11 secured to the platform 4.
  • the pivoting of the pivots 3 of the movable vanes 2 around the radial axis XX ' is controlled by a rod made up of two parts respectively upstream 12 and downstream 13.
  • the upstream parts 12 and downstream 13 are respectively arranged inside and outside the manifold 5.
  • the upstream portion 12 is inserted into the bore 10 of the platform 4 by means of lights made respectively in the manifold 5, in the platform 4 and in the hollow friction sleeve 11, the different lights being arranged opposite one another.
  • the downstream part 13 is connected by a first end to the upstream part 12 by means of a locking lock nut 14 and comprises a second end movable linearly in a ball joint 15 secured to a control and synchronization ring 16
  • the control of the pivoting of all the movable blades is carried out simultaneously via the control ring in a manner known per se.
  • FIG. 2 represents a perspective and exploded view of the means of fixing and articulation of the pivots of the movable blades, according to the invention.
  • the articulation of the pivot 3 of a movable blade 2 inside the downstream bore 10 of the platform 4 is effected by means of a hollow friction sleeve 11.
  • the hollow sleeve comprises, in its upper region, a slit 20 circumferential of predetermined width.
  • the hollow socket 11 is put in place and fixed in the downstream bore 10 of the platform 4 so that the slot 20 is disposed opposite the light 21 of the platform 4.
  • the upstream part 12 of the link has a flat area pierced at its end with an eye 22 of predetermined shape and section, for example in the shape of a square. This flat area is inserted into the downstream bore 10 of the platform 4 via the lumen 21 of the platform and the slot 20 of the hollow bushing 11.
  • a hollow tip 17 is permanently fixed, for example by shrinking, on the pivot 3 of the movable blade 2.
  • the tip 17 has a threaded upper part 18, an intermediate part 19 of predetermined shape and section, and a lower part in which the pivot 3 is fitted.
  • the shape of the intermediate part 19 is complementary to the shape of the eye 22 of the upstream part 12 of the link and its section is slightly smaller than that of the eye 22 so that when the pivot 3 provided with its end piece 17 is put in place in the bore 10 of the platform 4, the intermediate part 19 fits into the eye 22 of the link 12, the eye 22 fitting exactly the shape of the intermediate part 19 of the end piece 17.
  • the pivot 3 of the moving blade 2 and the upstream part 12 of the link are made integral in rotation by a tightening means, for example a shouldered nut 23 screwed onto the threaded upper part 18 of the end piece 17.
  • the orientation of the blades In order for the orientation of the blades to be carried out with precision, it is necessary for the orientation of the intermediate part 19 of the end piece 17 to be carried out precisely relative to the movable blade 2. Likewise, the slot 20 of the socket 11 must be oriented very precisely with respect to the platform 4. For this purpose, it is preferable to use a mounting tool or a polarizing device.
  • the platform 4 When the pivot 2 provided with its end piece 17 is mounted in the platform 4 with the friction sleeve 11, the upstream part 12 of the connecting rod and the tightening nut 23, the platform 4 is put in place in the manifold 5 and the upstream side 7 and downstream 8 side flanges are fixed to corresponding flanges of the manifold 5.
  • the side flanges 7, 8 have several holes 24 in which are inserted in known manner fixing means not shown.
  • holes 25 are provided for fixing the different platforms to one another.
  • the downstream part 13 of the link disposed outside the manifold 5 is then fixed by a first end to the upstream part 12, for example by screwing then tightening by means of a lock nut 14.
  • the downstream part 13 of the link comprises a second end, for example of square section, linked to means, not shown in FIG. 2, for controlling and synchronizing the pivoting of the blades by means of the ball joint 15 secured to the control ring 16.
  • Figure 3 is a perspective view of the means of fixing and articulation of the pivots of the movable blades after mounting in the platform, according to the invention.
  • the pivots 3 of the blades, the bush 11 and the clamping nut 23 are all hollow, they allow the arrival of the hot defrost air inside the movable blades.
  • the slot 20 of the socket 11 and the light 21 of the platform 4 allow the maneuverability of the device variable pitch control of the vanes which is located outside the manifold 5.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
EP97400549A 1996-03-14 1997-03-13 Antriebsvorrichtung für verstellbare Leitschaufeln eines Turbomaschinenkompressors Expired - Lifetime EP0795681B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9603203A FR2746141B1 (fr) 1996-03-14 1996-03-14 Dispositif de commande pour pivot integre dans un collecteur
FR9603203 1996-03-14

Publications (2)

Publication Number Publication Date
EP0795681A1 true EP0795681A1 (de) 1997-09-17
EP0795681B1 EP0795681B1 (de) 2000-04-26

Family

ID=9490178

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97400549A Expired - Lifetime EP0795681B1 (de) 1996-03-14 1997-03-13 Antriebsvorrichtung für verstellbare Leitschaufeln eines Turbomaschinenkompressors

Country Status (5)

Country Link
US (1) US5795128A (de)
EP (1) EP0795681B1 (de)
CA (1) CA2197398C (de)
DE (1) DE69701759T2 (de)
FR (1) FR2746141B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1867877A1 (de) * 2006-06-16 2007-12-19 Ansaldo Energia S.P.A. Verdichter einer Gastubine
FR2975435A1 (fr) * 2011-05-16 2012-11-23 Snecma Dispositif de degivrage d'un bec de separation de turbomachine
CN114458450A (zh) * 2022-02-10 2022-05-10 中国航发沈阳发动机研究所 一种航空发动机进气机匣防冰结构

Families Citing this family (22)

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SE512085C2 (sv) * 1998-05-28 2000-01-24 Abb Ab Rotormaskininrättning
US6019574A (en) * 1998-08-13 2000-02-01 General Electric Company Mismatch proof variable stator vane
FR2784711B1 (fr) 1998-10-16 2001-01-05 Techlam Dispositif de commande d'aubes a angle de calage variable
FR2793521B1 (fr) 1999-05-10 2005-09-23 Techlam Biellette de commande d'aube a calage variable
US6382906B1 (en) * 2000-06-16 2002-05-07 General Electric Company Floating spoolie cup impingement baffle
FR2814205B1 (fr) 2000-09-18 2003-02-28 Snecma Moteurs Turbomachine a veine d'ecoulement ameliore
FR2814206B1 (fr) * 2000-09-18 2002-12-20 Snecma Moteurs Dispositif de commande d'aubes a calage variable
JP3482196B2 (ja) * 2001-03-02 2003-12-22 三菱重工業株式会社 可変容量タービンの組立・調整方法およびその装置
FR2835294B1 (fr) * 2002-01-29 2004-04-16 Snecma Moteurs Dispositif de commande d'aube a angle de calage variable a liaison sans jeu
FR2835295B1 (fr) 2002-01-29 2004-04-16 Snecma Moteurs Dispositif de commande d'aube a angle de calage variable a liaison par pincement pour redresseur de compresseur de turbomachine
US7186072B2 (en) * 2002-08-23 2007-03-06 Mtu Aero Engines Gmbh Recirculation structure for a turbocompressor
DE10243103A1 (de) * 2002-09-17 2004-03-25 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Verstellung von Kompressorschaufeln einer Gasturbine
GB0312098D0 (en) * 2003-05-27 2004-05-05 Rolls Royce Plc A variable arrangement for a turbomachine
FR2857699B1 (fr) * 2003-07-17 2007-06-29 Snecma Moteurs Dispositif de degivrage pour aube de roue directrice d'entree de turbomachine, aube dotee d'un tel dispositif de degivrage, et moteur d'aeronef equipe de telles aubes
FR2862338B1 (fr) * 2003-11-17 2007-07-20 Snecma Moteurs Dispositif de liaison entre un distributeur et une enceinte d'alimentation pour injecteurs de fluide de refroidissement dans une turbomachine
FR2880926A1 (fr) * 2005-01-14 2006-07-21 Snecma Moteurs Sa Dispositif de prelevement d'air sur une aube pivotante de stator de machine
EP2058524A1 (de) * 2007-11-12 2009-05-13 Siemens Aktiengesellschaft Kompressor mit veränderlichen Leitschaufeln mit Zapfluftsystem
US10704411B2 (en) 2018-08-03 2020-07-07 General Electric Company Variable vane actuation system for a turbo machine
FR3112368B1 (fr) 2020-07-08 2022-08-05 Safran Aircraft Engines Entrée d'air pour une turbomachine d’aéronef, une turbomachine d'aéronef équipée d’une telle entrée d’air et son procédé de maintenance
FR3115561B1 (fr) 2020-10-23 2023-04-21 Safran Aircraft Engines Aubage d’entrée d'air pour une turbomachine d’aéronef, turbomachine d'aéronef équipée d’un tel aubage d’entrée d’air et son procédé de fabrication
CN113530888B (zh) * 2021-08-24 2022-08-09 中国航发湖南动力机械研究所 一种带防冰功能的多腔室集成化导叶机匣结构
US11698024B1 (en) 2022-05-10 2023-07-11 Pratt & Whitney Canada Corp. System and method of anti-icing inlet guide vanes

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FR1053647A (fr) * 1952-04-05 1954-02-03 Snecma Perfectionnements aux propulseurs à turbine à gaz
DE920614C (de) * 1945-03-08 1954-11-25 Daimler Benz Ag Schwenkbare Leitschaufel, insbesondere fuer Kuehl- und Aufladegeblaese von Luftfahrzeugen
US2823700A (en) * 1954-11-19 1958-02-18 Westinghouse Electric Corp Fluid flow control apparatus
US2858062A (en) * 1955-01-24 1958-10-28 Gen Electric Variable stator mechanism
US4139329A (en) * 1977-05-16 1979-02-13 Westinghouse Canada Limited Vane tip motion transfer device
FR2599785A1 (fr) * 1986-06-04 1987-12-11 Snecma Aubage directeur d'entree d'air a calage variable pour turboreacteur
EP0546935A1 (de) * 1991-12-11 1993-06-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Stator zur Einführung von Luft in das Innere einer Turbomaschine und Verfahren zum Montieren einer Schaufel dieses Stators
US5316438A (en) * 1993-01-29 1994-05-31 Industria De Turbo Propulsores S.A. Gas turbine engine variable aerofoil vane actuation mechanism

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US4193738A (en) * 1977-09-19 1980-03-18 General Electric Company Floating seal for a variable area turbine nozzle
DE2810240C2 (de) * 1978-03-09 1985-09-26 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Verstelleitgitter für axial durchströmte Turbinen, insbesondere Hochdruckturbinen von Gasturbinentriebwerken
US4214851A (en) * 1978-04-20 1980-07-29 General Electric Company Structural cooling air manifold for a gas turbine engine
FR2631386A1 (fr) * 1988-05-11 1989-11-17 Snecma Turbomachine comportant une grille d'entree incorporant des tubes de passage d'huile
US5492446A (en) * 1994-12-15 1996-02-20 General Electric Company Self-aligning variable stator vane
US5593275A (en) * 1995-08-01 1997-01-14 General Electric Company Variable stator vane mounting and vane actuation system for an axial flow compressor of a gas turbine engine

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE920614C (de) * 1945-03-08 1954-11-25 Daimler Benz Ag Schwenkbare Leitschaufel, insbesondere fuer Kuehl- und Aufladegeblaese von Luftfahrzeugen
FR1053647A (fr) * 1952-04-05 1954-02-03 Snecma Perfectionnements aux propulseurs à turbine à gaz
US2823700A (en) * 1954-11-19 1958-02-18 Westinghouse Electric Corp Fluid flow control apparatus
US2858062A (en) * 1955-01-24 1958-10-28 Gen Electric Variable stator mechanism
US4139329A (en) * 1977-05-16 1979-02-13 Westinghouse Canada Limited Vane tip motion transfer device
FR2599785A1 (fr) * 1986-06-04 1987-12-11 Snecma Aubage directeur d'entree d'air a calage variable pour turboreacteur
EP0546935A1 (de) * 1991-12-11 1993-06-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Stator zur Einführung von Luft in das Innere einer Turbomaschine und Verfahren zum Montieren einer Schaufel dieses Stators
US5316438A (en) * 1993-01-29 1994-05-31 Industria De Turbo Propulsores S.A. Gas turbine engine variable aerofoil vane actuation mechanism

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1867877A1 (de) * 2006-06-16 2007-12-19 Ansaldo Energia S.P.A. Verdichter einer Gastubine
WO2007144430A1 (en) * 2006-06-16 2007-12-21 Ansaldo Energia S.P.A. Gas turbine compressor
US8075253B2 (en) 2006-06-16 2011-12-13 Ansaldo Energia S.P.A. Gas turbine compressor
FR2975435A1 (fr) * 2011-05-16 2012-11-23 Snecma Dispositif de degivrage d'un bec de separation de turbomachine
CN114458450A (zh) * 2022-02-10 2022-05-10 中国航发沈阳发动机研究所 一种航空发动机进气机匣防冰结构

Also Published As

Publication number Publication date
CA2197398C (fr) 2004-04-27
EP0795681B1 (de) 2000-04-26
FR2746141A1 (fr) 1997-09-19
FR2746141B1 (fr) 1998-04-17
DE69701759D1 (de) 2000-05-31
US5795128A (en) 1998-08-18
DE69701759T2 (de) 2000-11-30
CA2197398A1 (fr) 1997-09-15

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