EP0395498A1 - Verstellvorrichtung für schwenkbare Leitschaufeln mit eingebautem Drehteller - Google Patents

Verstellvorrichtung für schwenkbare Leitschaufeln mit eingebautem Drehteller Download PDF

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Publication number
EP0395498A1
EP0395498A1 EP90401108A EP90401108A EP0395498A1 EP 0395498 A1 EP0395498 A1 EP 0395498A1 EP 90401108 A EP90401108 A EP 90401108A EP 90401108 A EP90401108 A EP 90401108A EP 0395498 A1 EP0395498 A1 EP 0395498A1
Authority
EP
European Patent Office
Prior art keywords
blade
cup
casing
turbomachine
variable setting
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
EP90401108A
Other languages
English (en)
French (fr)
Other versions
EP0395498B1 (de
Inventor
Jacky Naudet
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 EP0395498A1 publication Critical patent/EP0395498A1/de
Application granted granted Critical
Publication of EP0395498B1 publication Critical patent/EP0395498B1/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

Definitions

  • the present invention relates to a stator blade with variable setting for a turbomachine and more precisely means for producing such a blade so that its manufacture is less expensive.
  • variable-pitch blades of the turbojet stator resemble those shown in FIGS. 1 and 2, showing the state of the art of the present application.
  • a blade 1 whose blade 2, with variable setting, is mounted in the casing 3 of a turbomachine.
  • the blade has a pivot control rod 4 which passes through the bore 5 of a boss 6 of the casing 3.
  • the blade has a head “matrix” 7 arranged in a counterboring 8 of the casing.
  • the "plate” 7 is machined in one piece with the rest of the blade and its diameter is generally equal to the chord "c" of the blade, (it is between 5 and 6 times the thickness "e” of that -this).
  • the blades being machined by electrochemical machining in bars of alloys or steels, one must start from rectangular blanks whose width is at least equal to the chord of the blade and whose thickness is at least equal to the plate 7 of dawn head.
  • Document FR-A-2 599 785 shows a particular embodiment thereof in which a circular plate is in one piece with the blade.
  • the object of the invention is to produce a turbomachine blade with variable setting, faster machining and requiring less raw material in order to reduce manufacturing costs without detracting from the necessary qualities of such blades.
  • Documents US-A-2 955 744 and G8-A-2 027 811 thus show blades of which a circular cup is brazed or welded on the blade.
  • the invention also aims to provide anti-friction properties to the dawn plate that it would not otherwise have (this function was previously performed by an anti-friction washer), while avoiding welding or soldering operations of the plate on the blade but nevertheless ensuring the combined rotation drive of the plate and the blade.
  • the subject of the invention is therefore, generally, a variable setting vane for turbomachinery comprising a swivel foot in an internal rail, a blade which can be oriented in the vein, a blade / pivot-head connecting plate suitable for journalling in a countersink of the casing of the turbomachine, and a control rod mounted inside a radial bore of the casing inside which an anti-friction sleeve is interposed.
  • the blade has a rectangular tongue integral with the blade and cut in the extension thereof and the head plate consists of an attached cylindrical cup whose cylindrical wall journals in the countersinking of the housing.
  • the cup has a rectangular diametrical groove engaged on the tongue of the blade to be driven in rotation by the latter.
  • the blade 10 comprises a blade 11 comprising at the head a control rod 12. Between the blade 11 and the rod 12 is made a tongue 13 or block of generally parallelepiped shape of small width whose edges longitudinal 13a are parallel to each other and to the chord of the blade while the upstream 13a and downstream 13c edges are portions of the same cylinder centered on the axis of the control head and of the same diameter D as the counterbore 14 (shown in Figures 5 and 6) of the housing in which the blade 10 must rotate.
  • a cylindrical cup 15 of the same diameter D as the tongue is pierced in its center with a bore 15a through which the control rod 12 of the blade passes.
  • the internal face 15b of the cup 15 is formed of a left surface reconstituting the shape of the air stream of the turbomachine.
  • the internal face 15b therefore has the shape concave of a portion of cylinder (or cone) whose diameter would be that of the internal wall of the casing at the level of the stator stage concerned.
  • the cup has a diametrical groove 15c of the same width as the tongue 13 of the blade.
  • the groove 15c can thus be placed on the tongue 13 and ensure the simultaneous rotation of the cup 15 with the blade 10.
  • FIG 5 there is shown, as a first embodiment, the mounting of a blade according to Figures 3 and 4, in a compressor housing 16.
  • the blade is arranged from the inside of the casing 16 in the radial bore 17 thereof.
  • An anti-friction sleeve 18 is mounted on the outside of the casing.
  • the socket 18 has an external shoulder 18a which comes to bear against the boss of the casing while a clearance is left between its internal end 18b and the upper face of the cup 15.
  • the cup 15 is slightly set back in the counterbore 14, with respect to the vein, which is necessary to avoid a projection in the vein during the angular setting of the blades.
  • the sleeve 18 is placed last so that in its absence the blade can be tilted for its installation and removal.
  • the cup 15 or the socket assembly plus the cup 19 can be made of an anti-friction material either based on sintered carbon such as the material sold under the name of "VESPEL” or based on colloidal substance reinforced with braided fibers such as that marketed under the name of AVIMID.
  • the invention has several advantages: - First of all, it allows a reduction in the gross volume of the blade blank before ECM machining, this reduction possibly ranging from 45 to 65% depending on the width of the tongue 13 of the blade; - The invention also allows a significant reduction in mass since the insert cup is made of composite material of lower density than the steel from which the blade is formed; - Finally, by reducing the volume of the blank, the duration, and therefore the cost of the ECM machining of the blade is reduced accordingly, a reduction in cost that has been able to be estimated at 20%.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
EP90401108A 1989-04-26 1990-04-25 Verstellvorrichtung für schwenkbare Leitschaufeln mit eingebautem Drehteller Expired - Lifetime EP0395498B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8905517A FR2646467A1 (fr) 1989-04-26 1989-04-26 Aube de stator a calage variable a coupelle rapportee
FR8905517 1989-04-26

Publications (2)

Publication Number Publication Date
EP0395498A1 true EP0395498A1 (de) 1990-10-31
EP0395498B1 EP0395498B1 (de) 1992-09-09

Family

ID=9381138

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90401108A Expired - Lifetime EP0395498B1 (de) 1989-04-26 1990-04-25 Verstellvorrichtung für schwenkbare Leitschaufeln mit eingebautem Drehteller

Country Status (4)

Country Link
US (1) US5039277A (de)
EP (1) EP0395498B1 (de)
DE (1) DE69000296T2 (de)
FR (1) FR2646467A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013010596A1 (de) * 2011-07-21 2013-01-24 Bosch Mahle Turbo Systems Gmbh & Co. Kg Variable turbinen-/verdichtergeometrie und zugehöriges herstellverfahren

Families Citing this family (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2682157B1 (fr) * 1991-10-02 1995-01-20 Snecma Biellette de commande d'aube et reseau de telles biellettes.
DE4237031C1 (de) * 1992-11-03 1994-02-10 Mtu Muenchen Gmbh Verstellbare Leitschaufel
US5622473A (en) * 1995-11-17 1997-04-22 General Electric Company Variable stator vane assembly
DE19752534C1 (de) * 1997-11-27 1998-10-08 Daimler Benz Ag Radialdurchströmte Abgasturboladerturbine
US6146093A (en) * 1998-12-16 2000-11-14 General Electric Company Variable vane seal and washer
US6264369B1 (en) 1999-01-29 2001-07-24 General Electric Company Variable vane seal and washer materials
US6210106B1 (en) * 1999-04-30 2001-04-03 General Electric Company Seal apparatus for gas turbine engine variable vane
US6453556B1 (en) * 2000-10-11 2002-09-24 Hmy Ltd. Method of producing exhaust gas vane blade for superchargers of motor vehicles and vane blade
ITTO20010445A1 (it) * 2001-05-11 2002-11-11 Fiatavio Spa Statore di una turbina assiale a geometria variabile per applicazioniaeronautiche.
CN1293291C (zh) * 2001-08-03 2007-01-03 株式会社秋田精密冲压 Vgs型涡轮增压器中的可变叶片制造方法
CN1282822C (zh) * 2001-08-03 2006-11-01 株式会社秋田精密冲压 Vgs型涡轮增压器中的可变叶片制造方法和可变叶片
DE10250063A1 (de) * 2002-10-25 2004-05-06 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Verstellung von Kompressorschaufeln einer Gasturbine
US6808364B2 (en) 2002-12-17 2004-10-26 General Electric Company Methods and apparatus for sealing gas turbine engine variable vane assemblies
US7094022B2 (en) * 2003-05-27 2006-08-22 General Electric Company Variable stator vane bushings and washers
US7112039B2 (en) * 2003-10-29 2006-09-26 United Technologies Corporation Variable vane electro-graphic thrust washer
FR2885182B1 (fr) * 2005-04-28 2010-11-26 Snecma Moteurs Aube de stator a calage variable, procede de reparation d'une aube
US7588415B2 (en) * 2005-07-20 2009-09-15 United Technologies Corporation Synch ring variable vane synchronizing mechanism for inner diameter vane shroud
US7690889B2 (en) * 2005-07-20 2010-04-06 United Technologies Corporation Inner diameter variable vane actuation mechanism
US7753647B2 (en) * 2005-07-20 2010-07-13 United Technologies Corporation Lightweight cast inner diameter vane shroud for variable stator vanes
US7665959B2 (en) * 2005-07-20 2010-02-23 United Technologies Corporation Rack and pinion variable vane synchronizing mechanism for inner diameter vane shroud
US7628579B2 (en) * 2005-07-20 2009-12-08 United Technologies Corporation Gear train variable vane synchronizing mechanism for inner diameter vane shroud
US7722318B2 (en) * 2007-02-13 2010-05-25 United Technologies Corporation Hole liners for repair of vane counterbore holes
US9133726B2 (en) * 2007-09-17 2015-09-15 United Technologies Corporation Seal for gas turbine engine component
US8105019B2 (en) * 2007-12-10 2012-01-31 United Technologies Corporation 3D contoured vane endwall for variable area turbine vane arrangement
US9404374B2 (en) 2008-04-09 2016-08-02 United Technologies Corporation Trunnion hole repair utilizing interference fit inserts
US9062560B2 (en) * 2012-03-13 2015-06-23 United Technologies Corporation Gas turbine engine variable stator vane assembly
GB201206603D0 (en) * 2012-04-16 2012-05-30 Rolls Royce Plc Variable stator vane arrangement
EP2738356B1 (de) * 2012-11-29 2019-05-01 Safran Aero Boosters SA Statorschaufel einer Strömungsmaschine, Statorschaufelkranz einer Strömungsmaschine und zugehöriges Montageverfahren
CA2903738A1 (en) * 2013-03-07 2014-09-12 Rolls-Royce Canada, Ltd. Gas turbine engine comprising an outboard insertion system of vanes and corresponding assembling method
US9995166B2 (en) * 2014-11-21 2018-06-12 General Electric Company Turbomachine including a vane and method of assembling such turbomachine
DE102014223975A1 (de) * 2014-11-25 2016-05-25 MTU Aero Engines AG Leitschaufelkranz und Strömungsmaschine
US10208619B2 (en) 2015-11-02 2019-02-19 Florida Turbine Technologies, Inc. Variable low turbine vane with aft rotation axis
JP6694950B2 (ja) * 2016-03-30 2020-05-20 三菱重工エンジン＆ターボチャージャ株式会社 可変容量型ターボチャージャ

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2955744A (en) * 1955-05-20 1960-10-11 Gen Electric Compressor
US3059902A (en) * 1961-07-03 1962-10-23 Chrysler Corp Adjustable nozzle and intermediate inner shroud support
GB1223390A (en) * 1968-08-19 1971-02-24 Gen Motors Corp Variable nozzles for high-temperature turbines
US3723021A (en) * 1971-01-28 1973-03-27 Caterpillar Tractor Co Flexible airfoil for compressor
GB1505858A (en) * 1976-12-08 1978-03-30 Secr Defence Axial flow rotary machines
GB2027811A (en) * 1978-08-09 1980-02-27 Mtu Muenchen Gmbh A gas turbine engine having means for bleeding compressor air
FR2599785A1 (fr) * 1986-06-04 1987-12-11 Snecma Aubage directeur d'entree d'air a calage variable pour turboreacteur
EP0298894A1 (de) * 1987-07-08 1989-01-11 United Technologies Corporation Kompressor mit geteiltem Gehäuse
US4856962A (en) * 1988-02-24 1989-08-15 United Technologies Corporation Variable inlet guide vane

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2933235A (en) * 1955-01-11 1960-04-19 Gen Electric Variable stator compressor
DE2740192C2 (de) * 1977-09-07 1981-11-12 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Spaltdichtung für eine um ihre Längsachse verstellbare, axial umströmte Leitschaufel einer Strömungsmaschine
GB2170279B (en) * 1985-01-30 1988-10-19 Ampep Plc Self-lubricating bearings
FR2582720B1 (fr) * 1985-05-29 1989-06-02 Snecma Procede de realisation de pivot d'aube de turbomachine et aube de stator le comportant
US4710036A (en) * 1986-03-20 1987-12-01 Smith International, Inc. Bearing assembly
FR2608678B1 (fr) * 1986-12-17 1991-02-08 Snecma Dispositif de commande d'aubes a calage variable de redresseur de turbomachine

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2955744A (en) * 1955-05-20 1960-10-11 Gen Electric Compressor
US3059902A (en) * 1961-07-03 1962-10-23 Chrysler Corp Adjustable nozzle and intermediate inner shroud support
GB1223390A (en) * 1968-08-19 1971-02-24 Gen Motors Corp Variable nozzles for high-temperature turbines
US3723021A (en) * 1971-01-28 1973-03-27 Caterpillar Tractor Co Flexible airfoil for compressor
GB1505858A (en) * 1976-12-08 1978-03-30 Secr Defence Axial flow rotary machines
GB2027811A (en) * 1978-08-09 1980-02-27 Mtu Muenchen Gmbh A gas turbine engine having means for bleeding compressor air
FR2599785A1 (fr) * 1986-06-04 1987-12-11 Snecma Aubage directeur d'entree d'air a calage variable pour turboreacteur
EP0298894A1 (de) * 1987-07-08 1989-01-11 United Technologies Corporation Kompressor mit geteiltem Gehäuse
US4856962A (en) * 1988-02-24 1989-08-15 United Technologies Corporation Variable inlet guide vane

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013010596A1 (de) * 2011-07-21 2013-01-24 Bosch Mahle Turbo Systems Gmbh & Co. Kg Variable turbinen-/verdichtergeometrie und zugehöriges herstellverfahren
WO2013010848A1 (de) * 2011-07-21 2013-01-24 Bosch Mahle Turbo Systems Gmbh & Co. Kg Schaufellagerring einer variablen turbinen-/verdichtergeometrie

Also Published As

Publication number Publication date
DE69000296T2 (de) 1993-03-25
US5039277A (en) 1991-08-13
DE69000296D1 (de) 1992-10-15
FR2646467A1 (fr) 1990-11-02
EP0395498B1 (de) 1992-09-09

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