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EP0388285A1 - Haltungssystem für verstellbare Leitschaufeln - Google Patents

Haltungssystem für verstellbare Leitschaufeln Download PDF

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Publication number
EP0388285A1
EP0388285A1 EP90400669A EP90400669A EP0388285A1 EP 0388285 A1 EP0388285 A1 EP 0388285A1 EP 90400669 A EP90400669 A EP 90400669A EP 90400669 A EP90400669 A EP 90400669A EP 0388285 A1 EP0388285 A1 EP 0388285A1
Authority
EP
European Patent Office
Prior art keywords
blade
downstream
retention system
bush
upstream
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
EP90400669A
Other languages
English (en)
French (fr)
Other versions
EP0388285B1 (de
Inventor
Daniel Jean Marey
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 EP0388285A1 publication Critical patent/EP0388285A1/de
Application granted granted Critical
Publication of EP0388285B1 publication Critical patent/EP0388285B1/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
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/22—Three-dimensional parallelepipedal

Definitions

  • the invention relates to turbomachine compressors and more particularly inside these means for radial retention and limitation of angular displacement of the variable pitch vanes.
  • the adaptation of the orientation of the stator fins of the different compressor stages is particularly desirable when it is desired, for example for the different stages, at a given speed, the greatest possible pressure while retaining a sufficient pumping margin.
  • stator vanes with variable setting are generally controlled in rotation by rods external to the casing and connected together by a control ring.
  • the blades generally have head and foot journals which are mounted to rotate in sockets.
  • Document FR-A 2 524 934 thus describes a blade having at its base a bushing pierced with a bore in which the blade root swivels, the bushing being able to comprise a diamond face whose parallel edges ensure a function of limitation of the deflection maximum angular tolerated for a blade, so that, if one of the control levers of a blade breaks, it cannot be feathered or across the flow which would cause a probable pumping of the entire floor.
  • the object of the present invention is to simplify the mounting of the stator vanes with variable setting by producing a means of pivoting the blade which also ensures the positioning and the radial retention of the blade.
  • the invention also aims in one of these variants to ensure, quite simply, the limitation of the angular displacement of the stator blades in order to limit the risks of feathering or across the flow of the blade in the event breakage of a control rod.
  • the invention also aims to achieve the retention of the blade and possibly the limitation of angular movement in a region of the engine located at the outer casing in order to simplify the implementation and positioning.
  • the invention therefore relates to a system for retaining stator vanes with variable setting of a turbomachine compressor, said vanes being arranged between an inner ring of an external casing in which the casing comprises at least one upstream ferrule and a downstream ferrule joined together by two flanges facing each other, one upstream and the other downstream, while each blade has at its head a journal mounted to rotate in a bushing pierced with a radial bore and the blade is held radially in the socket by means of two parallel pins arranged longitudinally, said pins passing through the socket and cooperating with a
  • the stator stage with variable setting comprises vanes 1 comprising at the head a journal 2 surmounted by a threaded part intended for securing the vane with a control rod 3
  • the pin 2 has an annular groove with semi-circular section 4.
  • the pin 2 is engaged in the radial bore 5, of a sleeve 6.
  • the latter has the shape of a parallelepiped with trapezoidal section whose small base 6a is turned radially towards the inside of the engine and therefore "looks" at the top of the blade of the blade 1 while that the large base 6b is facing outwards.
  • the bore 5 of diameter D is drilled right through between the bases 6a and 6b.
  • the socket also has two holes 7 made longitudinally between the downstream face 6c, orthogonal to the bases 6a, 6b and the upstream, inclined face 6d and are symmetrical with respect to a plane containing the axis of the bore 5.
  • the two holes 7 are spaced apart by a width D equal to the diameter of the bore 5 which they partially pass through at about half height of the sleeve.
  • the pins 8 are longer than the holes 7 so that, once they have been put in place, they protrude from the downstream face 6c of the sleeve.
  • the turbojet engine housing is separated into two facing ferrules, one upstream 9 and the other downstream 10.
  • the upstream ferrule has at its downstream edge a connecting flange 9a (called upstream by analogy with the ferrule which carries it) and has bosses 9b projecting externally from the ferrule 9.
  • bosses 9b In the bosses 9b, are housings 9c shaped of trapezoidal section parallelepipeds capable of receiving the sockets 6 carried by the vanes 1.
  • the housings 9c have the same dimension as the sockets 6 and therefore open freely on the rear face of the upstream flange 9a, so that once in place, the sockets 6 are flush with the rear edge of the upstream flange 9a.
  • tapped holes 9d are made for the connection with the downstream ferrule 10.
  • the downstream ferrule 10 has on its front edge a downstream flange 10a which faces the flange 9a.
  • the flange 10a has holes 10b corresponding to the internal threads 9d of the upstream flange for securing the flanges to each other by screws 11.
  • the flange 10a On its front edge, the flange 10a has blind holes 10c produced in pairs, the holes of a pair having the same spacing D as the holes 7 in the socket 6.
  • the blind holes 10c can be replaced by a simple annular groove.
  • the blades 1 fitted with their bushing 6 are mounted in the casing by positioning the bushings 6 in their housings 9c of the upstream ferrule 9.
  • the downstream ferrule 10 is brought together and the flange 10a is oriented so that the part keys 8 protruding from the faces 6c of the sockets 6, enters the blind holes 10c of the flange 10a, which locks the pivots of the blades and assumes the maintenance of the sockets 6 in the flanges.
  • FIGS. 4 and 4a a variant of the blade journal has been shown in cross section at the level of the groove, capable of ensuring the limitation of the angular amplitude of the blades.
  • the assembly according to the invention has the advantage of allowing easy positioning and radial retention of small-sized blades produced by spinning and does not require, for their radial positioning, shoulders of diameter greater than the thickness of the blade. dawn, which was the case previously.
  • this embodiment it is possible to use vanes without extra thicknesses and therefore to make savings in manufacturing costs.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP90400669A 1989-03-15 1990-03-14 Haltungssystem für verstellbare Leitschaufeln Expired - Lifetime EP0388285B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8903375 1989-03-15
FR8903375A FR2644525B1 (fr) 1989-03-15 1989-03-15 Systeme de retention d'aubes de stator a calage variable

Publications (2)

Publication Number Publication Date
EP0388285A1 true EP0388285A1 (de) 1990-09-19
EP0388285B1 EP0388285B1 (de) 1993-05-19

Family

ID=9379699

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90400669A Expired - Lifetime EP0388285B1 (de) 1989-03-15 1990-03-14 Haltungssystem für verstellbare Leitschaufeln

Country Status (4)

Country Link
US (1) US5061152A (de)
EP (1) EP0388285B1 (de)
DE (1) DE69001630T2 (de)
FR (1) FR2644525B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2920492A1 (fr) * 2007-08-30 2009-03-06 Snecma Sa Etage d'aubes a calage variable pour une turbomachine
FR2995934A1 (fr) * 2012-09-24 2014-03-28 Snecma Aube pour redresseur de turbomachine

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5281087A (en) * 1992-06-10 1994-01-25 General Electric Company Industrial gas turbine engine with dual panel variable vane assembly
FR2742800B1 (fr) * 1995-12-20 1998-01-16 Snecma Agencement d'extremites internes d'un etage d'aubes a calage variable
DE19547653C2 (de) * 1995-12-20 1999-08-19 Abb Patent Gmbh Leitvorrichtung für eine Turbine mit einem Leitschaufelträger und Verfahren zur Herstellung dieser Leitvorrichtung
US6019574A (en) * 1998-08-13 2000-02-01 General Electric Company Mismatch proof variable stator vane
GB0116675D0 (en) * 2001-07-07 2001-08-29 Lucas Industries Ltd Vane actuator
DE10358421A1 (de) * 2003-12-13 2005-07-07 Mtu Aero Engines Gmbh Rotor für eine Turbomaschine
US7278819B2 (en) * 2005-07-05 2007-10-09 General Electric Company Variable stator vane lever arm assembly and method of assembling same
US7713022B2 (en) * 2007-03-06 2010-05-11 United Technologies Operations Small radial profile shroud for variable vane structure in a gas turbine engine
JP2010196550A (ja) * 2009-02-24 2010-09-09 Mitsubishi Heavy Ind Ltd 回転軸とレバーの取付構造、回転軸とレバーの取付方法、及び、流体機械
US9644491B2 (en) 2014-06-13 2017-05-09 Pratt & Whitney Canada Corp. Single bolting flange arrangement for variable guide vane connection
US10526911B2 (en) * 2017-06-22 2020-01-07 United Technologies Corporation Split synchronization ring for variable vane assembly
BE1026199B1 (fr) * 2018-04-10 2019-11-12 Safran Aero Boosters S.A. Virole exterieure en deux parties

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB965169A (en) * 1962-02-14 1964-07-29 Power Jets Res & Dev Ltd Improvements in or relating to rotary fluid-flow machines such as axial flow compressors
US3314654A (en) * 1965-07-30 1967-04-18 Gen Electric Variable area turbine nozzle for axial flow gas turbine engines
GB2159887A (en) * 1984-06-04 1985-12-11 Gen Electric A stator vane mounting arrangement

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3736070A (en) * 1971-06-22 1973-05-29 Curtiss Wright Corp Variable stator blade assembly for axial flow, fluid expansion engine
JPS5666527U (de) * 1979-10-29 1981-06-03
FR2524934B1 (fr) * 1982-04-08 1986-12-26 Snecma Dispositif de butee de securite pour pivot d'aubes de stator a calage variable
FR2608678B1 (fr) * 1986-12-17 1991-02-08 Snecma Dispositif de commande d'aubes a calage variable de redresseur de turbomachine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB965169A (en) * 1962-02-14 1964-07-29 Power Jets Res & Dev Ltd Improvements in or relating to rotary fluid-flow machines such as axial flow compressors
US3314654A (en) * 1965-07-30 1967-04-18 Gen Electric Variable area turbine nozzle for axial flow gas turbine engines
GB2159887A (en) * 1984-06-04 1985-12-11 Gen Electric A stator vane mounting arrangement

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2920492A1 (fr) * 2007-08-30 2009-03-06 Snecma Sa Etage d'aubes a calage variable pour une turbomachine
US8162597B2 (en) 2007-08-30 2012-04-24 Snecma Stage of variable-pitch vanes for a turbomachine
FR2995934A1 (fr) * 2012-09-24 2014-03-28 Snecma Aube pour redresseur de turbomachine

Also Published As

Publication number Publication date
EP0388285B1 (de) 1993-05-19
DE69001630D1 (de) 1993-06-24
FR2644525B1 (fr) 1991-05-24
US5061152A (en) 1991-10-29
DE69001630T2 (de) 1993-10-21
FR2644525A1 (fr) 1990-09-21

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