EP0093631A1 - Sicherheitsanschlag für die Zapfen von drehregelbaren Leitschaufeln - Google Patents

Sicherheitsanschlag für die Zapfen von drehregelbaren Leitschaufeln Download PDF

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Publication number
EP0093631A1
EP0093631A1 EP83400695A EP83400695A EP0093631A1 EP 0093631 A1 EP0093631 A1 EP 0093631A1 EP 83400695 A EP83400695 A EP 83400695A EP 83400695 A EP83400695 A EP 83400695A EP 0093631 A1 EP0093631 A1 EP 0093631A1
Authority
EP
European Patent Office
Prior art keywords
pivot
arm
inner ring
fixing means
foot pivot
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
EP83400695A
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English (en)
French (fr)
Other versions
EP0093631B1 (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 EP0093631A1 publication Critical patent/EP0093631A1/de
Application granted granted Critical
Publication of EP0093631B1 publication Critical patent/EP0093631B1/de
Expired 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

Definitions

  • the invention relates to a safety stop device for a stator vane pivot with variable setting, the vane comprising a head pivot and a foot pivot, the head pivot, cooperating with a bearing fixed in the motor housing. , being driven by a device for adjusting the orientation of the blades, the foot pivot being movable in a bearing fixed in an inner ring of the motor.
  • stator vanes with variable setting is given in French patent 2 205 952 in which the preliminary compression stage and four upper compression stages are fitted with adjustable stator fins.
  • the pivots at the head of these fins are controlled by a ring and lever system which, from a single order, changes the orientation of the fins of each stage concerned.
  • the stator of the preliminary compression stage comprises fins of relatively large dimensions, which are further provided with a pivot at the foot allowing the bending forces to be taken up.
  • the invention aims to minimize the drawbacks resulting from a break in control and is suitable in particular for stator blades with variable setting controlled at the head and comprising a foot pivot.
  • the device according to the invention is remarkable in that it consists of an arm comprising means for fixing to the foot pivot and abutment elements provided in the inner ring against which the arm bears.
  • FIG. 1 shows in partial section part of a compressor stage comprising a stator 1 formed of a crown of blades 2 with pivots at the head 3 and at the foot 4, the orientation of which is controlled at the head by a control system 5 located outside the crankcase 6, and a rotor 7 formed of vanes 8, the feet of which are embedded in the rotor disc 9.
  • the head pivot 3 pivots in a bearing fixed in the upper ring or casing 6.
  • a connecting rod or control lever 10 is fixed by one of its ends to the pivot 3 and, by its other end, to a control device 11 of the crown of blades.
  • the foot pivot 4 is held in a staircase 12 fixed in the inner ring (13).
  • the stop device according to the invention (FIGS. 2, 3, 5) consists of at least one arm 14 comprising means for fixing to the pivot 4 and stop elements 15, 16 fixed to the inner ring 13 and against which the arm 14 is supported, in the event of a break in the control mechanism 10-11 for example.
  • the cylindrical pivot 4 of the blade root carries at its end at least one flat 17, and preferably two parallel flat.
  • the pivot 4 cooperates with a bearing 12 consisting of a bush made of a self-lubricating material fixed in the lower ring 13 of the stage.
  • This ring is provided on its inner surface 18 with a circumferential groove 19 in which the end of the pivot 4 projects and, in particular, the part carrying the flats 17.
  • An arm 14 is fixed on the end of the pivot by fixing means formed by a central hole 20 of rectangular shape with two opposite curved sides corresponding to the shape of the end of the pivot.
  • the arm 14 has, in plan view ( Figure 4) a diamond shape in which the two vertices 22, 23 located on the small diagonal, are rounded. The length of this diagonal is less than the width of the groove 19.
  • angles of the rhombus are determined so as to allow the orientation of the blades to be adjusted at a given angle.
  • the end of the opposite sides of the rhombus is placed against the abutment elements formed by the sides 15, 16 of the groove 19.
  • annular profile 21 for example in the form of a C, is fixed by any means known per se to the lower ring 13.
  • the foot pivot 4 carries in its axis a hexagonal blind hole 24, into which penetrates a stud 25 of comparable shape and dimensions, perpendicular to the plane of the arm 14 and integral with that -this.
  • a profile annular in C 21 fixed on the inner ring seals and possibly maintains the arm in cooperation with the pivot.
  • the fact of limiting the amplitude of the possible accidental movement of the blade makes it possible to limit the total length of the motor: in fact, the blades can no longer be placed in a flag, rope parallel to the wind bed, we can reduce the length of the motor by 5 mm per stage, resulting in a significant reduction in mass.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Sliding-Contact Bearings (AREA)
  • Control Of Turbines (AREA)
EP83400695A 1982-04-08 1983-04-06 Sicherheitsanschlag für die Zapfen von drehregelbaren Leitschaufeln Expired EP0093631B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8206117A FR2524934B1 (fr) 1982-04-08 1982-04-08 Dispositif de butee de securite pour pivot d'aubes de stator a calage variable
FR8206117 1982-04-08

Publications (2)

Publication Number Publication Date
EP0093631A1 true EP0093631A1 (de) 1983-11-09
EP0093631B1 EP0093631B1 (de) 1986-01-29

Family

ID=9272876

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83400695A Expired EP0093631B1 (de) 1982-04-08 1983-04-06 Sicherheitsanschlag für die Zapfen von drehregelbaren Leitschaufeln

Country Status (5)

Country Link
US (1) US4514141A (de)
EP (1) EP0093631B1 (de)
JP (1) JPS58206810A (de)
DE (1) DE3361967D1 (de)
FR (1) FR2524934B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2556410A1 (fr) * 1983-12-07 1985-06-14 Snecma Dispositif de centrage de l'anneau interieur d'un stator a ailettes a calage variable
FR2582720A1 (fr) * 1985-05-29 1986-12-05 Snecma Procede de realisation de pivot d'aube de turbomachine et aube de stator le comportant

Families Citing this family (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2583817B1 (fr) * 1985-06-20 1988-07-29 Snecma Biellette de commande d'aube a calage variable de stator de compresseur de turbomachine
US4695220A (en) * 1985-09-13 1987-09-22 General Electric Company Actuator for variable vanes
US4792277A (en) * 1987-07-08 1988-12-20 United Technologies Corporation Split shroud compressor
FR2644525B1 (fr) * 1989-03-15 1991-05-24 Snecma Systeme de retention d'aubes de stator a calage variable
US5492446A (en) * 1994-12-15 1996-02-20 General Electric Company Self-aligning variable stator vane
FR2742799B1 (fr) * 1995-12-20 1998-01-16 Snecma Palier d'extremite interne d'aube pivotante
US20080053547A1 (en) * 1997-11-24 2008-03-06 Yungrwei Chen Energy attenuation apparatus for a conduit conveying liquid under pressure, system incorporating same, and method of attenuating energy in a conduit
US6019574A (en) * 1998-08-13 2000-02-01 General Electric Company Mismatch proof variable stator vane
EP1205639A1 (de) * 2000-11-09 2002-05-15 General Electric Company Befestigungsanordnung von verstellbaren Turbinenleitschaufeln im inneren Haltering
US6413043B1 (en) * 2000-11-09 2002-07-02 General Electric Company Inlet guide vane and shroud support contact
US6682299B2 (en) 2001-11-15 2004-01-27 General Electric Company Variable stator vane support arrangement
DE10161292A1 (de) * 2001-12-13 2003-06-26 Rolls Royce Deutschland Lagerring zur Lagerung von Schaufelfüßen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine
FR2835562B1 (fr) * 2002-02-07 2004-07-16 Snecma Moteurs Agencement de pivotement d'aube de stator dans une turbomachine
GB2412947B (en) * 2004-04-07 2006-06-14 Rolls Royce Plc Variable stator vane assemblies
FR2875270B1 (fr) * 2004-09-10 2006-12-01 Snecma Moteurs Sa Retenue des clavettes de centrage des anneaux sous aubes de stator a calage variable d'un moteur a turbine a gaz
GB0504588D0 (en) * 2005-03-05 2005-04-13 Rolls Royce Plc Pivot ring
US7249613B1 (en) 2006-02-03 2007-07-31 Dayco Products, Llc Energy attenuation device
US7717135B2 (en) * 2006-02-03 2010-05-18 Yh America, Inc. Energy attenuation device
DE102006024085B4 (de) * 2006-05-23 2020-04-16 MTU Aero Engines AG Turboverdichter in Axialbauweise
US20080210486A1 (en) * 2007-03-02 2008-09-04 Dayco Products, Llc Energy attenuation device
FR2928961B1 (fr) * 2008-03-19 2015-11-13 Snecma Distributeur sectorise pour une turbomachine.
FR2964710B1 (fr) * 2010-09-14 2012-08-31 Snecma Douille pour aube a calage variable
FR2995934B1 (fr) * 2012-09-24 2018-06-01 Safran Aircraft Engines Aube pour redresseur de turbomachine
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
EP3954882B1 (de) * 2016-03-30 2023-05-03 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbolader mit variabler geometrie
FR3053383B1 (fr) * 2016-07-04 2019-08-02 Safran Aircraft Engines Clinquant de retention de douilles d'anneaux de commande d'aubes a calage variable et turboreacteur l'incorporant
FR3055374B1 (fr) * 2016-08-23 2018-08-03 Safran Aircraft Engines Piece d'interface pour reconditionner un anneau de commande d'un compresseur de moteur, et procede de reconditionnement associe
DE102016215807A1 (de) * 2016-08-23 2018-03-01 MTU Aero Engines AG Innenring für einen Leitschaufelkranz einer Strömungsmaschine
DE102017109952A1 (de) * 2017-05-09 2018-11-15 Rolls-Royce Deutschland Ltd & Co Kg Rotorvorrichtung einer Strömungsmaschine
GB201715165D0 (en) 2017-09-20 2017-11-01 Rolls Royce Plc Bearing assembly
DE102018210601A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Segmentring zur montage in einer strömungsmaschine
DE102018213983A1 (de) 2018-08-20 2020-02-20 MTU Aero Engines AG Verstellbare Leitschaufelanordnung, Leitschaufel, Dichtungsträger und Turbomaschine
CN112096658B (zh) 2020-11-06 2021-01-22 中国航发上海商用航空发动机制造有限责任公司 航空发动机压气机及其可调静子叶片位置保持结构
FR3123885B1 (fr) * 2021-06-15 2023-06-16 Safran Aircraft Engines Redresseur non carene de turbomachine equipe d’aubes de stator fixees a des pivots et turbomachine correspondante
FR3132123B1 (fr) * 2022-01-21 2023-12-08 Safran Aircraft Engines Aube de redresseur de flux secondaire de turbomachine, turbomachine munie de celle-ci
US12180974B2 (en) 2022-03-24 2024-12-31 Copeland Lp Variable inlet guide vane apparatus and compressor including same
US12516678B2 (en) * 2023-03-20 2026-01-06 Copeland Lp Variable inlet guide vane apparatus combined with compressor end cap
FR3161923A1 (fr) * 2024-05-06 2025-11-07 Safran Aircraft Engines Etage d’aubes a calage variable pour une turbomachine d’aeronef

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE556572A (de) * 1955-08-16
GB621175A (en) * 1946-11-16 1949-04-05 Power Jets Res & Dev Ltd Improvements in or relating to stator blading of compressors and like machines
FR1041161A (fr) * 1951-08-14 1953-10-21 Napier & Son Ltd Perfectionnements aux appareils à réaction à courant axial de fluide comprenant au moins une rangée d'aubes radiales
DE1047538B (de) * 1956-10-29 1958-12-24 Siemens Ag Drehbare Leitschaufel mit begrenztem Drehbereich, insbesondere fuer Turbinen, z. B. Gasturbinen
US3029067A (en) * 1956-05-31 1962-04-10 Garrett Corp Variable area nozzle means for turbines
US3303992A (en) * 1965-03-03 1967-02-14 Gen Motors Corp Variable vane stator ring
US3367628A (en) * 1966-10-31 1968-02-06 United Aircraft Corp Movable vane unit

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1570536A (en) * 1925-02-20 1926-01-19 Morgan Smith S Co Gate stop for turbine construction
FR1281702A (fr) * 1960-03-15 1962-01-12 Daimler Benz Ag Dispositif de palier d'aubes directrices réglables pour turbines à gaz ou pour turbines à air chaud
US3107546A (en) * 1960-04-25 1963-10-22 Pacific Valves Inc Internal stop means for valves
NO119216B (de) * 1965-04-12 1970-04-06 Nydqvist & Holm Ab
US3295827A (en) * 1966-04-06 1967-01-03 Gen Motors Corp Variable configuration blade

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB621175A (en) * 1946-11-16 1949-04-05 Power Jets Res & Dev Ltd Improvements in or relating to stator blading of compressors and like machines
FR1041161A (fr) * 1951-08-14 1953-10-21 Napier & Son Ltd Perfectionnements aux appareils à réaction à courant axial de fluide comprenant au moins une rangée d'aubes radiales
BE556572A (de) * 1955-08-16
US3029067A (en) * 1956-05-31 1962-04-10 Garrett Corp Variable area nozzle means for turbines
DE1047538B (de) * 1956-10-29 1958-12-24 Siemens Ag Drehbare Leitschaufel mit begrenztem Drehbereich, insbesondere fuer Turbinen, z. B. Gasturbinen
US3303992A (en) * 1965-03-03 1967-02-14 Gen Motors Corp Variable vane stator ring
US3367628A (en) * 1966-10-31 1968-02-06 United Aircraft Corp Movable vane unit

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2556410A1 (fr) * 1983-12-07 1985-06-14 Snecma Dispositif de centrage de l'anneau interieur d'un stator a ailettes a calage variable
EP0146449A1 (de) * 1983-12-07 1985-06-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Einrichtung für die Zentrierung eines inneren Statorringes, unterstützt durch bewegliche Schaufeln
US4604030A (en) * 1983-12-07 1986-08-05 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Compressor with variable incidence stator vanes
FR2582720A1 (fr) * 1985-05-29 1986-12-05 Snecma Procede de realisation de pivot d'aube de turbomachine et aube de stator le comportant
EP0204615A1 (de) * 1985-05-29 1986-12-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Herstellungsverfahren für eine Turbinenschaufel und für ihren Drehpunkt
US4706354A (en) * 1985-05-29 1987-11-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Method of manufacturing a root pivot assembly of a variable incidence turbo-machine blade

Also Published As

Publication number Publication date
JPH029161B2 (de) 1990-02-28
US4514141A (en) 1985-04-30
EP0093631B1 (de) 1986-01-29
FR2524934B1 (fr) 1986-12-26
DE3361967D1 (en) 1986-03-13
FR2524934A1 (fr) 1983-10-14
JPS58206810A (ja) 1983-12-02

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