EP0274293A1 - Lufteintrittsgehäuse für eine Turbomaschine mit Radialstreben - Google Patents

Lufteintrittsgehäuse für eine Turbomaschine mit Radialstreben Download PDF

Info

Publication number
EP0274293A1
EP0274293A1 EP19870402659 EP87402659A EP0274293A1 EP 0274293 A1 EP0274293 A1 EP 0274293A1 EP 19870402659 EP19870402659 EP 19870402659 EP 87402659 A EP87402659 A EP 87402659A EP 0274293 A1 EP0274293 A1 EP 0274293A1
Authority
EP
European Patent Office
Prior art keywords
tie rod
turbomachine
arm
carried
hub
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
EP19870402659
Other languages
English (en)
French (fr)
Other versions
EP0274293B1 (de
Inventor
Jean-Pierre 431 allée Marquise de Sévigné Ruis
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 EP0274293A1 publication Critical patent/EP0274293A1/de
Application granted granted Critical
Publication of EP0274293B1 publication Critical patent/EP0274293B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • 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
    • Y10T137/00—Fluid handling
    • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]

Definitions

  • the present invention relates to a turbomachine inlet casing of the double flow type comprising radiating arms composed of a fixed part and an associated flap with variable setting and of the type with cantilever mounting without support bearing.
  • French patent applications 86-07369 and 86-08016 present examples of mounting such an inlet casing and more particularly describe embodiments of the device for controlling said flaps.
  • each arm comprises a metal tie rod forming a central core and disposed between an outer ferrule and an inner hub on which it is fixed by a nut on which a tightening is exerted so as to obtain a prestressing of the tie rod.
  • the turbomachine inlet casing produced according to the invention and shown in FIGS. 1 and 2 comprises an outer shell 1 composed of an upstream shell 1a and a downstream shell 1b, upstream and downstream being defined with respect to the direction of circulation in the main stream of gas from the turbomachine.
  • the upstream shell 1a has an upstream flange 2 and a row of bosses 3 peripherally and uniformly distributed. Each boss 3 is capped by a cap 4.
  • the upstream shell 1a On its radially internal face, the upstream shell 1a has a recess 1c in the bottom of which a cutout 1d is formed which extends on the external face between two yokes 1e.
  • the upstream ferrule 1a is secured to the downstream ferrule 1b by means of two flanges 5 and 6 respectively.
  • the downstream ferrule 1b also includes a downstream flange 7, an annular external platform 8. At the level of the flange 7 is provided the connection to a flange of the adjacent casing.
  • the internal wall 9 of the downstream shell 1b is spherical and its function will be specified below.
  • each ferrule respectively has a row of half-bosses, respectively 10 and 11, cooperating, peripherally and uniformly distributed.
  • the inlet casing is associated with a hub 12 consisting of a plurality of metallic inserts 13 each comprising two radial bores upstream 14 and downstream 15. These inserts are embedded in layers 16 of wound filaments, as this is visible for example in Figure 2.
  • the upstream flange 17 of the hub 12 forms an annular lip in which is formed a groove 18 open towards the rear.
  • the downstream flange 19 also has a groove 20 open towards the rear.
  • the turbomachine Downstream of the inlet casing, the turbomachine comprises a rotating compression rotor stage, a blade 21 and the disc 22 are partially shown in FIG. 1. On the disc 22 is fixed a rotating internal cover 23, placed inside of the hub 12.
  • the internal cover 23 has an upstream flange 24 which carries a sealing wiper 25 engaged in the groove 18 of the hub and it likewise comprises a downstream flange 25 which carries a sealing wiper 26 engaged in the groove 20 of the hub 12.
  • a plurality of radiating arms 27 which may be according to the embodiment shown sixteen in number. These arms 27 each consist of an upstream fixed part 27a and a downstream movable part forming a movable flap 27b.
  • Each movable flap 27b has a radially internal pivot 28 capable of rotating inside the downstream bore 15 of the insert 13 of the hub 12 in which it is placed.
  • the movable flap 27b also includes a radially external pivot 29, associated for example with a bushing 30.
  • the pivot 29 and the bushing 30 are placed in a bore 31 formed by the two half-bosses 10 and 11 of the outer shroud 1.
  • head of each external pivot 29 is fixed, for example by means of a bolt 32, the end of a lever 33 connected at its other end, by means of a pin 34, to a ring 35 for control and synchronization movable flaps 27b.
  • An actuating means of a known type for example a jack (not shown in the drawing) is associated with said control ring 35.
  • the pins 34 are housed in a support 36 which rests and slides on the platform 8 of the downstream ferrule 1b.
  • the fixed arm part 27a is composed of a metallic core constituting a tie rod 37 for fixing, surrounded by a sheath 38 of composite material, itself covered with a skin, on the lower side 39 and upper side 40, which can be either metallic or also made of composite material.
  • the head 37a of a tie rod 37 is fixed between the two yokes 1e carried by the outer shell 1 by means of an axis 41.
  • the foot 37b of a tie rod 37 is placed in the upstream bore 14 of an insert 13 of the hub 12 and it ends in a threaded part 37c cooperating with a tightening nut 42.
  • the radially outer apex of the fixed part 27a of the casing arms 27 is first embedded in the recess 1c on the inner face of the upstream shell 1a.
  • a tie rod 37 is inserted from the inside into the composite assembly 38-39-40 of the arm, it slides until it comes to place the head 37a of the tie rod between the two yokes 1e to which it is secured by the axis 41.
  • L 'nut 42 is placed on the foot 37b of the tie without tightening. All the fixed parts 27a of the arms 27 and all the tie rods 37 are thus successively mounted between the upstream ferrule 1a and the hub 12.
  • the internal pivots 28 and the external pivots 29 of the movable flaps 27b are successively and respectively placed in the downstream bores 15 of the inserts 13 of the hub 12 and in the half-bosses 10 of the upstream shell 1a.
  • the upstream ferrules 1a and downstream 1b are then assembled at their respective flanges 5 and 6, the half-bosses 11 of the downstream ferrule 1b covering the external pivots 29 and sockets 30 of the movable flaps 27b.
  • the nuts 42 are then tightened so as to obtain a prestressing of the tie rods 37.
  • the internal cover 23 is also fixed to the disc 22 of the rotor.
  • the assembly of the inlet casing is then assembled at the level of the cooperating flanges of the outer shroud and of the adjacent turbomachine casing, taking care to correctly engage the sealing wipers 25 and 26 of the cover 22 in the corresponding grooves 18 and 20 from hub 12.
  • F1 is the aerodynamic force applied to the movable flaps 27b.
  • the prestressing obtained by the tightening mentioned above which is applied to the nuts 42 for fixing the tie rods 37 can be broken down into an axial component F2 and a radial component F3.
  • the radial component F3 is a force taken up by the winding of the internal hub 12.
  • an electrical resistance can be placed in the sheath 38, respectively 43 upstream side and 44 downstream side.
  • the connections 43a and 44a of these resistors are then placed on the cap 4, connecting them to the incoming electrical conductors 45 and 46.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP19870402659 1986-11-26 1987-11-25 Lufteintrittsgehäuse für eine Turbomaschine mit Radialstreben Expired - Lifetime EP0274293B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8616449A FR2607188B1 (fr) 1986-11-26 1986-11-26 Carter d'entree de turbomachine a bras rayonnants
FR8616449 1986-11-26

Publications (2)

Publication Number Publication Date
EP0274293A1 true EP0274293A1 (de) 1988-07-13
EP0274293B1 EP0274293B1 (de) 1990-04-11

Family

ID=9341217

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19870402659 Expired - Lifetime EP0274293B1 (de) 1986-11-26 1987-11-25 Lufteintrittsgehäuse für eine Turbomaschine mit Radialstreben

Country Status (4)

Country Link
US (1) US4821758A (de)
EP (1) EP0274293B1 (de)
DE (1) DE3762257D1 (de)
FR (1) FR2607188B1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2266562A (en) * 1992-04-23 1993-11-03 Turbo Propulsores Ind Gas turbine engine variable stator vane assembly.
US5314301A (en) * 1992-02-13 1994-05-24 Rolls-Royce Plc Variable camber stator vane
FR2714109A1 (fr) * 1993-12-22 1995-06-23 Snecma Aube de turbomachine à cambrure variable.
EP2083174A1 (de) 2008-01-25 2009-07-29 Siemens Aktiengesellschaft Einlassleitschaufel für einen Gasverdichter

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4212878A1 (de) * 1992-04-17 1993-03-18 Daimler Benz Ag Verstellbarer leitschaufelkranz
GB2339244B (en) * 1998-06-19 2002-12-18 Rolls Royce Plc A variable camber vane
US6619916B1 (en) * 2002-02-28 2003-09-16 General Electric Company Methods and apparatus for varying gas turbine engine inlet air flow
US6725645B1 (en) * 2002-10-03 2004-04-27 General Electric Company Turbofan engine internal anti-ice device
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
US7246480B2 (en) * 2004-11-04 2007-07-24 Siemens Power Generation, Inc. System for heating an air intake of turbine engine
US7230205B2 (en) * 2005-03-29 2007-06-12 Siemens Power Generation, Inc. Compressor airfoil surface wetting and icing detection system
ATE446439T1 (de) * 2005-07-01 2009-11-15 Siemens Ag Gekühlte gasturbinenleitschaufel für eine gasturbine, verwendung einer gasturbinenleitschaufel sowie verfahren zum betreiben einer gasturbine
GB0519502D0 (en) * 2005-09-24 2005-11-02 Rolls Royce Plc Vane assembly
US7549839B2 (en) * 2005-10-25 2009-06-23 United Technologies Corporation Variable geometry inlet guide vane
US8061975B2 (en) * 2007-08-31 2011-11-22 General Electric Company Slipring bushing assembly for moveable turbine vane
US8197196B2 (en) * 2007-08-31 2012-06-12 General Electric Company Bushing and clock spring assembly for moveable turbine vane
FR2941998B1 (fr) * 2009-02-06 2011-03-11 Gen Electric Ensemble de douille et de ressort-moteur pour aube mobile de turbine.
US8992173B2 (en) * 2011-11-04 2015-03-31 United Technologies Corporation Tie-rod nut including a nut flange with a plurality of mounting apertures
EP2946083B1 (de) * 2013-01-21 2023-07-19 Raytheon Technologies Corporation Turbinengehäuseeinstellung mit einstellbaren zugstangen
FR3010047B1 (fr) * 2013-09-04 2017-03-31 Snecma Structure de liaison moteur-nacelle a platine a vis
US10808568B2 (en) * 2018-09-12 2020-10-20 Raytheon Technologies Corporation Airfoil assembly for a gas turbine engine
CN111577463B (zh) * 2020-05-25 2021-08-17 中国航发沈阳发动机研究所 一种发动机进气机匣结构

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR57426E (fr) * 1946-01-11 1953-01-28 Perfectionnements aux turbines à gaz
GB774501A (en) * 1953-10-15 1957-05-08 Power Jets Res & Dev Ltd A stator guide vane construction for elastic fluid turbines
US2807433A (en) * 1952-07-10 1957-09-24 Havilland Engine Co Ltd Stationary blade rings of axial flow turbines or compressors
US3224666A (en) * 1963-04-16 1965-12-21 Svenska Aeroplan Ab Rotary fan arrangement
GB1023766A (en) * 1964-02-14 1966-03-23 Bristol Siddeley Engines Ltd Improvements in or relating to a member of aerodynamic cross-sectional shape having a variable camber
US3990810A (en) * 1975-12-23 1976-11-09 Westinghouse Electric Corporation Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine
FR2526485A1 (fr) * 1982-05-07 1983-11-10 Snecma Roue directrice d'entree de soufflante de turboreacteur permettant le demontage unitaire des aubes mobiles, et procede pour la mise en oeuvre

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR57426E (fr) * 1946-01-11 1953-01-28 Perfectionnements aux turbines à gaz
US2807433A (en) * 1952-07-10 1957-09-24 Havilland Engine Co Ltd Stationary blade rings of axial flow turbines or compressors
GB774501A (en) * 1953-10-15 1957-05-08 Power Jets Res & Dev Ltd A stator guide vane construction for elastic fluid turbines
US3224666A (en) * 1963-04-16 1965-12-21 Svenska Aeroplan Ab Rotary fan arrangement
GB1023766A (en) * 1964-02-14 1966-03-23 Bristol Siddeley Engines Ltd Improvements in or relating to a member of aerodynamic cross-sectional shape having a variable camber
US3990810A (en) * 1975-12-23 1976-11-09 Westinghouse Electric Corporation Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine
FR2526485A1 (fr) * 1982-05-07 1983-11-10 Snecma Roue directrice d'entree de soufflante de turboreacteur permettant le demontage unitaire des aubes mobiles, et procede pour la mise en oeuvre

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5314301A (en) * 1992-02-13 1994-05-24 Rolls-Royce Plc Variable camber stator vane
GB2266562A (en) * 1992-04-23 1993-11-03 Turbo Propulsores Ind Gas turbine engine variable stator vane assembly.
GB2266562B (en) * 1992-04-23 1995-10-11 Turbo Propulsores Ind Gas turbine stator vane assembly
FR2714109A1 (fr) * 1993-12-22 1995-06-23 Snecma Aube de turbomachine à cambrure variable.
EP0659979A1 (de) * 1993-12-22 1995-06-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbinenschaufel mit verstellbare Wölbung
US5520511A (en) * 1993-12-22 1996-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbomachine vane with variable camber
EP2083174A1 (de) 2008-01-25 2009-07-29 Siemens Aktiengesellschaft Einlassleitschaufel für einen Gasverdichter

Also Published As

Publication number Publication date
EP0274293B1 (de) 1990-04-11
US4821758A (en) 1989-04-18
FR2607188B1 (fr) 1991-02-08
DE3762257D1 (de) 1990-05-17
FR2607188A1 (fr) 1988-05-27

Similar Documents

Publication Publication Date Title
EP0274293A1 (de) Lufteintrittsgehäuse für eine Turbomaschine mit Radialstreben
CA2763415C (fr) Dispositif a verin fixe pour la commande de l'orientation des pales de soufflante d'un turbopropulseur
FR2660014A1 (fr) Dispositif de controle du jeu des extremites des aubes avec reglage de la position de segments d'anneau de renforcement par le mouvement d'un anneau de marche a l'unisson.
EP0636766B1 (de) Turbomaschinenstator mit verstellbaren Leitschaufeln und deren Bedienungsring
CA2794825C (fr) Procede d'adaptation de debit d'air de turbomachine a compresseur centrifuge et diffuseur de mise en oeuvre
FR2608678A1 (fr) Dispositif de commande d'aubes a calage variable de redresseur de turbomachine
EP1793093A2 (de) Leitschaufeln einer verbesserten Turbomaschine
FR2723614A1 (fr) Dispositif d'assemblage d'un etage circulaire d'aubes pivotantes.
CA2537672A1 (fr) Carter interne de turbomachine equipe d'un bouclier thermique
FR2696500A1 (fr) Turbomachine équipée de moyens de réglage du jeu entre les redresseurs et le rotor d'un compresseur.
WO2010122053A1 (fr) Carter intermediaire de turbomachine d'aeronef comprenant des bras structuraux de raccord a fonctions mecanique et aerodynamique dissociees
FR2653171A1 (fr) Carter de compresseur de turbomachine muni d'un dispositif de pilotage de son diametre interne.
FR2479902A1 (fr) Structure de controle de deviation de carter pour les turbines a gaz d'aeronefs
FR2982904A1 (fr) Moyeu de carter pour turboreacteur d'aeronef comprenant des moyens de commande de vannes de decharge ameliores
EP1491725B1 (de) Lagervorrichtung für eine verstellbare Schaufel
FR2882577A1 (fr) Dispositif de reglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine
EP0378943B1 (de) Kompressorgehäuse mit regelbarem Innendurchmesser für eine Turbomaschine
FR2943093A1 (fr) Dispositif de reglage de la position radiale et/ou axiale d'une virole de stator de turbomachine
EP0751297B1 (de) Turbomolekularpumpe
FR2683764A1 (fr) Procede de fabrication d'une aube de turbomachine realisee en materiau composite.
FR3053383B1 (fr) Clinquant de retention de douilles d'anneaux de commande d'aubes a calage variable et turboreacteur l'incorporant
EP4204302A1 (de) Nicht ummantelter propeller mit verstellschaufeln mit verringerten störungsplattformen
FR2583820A1 (fr) Dispositif de variation de section de passage d'un distributeur de turbine
FR2664018A1 (fr) Systeme de vanne de derivation.
FR3108665A1 (fr) Rotor de soufflante comprenant des aubes à centre de gravité en amont

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19871210

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 19890317

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MO

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
REF Corresponds to:

Ref document number: 3762257

Country of ref document: DE

Date of ref document: 19900517

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: FR

Ref legal event code: CL

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Ref country code: FR

Ref legal event code: CD

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20051025

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20051026

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20051027

Year of fee payment: 19

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20070601

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20061125

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20070731

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20061125

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20061130