GB1368353A - Actuation ring for variable geometry axial flow compressors - Google Patents

Actuation ring for variable geometry axial flow compressors

Info

Publication number
GB1368353A
GB1368353A GB385072A GB385072A GB1368353A GB 1368353 A GB1368353 A GB 1368353A GB 385072 A GB385072 A GB 385072A GB 385072 A GB385072 A GB 385072A GB 1368353 A GB1368353 A GB 1368353A
Authority
GB
United Kingdom
Prior art keywords
ring
axial flow
bushes
dowel
sectors
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.)
Expired
Application number
GB385072A
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB1368353A publication Critical patent/GB1368353A/en
Expired legal-status Critical Current

Links

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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1368353 Axial flow compressors GENERAL ELECTRIC CO 27 Jan 1972 [1 Feb 1971] 3850/72 Heading F1C An actuator ring 18 for use in the angular adjustment of the stator vanes of the axial flow compressor stage in a gas turbine engine comprises at least two sectors 34 of less than 180 degrees extent connected by bridge pieces 36 which overlie the ends of the sectors and are secured thereto by dowel bushes 48 and loose fitting bolts 40, 42. The dowel bushes are a tight fit to provide accurate location of the bridge pieces. The sectors 34 are hollow and are provided with swaged tubes 44, 50 through which the bolts 40, 42 and dowel bushes 48 extend. The stator vanes of each row of vanes are connected to a single actuator ring 18 by separate levers 16 which engage spherical journals 58 secured to the ring 18 by bolts 60, 62. The ring which surrounds the compressor casing 10 is rotated to adjust the vanes by a link 20 which is pivotally attached to a bridge piece 36. The links 20 of all the rings 18 are operated by a single lever (22) Fig.1 (not shown), which is pivoted by an actuator (26).
GB385072A 1971-02-01 1972-01-27 Actuation ring for variable geometry axial flow compressors Expired GB1368353A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11141171A 1971-02-01 1971-02-01

Publications (1)

Publication Number Publication Date
GB1368353A true GB1368353A (en) 1974-09-25

Family

ID=22338386

Family Applications (1)

Application Number Title Priority Date Filing Date
GB385072A Expired GB1368353A (en) 1971-02-01 1972-01-27 Actuation ring for variable geometry axial flow compressors

Country Status (4)

Country Link
US (1) US3685920A (en)
DE (1) DE2203933A1 (en)
FR (1) FR2125012A5 (en)
GB (1) GB1368353A (en)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH557960A (en) * 1972-11-08 1975-01-15 Bbc Sulzer Turbomaschinen DEVICE FOR THE VANE ADJUSTMENT.
GB1511723A (en) * 1975-05-01 1978-05-24 Rolls Royce Variable stator vane actuating mechanism
US4050844A (en) * 1976-06-01 1977-09-27 United Technologies Corporation Connection between vane arm and unison ring in variable area stator ring
FR2595117B1 (en) * 1986-02-28 1991-05-17 Mtu Muenchen Gmbh VARIABLE GEOMETRIC TURBOCHARGER
US4925364A (en) * 1988-12-21 1990-05-15 United Technologies Corporation Adjustable spacer
GB2227527B (en) * 1989-01-25 1993-06-09 Rolls Royce Plc A variable stator vane arrangement for an axial flow compressor
DE19516382A1 (en) * 1995-05-04 1996-11-07 Deutsche Forsch Luft Raumfahrt Adjustment ring
US5993152A (en) * 1997-10-14 1999-11-30 General Electric Company Nonlinear vane actuation
FR2853930B1 (en) * 2003-04-16 2007-02-23 Snecma Moteurs DEVICE FOR THE CONTROL OF VARIABLE-SETTING AUBES IN A TURBOMACHINE
GB2412946A (en) * 2004-04-06 2005-10-12 Rolls Royce Plc A unison ring
US7753647B2 (en) * 2005-07-20 2010-07-13 United Technologies Corporation Lightweight cast inner diameter vane shroud for variable stator vanes
US7588415B2 (en) * 2005-07-20 2009-09-15 United Technologies Corporation Synch ring 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
US7690889B2 (en) * 2005-07-20 2010-04-06 United Technologies Corporation Inner diameter variable vane actuation mechanism
FR2902454A1 (en) * 2006-06-16 2007-12-21 Snecma Sa TURBOMACHINE STATOR COMPRISING A FLOOR OF ADJUSTERS ADJUSTED BY A ROTATING CROWN WITH AUTOMATIC CENTERING
FR2922257B1 (en) * 2007-10-12 2014-03-28 Snecma IMPROVEMENT TO A CALIBRATION CONTROL RING OF THE FIXED AUBES OF A TURBOMACHINE
US8141368B2 (en) 2008-11-11 2012-03-27 Delavan Inc Thermal management for fuel injectors
US8794910B2 (en) * 2011-02-01 2014-08-05 United Technologies Corporation Gas turbine engine synchronizing ring bumper
US20140064911A1 (en) * 2012-08-29 2014-03-06 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
US9644491B2 (en) 2014-06-13 2017-05-09 Pratt & Whitney Canada Corp. Single bolting flange arrangement for variable guide vane connection
EP2966264B1 (en) * 2014-07-07 2021-09-22 Safran Aero Boosters SA Vane segment of an axial turbomachine compressor
US10753224B2 (en) * 2017-04-27 2020-08-25 General Electric Company Variable stator vane actuator overload indicating bushing
US10634000B2 (en) 2017-06-23 2020-04-28 Rolls-Royce North American Technologies Inc. Method and configuration for improved variable vane positioning
GB201711582D0 (en) * 2017-07-19 2017-08-30 Rolls Royce Plc Unison ring assembly
US10724543B2 (en) 2017-08-11 2020-07-28 Raytheon Technologies Corporation Bridge bracket for variable-pitch vane system

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3146585A (en) * 1961-09-29 1964-09-01 Gen Electric Turbojet control system for preventing compressor stall due to inlet air disturbances
US3325087A (en) * 1965-04-28 1967-06-13 David R Davis Stator casing construction for gas turbine engines
US3496628A (en) * 1965-04-28 1970-02-24 Usa Method of joining thin-walled members,particularly in casings for gas turbine engines
US3314595A (en) * 1965-06-09 1967-04-18 Gen Electric Adjustment mechanism for axial flow compressors
US3314654A (en) * 1965-07-30 1967-04-18 Gen Electric Variable area turbine nozzle for axial flow gas turbine engines
US3458118A (en) * 1967-08-21 1969-07-29 Gen Electric Low profile stator adjusting mechanism
US3502260A (en) * 1967-09-22 1970-03-24 Gen Electric Stator vane linkage for axial flow compressors

Also Published As

Publication number Publication date
US3685920A (en) 1972-08-22
DE2203933A1 (en) 1972-08-17
FR2125012A5 (en) 1972-09-22

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Legal Events

Date Code Title Description
CSNS Application of which complete specification have been accepted and published, but patent is not sealed