GB837649A - Improvements in compressor stator vane assembly - Google Patents

Improvements in compressor stator vane assembly

Info

Publication number
GB837649A
GB837649A GB35218/57A GB3521857A GB837649A GB 837649 A GB837649 A GB 837649A GB 35218/57 A GB35218/57 A GB 35218/57A GB 3521857 A GB3521857 A GB 3521857A GB 837649 A GB837649 A GB 837649A
Authority
GB
United Kingdom
Prior art keywords
levers
blades
blade
pin
ring
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
GB35218/57A
Inventor
Henry Albert Eckenfels
Levar C Jensen
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
Priority to US544172A priority Critical patent/US2842305A/en
Application filed by General Electric Co filed Critical General Electric Co
Priority to GB35218/57A priority patent/GB837649A/en
Priority to FR1190067D priority patent/FR1190067A/en
Priority to CH362270D priority patent/CH362270A/en
Publication of GB837649A publication Critical patent/GB837649A/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
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Abstract

837,649. Axial-flow compressors. GENERAL ELECTRIC CO. Nov. 12, 1957, No. 35218/57. Class 110 (1). [Also in Group XXV] In an axial-flow compressor having radiallydirected stator blades mounted on a casing for rotation about their axes by means of actuating rings encircling the casing and connected by levers to the bases of the blades, the rings are connected to the levers by universal joints, and the levers are secured to the bases of the blades, relative rotation between the levers and their blades being prevented by tangs on the bases received within openings in the levers. In a multi-stage axial-flow compressor forming part of a jet-propulsion engine, each stator blade 30 is pivoted in a bore 24 and a counterbore 26, both of which are lined with a bearing material such as polytetrafluorethylene. The recessed end of a lever 42 is attached to the blade by means of a stud 36 and tangs 40, each integral with the blade, and also holds a retaining ring 38 against the end of the blade stem. The levers 42 of each row of blades 30 are connected to a ring 60 by ball joints 76. Each ball joint is attached to the ring 60 by a pin 64 which is retained by a cotter pin 72 and a clip 70 which goes over an enlarged part 66 of the pin. Each ring 60 carries a pin which engages a corresponding cam slot in a longitudinally slidable arm, so that when the arm is moved by an actuator in accordance with a change in speed, temperature or pressure, the rings 60 are rotated in unison to adjust the pitch of the stator blades.
GB35218/57A 1955-11-01 1957-11-12 Improvements in compressor stator vane assembly Expired GB837649A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US544172A US2842305A (en) 1955-11-01 1955-11-01 Compressor stator assembly
GB35218/57A GB837649A (en) 1957-11-12 1957-11-12 Improvements in compressor stator vane assembly
FR1190067D FR1190067A (en) 1957-11-12 1957-11-16 Compressor stator
CH362270D CH362270A (en) 1957-11-12 1958-07-23 Axial compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB35218/57A GB837649A (en) 1957-11-12 1957-11-12 Improvements in compressor stator vane assembly

Publications (1)

Publication Number Publication Date
GB837649A true GB837649A (en) 1960-06-15

Family

ID=10375215

Family Applications (1)

Application Number Title Priority Date Filing Date
GB35218/57A Expired GB837649A (en) 1955-11-01 1957-11-12 Improvements in compressor stator vane assembly

Country Status (3)

Country Link
CH (1) CH362270A (en)
FR (1) FR1190067A (en)
GB (1) GB837649A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2232725A (en) * 1989-06-17 1990-12-19 Rolls Royce Plc Stator vane actuating lever in gas turbine engine
EP1431520A2 (en) * 2002-12-16 2004-06-23 United Technologies Corporation Variable vane arm/unison ring attachment system
EP2525048A1 (en) * 2011-05-18 2012-11-21 Siemens Aktiengesellschaft Drive lever arrangement
CN103189602A (en) * 2010-07-30 2013-07-03 涡轮梅坎公司 Device for controlling pivoting blades of a turbine engine
CN117948191A (en) * 2024-03-26 2024-04-30 中国航发燃气轮机有限公司 Gas turbine and stator blade adjusting structure thereof

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2608678B1 (en) * 1986-12-17 1991-02-08 Snecma VARIABLE SETTING BLADE CONTROL DEVICE FOR TURBOMACHINE RECTIFIER

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2232725A (en) * 1989-06-17 1990-12-19 Rolls Royce Plc Stator vane actuating lever in gas turbine engine
US5024580A (en) * 1989-06-17 1991-06-18 Rolls-Royce Plc Control of variable stator vanes
GB2232725B (en) * 1989-06-17 1994-01-12 Rolls Royce Plc Improvements in or relating to control of variable stator vanes
EP2273074A1 (en) * 2002-12-16 2011-01-12 United Technologies Corporation Vane arm
EP1431520A3 (en) * 2002-12-16 2006-09-27 United Technologies Corporation Variable vane arm/unison ring attachment system
US7448848B2 (en) 2002-12-16 2008-11-11 United Technologies Corporation Variable vane arm/unison ring attachment system
EP1431520A2 (en) * 2002-12-16 2004-06-23 United Technologies Corporation Variable vane arm/unison ring attachment system
CN103189602A (en) * 2010-07-30 2013-07-03 涡轮梅坎公司 Device for controlling pivoting blades of a turbine engine
CN103189602B (en) * 2010-07-30 2015-12-09 涡轮梅坎公司 A kind of device controlling turbo machine pivotable vanes
EP2525048A1 (en) * 2011-05-18 2012-11-21 Siemens Aktiengesellschaft Drive lever arrangement
WO2012156180A1 (en) 2011-05-18 2012-11-22 Siemens Aktiengesellschaft Drive lever arrangement
US9435352B2 (en) 2011-05-18 2016-09-06 Siemens Aktiengesellschaft Drive lever arrangement
CN117948191A (en) * 2024-03-26 2024-04-30 中国航发燃气轮机有限公司 Gas turbine and stator blade adjusting structure thereof
CN117948191B (en) * 2024-03-26 2024-06-14 中国航发燃气轮机有限公司 Gas turbine and stator blade adjusting structure thereof

Also Published As

Publication number Publication date
CH362270A (en) 1962-05-31
FR1190067A (en) 1959-10-09

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