GB2016597A - Controlling guide vane angle of an axial-flow compressor of a gas turbine engine - Google Patents

Controlling guide vane angle of an axial-flow compressor of a gas turbine engine

Info

Publication number
GB2016597A
GB2016597A GB7906705A GB7906705A GB2016597A GB 2016597 A GB2016597 A GB 2016597A GB 7906705 A GB7906705 A GB 7906705A GB 7906705 A GB7906705 A GB 7906705A GB 2016597 A GB2016597 A GB 2016597A
Authority
GB
United Kingdom
Prior art keywords
axial
gas turbine
turbine engine
guide vane
flow compressor
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
GB7906705A
Other versions
GB2016597B (en
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB7906705A priority Critical patent/GB2016597B/en
Publication of GB2016597A publication Critical patent/GB2016597A/en
Application granted granted Critical
Publication of GB2016597B publication Critical patent/GB2016597B/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes

Abstract

A first detector (35) detects a first pressure PS1 in the compressed fluid downstream variable angle guide vanes 30 which is influenced by their angular setting, and a second detector 37 detects a second, higher pressure PH in the compressed fluid which is substantially independent of the setting of the guide vanes but is functionally dependent upon the rotational speed of a compressor 20 of the engine 10, the detected pressures being used by a control unit 36 to cause an actuation mechanism 38, 40, 42, 44 to adjust the angle of the guidevanes in a predetermined manner dependent upon the ratio <IMAGE> <IMAGE>
GB7906705A 1978-03-14 1979-02-26 Controlling guide vane angle of an axial-flow compressor of a gas turbine engine Expired GB2016597B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB7906705A GB2016597B (en) 1978-03-14 1979-02-26 Controlling guide vane angle of an axial-flow compressor of a gas turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1002778 1978-03-14
GB7906705A GB2016597B (en) 1978-03-14 1979-02-26 Controlling guide vane angle of an axial-flow compressor of a gas turbine engine

Publications (2)

Publication Number Publication Date
GB2016597A true GB2016597A (en) 1979-09-26
GB2016597B GB2016597B (en) 1982-11-17

Family

ID=26247185

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7906705A Expired GB2016597B (en) 1978-03-14 1979-02-26 Controlling guide vane angle of an axial-flow compressor of a gas turbine engine

Country Status (1)

Country Link
GB (1) GB2016597B (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2119862A (en) * 1982-05-06 1983-11-23 Gen Electric Variable stator vane (VSV) closed loop control system of a compressor
US4968217A (en) * 1989-09-06 1990-11-06 Rolls-Royce Plc Variable pitch arrangement for a gas turbine engine
WO1995016117A1 (en) * 1993-12-08 1995-06-15 United Technologies Corporation Closed loop stator vane control
EP1302669A2 (en) * 2001-10-10 2003-04-16 Coltec Industries Inc. Control system for positioning compressor inlet guide vanes
WO2006059972A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Compressor variable stage remote actuation for turbine engine

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
WO2006110123A2 (en) 2004-12-01 2006-10-19 United Technologies Corporation Vectoring transition duct for turbine engine
WO2006059970A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
DE602004028528D1 (en) 2004-12-01 2010-09-16 United Technologies Corp Tip turbine engine with multiple blower and turbine stages
EP1825113B1 (en) 2004-12-01 2012-10-24 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
WO2006059985A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Axial compressor for tip turbine engine
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
US9003759B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Particle separator for tip turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
WO2006110122A2 (en) 2004-12-01 2006-10-19 United Technologies Corporation Inflatable bleed valve for a turbine engine and a method of operating therefore
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
DE602004023769D1 (en) 2004-12-01 2009-12-03 United Technologies Corp STACKED RINGING COMPONENTS FOR TURBINE ENGINES
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2119862A (en) * 1982-05-06 1983-11-23 Gen Electric Variable stator vane (VSV) closed loop control system of a compressor
US4968217A (en) * 1989-09-06 1990-11-06 Rolls-Royce Plc Variable pitch arrangement for a gas turbine engine
WO1995016117A1 (en) * 1993-12-08 1995-06-15 United Technologies Corporation Closed loop stator vane control
EP1302669A2 (en) * 2001-10-10 2003-04-16 Coltec Industries Inc. Control system for positioning compressor inlet guide vanes
EP1302669A3 (en) * 2001-10-10 2003-11-19 Coltec Industries Inc. Control system for positioning compressor inlet guide vanes
US6735955B2 (en) 2001-10-10 2004-05-18 Goodrich Pump & Engine Control Systems, Inc. Control system for positioning compressor inlet guide vanes
WO2006059972A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Compressor variable stage remote actuation for turbine engine

Also Published As

Publication number Publication date
GB2016597B (en) 1982-11-17

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee

Effective date: 19950226