GB1215931A - Improvements in or relating to gas turbine engines - Google Patents

Improvements in or relating to gas turbine engines

Info

Publication number
GB1215931A
GB1215931A GB01509/67A GB1150967A GB1215931A GB 1215931 A GB1215931 A GB 1215931A GB 01509/67 A GB01509/67 A GB 01509/67A GB 1150967 A GB1150967 A GB 1150967A GB 1215931 A GB1215931 A GB 1215931A
Authority
GB
United Kingdom
Prior art keywords
speed
nozzle area
fuel
speeds
gas turbine
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
GB01509/67A
Inventor
Pierre Henry John Young
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 GB01509/67A priority Critical patent/GB1215931A/en
Priority to FR1564055D priority patent/FR1564055A/fr
Priority to US711958A priority patent/US3523423A/en
Publication of GB1215931A publication Critical patent/GB1215931A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/15—Control or regulation
    • F02K1/16—Control or regulation conjointly with another control

Abstract

1,215,931. Gas turbine jet-engines. ROLLS-ROYCE Ltd. March 11, 1968 [March 11, 1967], No. 11509/67. Headings F1G and F1J. [Also in Division G1] In a multi-spool gas turbine engine, the ratio of the speeds of the LP and HP spools is obtained electrically and used to control the nozzle area to prevent surges occurring in the turbine, the control being extended to the fuel supply if necessary. The principle is indicated by a family of curves (Fig. 2) of LP speed against HP speed for different nozzle areas, wherein the shaded portions represent the regions in which surges occur. The desired relationship between speeds and nozzle area is thus defined by curve ABCDEF, of which BCD represents changes in nozzle area, AB, DE represent changes in fuel supply and EF represents the maximum safe LP speed. The electric control system for the engine (Fig.3) is fed with signals representing the demanded fuel rate 41, the HP speed NH, LP speed NL and the temperature T of the air entering the compressor. The latter signals are combined to obtain the aerodynamic speeds NH/T¢ and NL/T¢, and the circuiting ensures that the nozzle area control valve 35 and the fuel throttle motors 23 are fed with the appropriate control signals when the engine parameters do not conform to the curve ABCDEF. The system also contains facilities for dealing with sudden changes in fuel demand associated with rapid acceleration and deceleration.
GB01509/67A 1967-03-11 1967-03-11 Improvements in or relating to gas turbine engines Expired GB1215931A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB01509/67A GB1215931A (en) 1967-03-11 1967-03-11 Improvements in or relating to gas turbine engines
FR1564055D FR1564055A (en) 1967-03-11 1968-03-08
US711958A US3523423A (en) 1967-03-11 1968-03-11 Gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB01509/67A GB1215931A (en) 1967-03-11 1967-03-11 Improvements in or relating to gas turbine engines

Publications (1)

Publication Number Publication Date
GB1215931A true GB1215931A (en) 1970-12-16

Family

ID=9987554

Family Applications (1)

Application Number Title Priority Date Filing Date
GB01509/67A Expired GB1215931A (en) 1967-03-11 1967-03-11 Improvements in or relating to gas turbine engines

Country Status (3)

Country Link
US (1) US3523423A (en)
FR (1) FR1564055A (en)
GB (1) GB1215931A (en)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3579992A (en) * 1969-01-03 1971-05-25 United Aircraft Corp Power plant variable geometry control
GB1340879A (en) * 1970-08-11 1973-12-19 Secr Defence Control system for gas turbine engine
GB1310784A (en) * 1970-09-17 1973-03-21 Nissan Motor Control system for gas turbine engine
US3686860A (en) * 1970-09-25 1972-08-29 Chandler Evans Inc Nozzle control
DE2208040C3 (en) * 1972-02-21 1979-05-23 Robert Bosch Gmbh, 7000 Stuttgart Control circuit for the process temperature of a gas turbine
DE2241363B2 (en) * 1972-08-23 1975-01-09 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Control device for a gas turbine engine, in particular a motor vehicle
US3797233A (en) * 1973-06-28 1974-03-19 United Aircraft Corp Integrated control for a turbopropulsion system
US3872292A (en) * 1973-07-26 1975-03-18 Us Navy Sonic means for detecting compressor stall
US3938321A (en) * 1974-03-04 1976-02-17 General Motors Corporation Gas turbine control
US3952502A (en) * 1974-03-04 1976-04-27 General Motors Corporation Gas turbine control
US3971208A (en) * 1974-04-01 1976-07-27 The Garrett Corporation Gas turbine fuel control
US4134258A (en) * 1974-06-10 1979-01-16 Nippondenso Co., Ltd. Fuel control system
GB1519143A (en) * 1974-07-09 1978-07-26 Lucas Industries Ltd Electronic fuel control for a gas turbine engine
GB1519144A (en) * 1974-07-09 1978-07-26 Lucas Industries Ltd Electronic fuel control for a gas turbine engine
US4206597A (en) * 1976-04-23 1980-06-10 The Boeing Company Fan R.P.M. control loop stabilization using high rotor speed
US4397148A (en) * 1980-07-02 1983-08-09 General Electric Company Control system for an augmented turbofan engine
US4813226A (en) * 1987-01-12 1989-03-21 Grosselfinger Robert A Demand control of variable geometry gas turbine power plant
US4947643A (en) * 1988-09-20 1990-08-14 United Technologies Corporation Active geometry control system for gas turbine engines
US5301500A (en) * 1990-07-09 1994-04-12 General Electric Company Gas turbine engine for controlling stall margin
US5206810A (en) * 1991-02-07 1993-04-27 General Electric Company Redundant actuator control
US7011498B2 (en) 1998-04-03 2006-03-14 Athena Technologies, Inc. Optimization method for power generation systems
US9506405B2 (en) 1998-04-03 2016-11-29 Rockwell Collins Control Technologies, Inc. Apparatus and method for controlling power generation system
US6171055B1 (en) * 1998-04-03 2001-01-09 Aurora Flight Sciences Corporation Single lever power controller for manned and unmanned aircraft
US8601786B2 (en) * 2006-10-12 2013-12-10 United Technologies Corporation Operational line management of low pressure compressor in a turbofan engine
EP2066872B1 (en) * 2006-10-12 2014-06-18 United Technologies Corporation Method and device to avoid turbofan instability in a gas turbine engine.

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2933887A (en) * 1953-07-16 1960-04-26 Rolls Royce Compound gas turbine engine with control for low-pressure rotor
US3021668A (en) * 1957-01-11 1962-02-20 Bendix Corp Nozzle area control for turbojet engines
GB862334A (en) * 1958-12-05 1961-03-08 Rolls Royce Improvements in or relating to gas turbine jet propulsion engines
US3289411A (en) * 1963-09-13 1966-12-06 Bendix Corp Coordinated afterburner fuel control and exhaust nozzle area control for gas turbine engine

Also Published As

Publication number Publication date
FR1564055A (en) 1969-04-18
US3523423A (en) 1970-08-11

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