GB1537278A - Gas turbine igniter systems - Google Patents

Gas turbine igniter systems

Info

Publication number
GB1537278A
GB1537278A GB5208075A GB5208075A GB1537278A GB 1537278 A GB1537278 A GB 1537278A GB 5208075 A GB5208075 A GB 5208075A GB 5208075 A GB5208075 A GB 5208075A GB 1537278 A GB1537278 A GB 1537278A
Authority
GB
United Kingdom
Prior art keywords
igniter
alternator
circuit
engine
exciter
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
GB5208075A
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 GB1537278A publication Critical patent/GB1537278A/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
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition

Abstract

1537278 Gas turbine ignition systems; afterburning 19 Dec 1975 [30 Dec 1974] 52080/75 Headings F1G and F1J An igniter in a gas turbine engine combustor is connected to a power source when the turbine shaft deceleration rate reaches a predetermined level following flameout. In the system shown, igniter 25 in an afterburner section is energized when an aircraft reaches a predetermined speed and a given throttle position is selected, at which stage a low voltage DC signal on 54 operates relay coil CR-2 to open CR-2A and close CR-2B to connector augmentor exciter 48 across alternator 43. Igniter 33 in the combustion chamber 27 is connected to a relatively low energy exciter 42 which is connected to a power source 60 via a switch 63 operable by the pilot, this igniter being adapted to operate continuously for long periods without risk of burning out. Igniter 34 in the combustion chamber is connected to a relatively high energy exciter 41 and is adapted to operate for a predetermined period following flameout. While the engine is being run up to a predetermined threshold speed, the contacts CR-1A, CR-1B are set to connect exciter 41 across the alternator, but once the engine reaches the threshold speed AND gate 67 causes coil CR-1 to open CR-1A and close CR-1B to de-energize igniter 34. When, due to flameout, the deceleration rate exceeds a given level for a given period, circuit 69 deactivates circuit 71 and a rate signal is applied to the AND gate to cause coil CR-1 to reset CR-1A and CR-1B to energize igniter 34 for a given period governed by circuit 71. Switch 57 can be closed to short-circuit the alternator and thereby provide for cranking or windmilling of the engine without ignition occurring. A switch 59 can be closed to energize relay CR-5 and close CR-5A to shortcircuit the alternator when effecting a wet prestart.
GB5208075A 1974-12-30 1975-12-19 Gas turbine igniter systems Expired GB1537278A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US53726474A 1974-12-30 1974-12-30

Publications (1)

Publication Number Publication Date
GB1537278A true GB1537278A (en) 1978-12-29

Family

ID=24141922

Family Applications (2)

Application Number Title Priority Date Filing Date
GB1926478A Expired GB1537279A (en) 1974-12-30 1975-12-19 Gas turbine igniter systems
GB5208075A Expired GB1537278A (en) 1974-12-30 1975-12-19 Gas turbine igniter systems

Family Applications Before (1)

Application Number Title Priority Date Filing Date
GB1926478A Expired GB1537279A (en) 1974-12-30 1975-12-19 Gas turbine igniter systems

Country Status (6)

Country Link
JP (1) JPS5198417A (en)
BE (1) BE837177A (en)
DE (1) DE2558756A1 (en)
FR (1) FR2296765A1 (en)
GB (2) GB1537279A (en)
IT (1) IT1052012B (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5523691A (en) * 1990-07-26 1996-06-04 Unison Industries Limited Partnership Diagnostic device for gas turbine ignition system
US5561350A (en) 1988-11-15 1996-10-01 Unison Industries Ignition System for a turbine engine
US5675257A (en) * 1990-07-26 1997-10-07 Unison Industries Limited Partnership Diagnostic device for gas turbine ignition system
US5754011A (en) 1995-07-14 1998-05-19 Unison Industries Limited Partnership Method and apparatus for controllably generating sparks in an ignition system or the like
US6670777B1 (en) 2002-06-28 2003-12-30 Woodward Governor Company Ignition system and method
WO2013139974A1 (en) * 2012-03-23 2013-09-26 Snecma Ignition unit for turbojet engine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2722449C2 (en) * 1977-05-18 1982-08-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Ignition device of a combustion chamber for gas turbine engines, in particular for gas turbine jet engines of aircraft
FR2496762B1 (en) * 1980-12-24 1985-06-28 Psa Grpt Int Eco Rech Develop IGNITION AND RE-IGNITION DEVICE FOR GAS TURBINE
FR3118994B1 (en) * 2021-01-15 2022-12-23 Safran Helicopter Engines IGNITION METHOD AND DEVICE

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB701659A (en) * 1950-10-11 1953-12-30 Carburation Pour L Automobile Improvements in or relating to electric ignition starting devices for gas turbine engines
US2881587A (en) * 1955-08-23 1959-04-14 Bendix Aviat Corp Electrical apparatus having means to control the supply of energy from a coil to a plurality of circuits
US2938147A (en) * 1959-02-17 1960-05-24 John J Rose Continuous ignition system for a turbojet engine
FR1319068A (en) * 1961-04-07 1963-02-22 Rolls Royce Combustion chamber of a gas turbo-engine
US3041833A (en) * 1961-07-06 1962-07-03 Paul J Vore Turbo jet and turbo prop engine relite device
GB1340879A (en) * 1970-08-11 1973-12-19 Secr Defence Control system for gas turbine engine
US3765176A (en) * 1972-02-22 1973-10-16 Gen Motors Corp Automatic relight
GB1415681A (en) * 1972-06-24 1975-11-26 Rolls Royce Flame-out control in gas turbine engine
US3793826A (en) * 1972-12-08 1974-02-26 Gen Motors Corp Electronic start control circuit for gas turbine engine

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5561350A (en) 1988-11-15 1996-10-01 Unison Industries Ignition System for a turbine engine
US5523691A (en) * 1990-07-26 1996-06-04 Unison Industries Limited Partnership Diagnostic device for gas turbine ignition system
US5675257A (en) * 1990-07-26 1997-10-07 Unison Industries Limited Partnership Diagnostic device for gas turbine ignition system
US5754011A (en) 1995-07-14 1998-05-19 Unison Industries Limited Partnership Method and apparatus for controllably generating sparks in an ignition system or the like
US6034483A (en) 1995-07-14 2000-03-07 Unison Industries, Inc. Method for generating and controlling spark plume characteristics
US6353293B1 (en) 1995-07-14 2002-03-05 Unison Industries Method and apparatus for controllably generating sparks in an ignition system or the like
US6670777B1 (en) 2002-06-28 2003-12-30 Woodward Governor Company Ignition system and method
WO2013139974A1 (en) * 2012-03-23 2013-09-26 Snecma Ignition unit for turbojet engine
FR2988435A1 (en) * 2012-03-23 2013-09-27 Snecma IGNITION BOX FOR IGNITION SEGREGATION TURBOJUSTER
CN104204468A (en) * 2012-03-23 2014-12-10 斯奈克玛 Ignition unit for turbojet engine
CN104204468B (en) * 2012-03-23 2016-10-26 斯奈克玛 Igniting unit for turbofan
RU2616726C2 (en) * 2012-03-23 2017-04-18 Снекма Ignition unit for jet-turbine engine
US9915207B2 (en) 2012-03-23 2018-03-13 Snecma Ignition unit for turbojet engine

Also Published As

Publication number Publication date
DE2558756A1 (en) 1976-07-08
BE837177A (en) 1976-04-16
FR2296765A1 (en) 1976-07-30
JPS5198417A (en) 1976-08-30
IT1052012B (en) 1981-06-20
GB1537279A (en) 1978-12-29

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Legal Events

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

Effective date: 19931219