GB740090A - Improvements relating to starting and ignition systems for gas turbine engines - Google Patents

Improvements relating to starting and ignition systems for gas turbine engines

Info

Publication number
GB740090A
GB740090A GB3161652D GB3161652D GB740090A GB 740090 A GB740090 A GB 740090A GB 3161652 D GB3161652 D GB 3161652D GB 3161652 D GB3161652 D GB 3161652D GB 740090 A GB740090 A GB 740090A
Authority
GB
United Kingdom
Prior art keywords
auxiliary
contacts
combustion chamber
lead
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
GB3161652D
Inventor
Harold Edward William West
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 GB3161652D priority Critical patent/GB740090A/en
Publication of GB740090A publication Critical patent/GB740090A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, 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
    • F02C7/26Starting; Ignition
    • F02C7/268Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/275Mechanical drives
    • F02C7/277Mechanical drives the starter being a separate turbine
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, 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
    • F02C7/26Starting; Ignition
    • F02C7/264Ignition
    • F02C7/266Electric

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

740,090. Gas turbine plant. ROLLSROYCE, Ltd. Dec. 11, 1953 [Dec. 12, 1952], No. 31616/52. Class 110(3) A starter system for 'a gas turbine engine started by an auxiliary turbine supplied with combustion products from an independent combustion chamber, comprising electrical igniter means in both the main and auxiliary combustion chambers and a source of electrical energy for supplying both igniter means, has switching means for transferring said source from the igniter in the auxiliary combustion chamber to the igniter in the main combustion chamber at an appropriate point in the course of starting the gas turbine engine. To start the engine, a manual push-button 30 is closed. This energizes a relay coil 31 of a rotary time control mechanism having cams which close the contacts 32, 33 and 34 and allow the push-button 30 to be released. The closure of contacts 32 energizes a relay 35 which closes contacts 36 and thereby energizes the solenoids 37, 38. These solenoids open valves controlling the air and fuel supply to an auxiliary combustion chamber supplying combustion gases to a starter turbine. These valves are spring-loaded to the closed position. The closure of contacts 33 energizes the high tension supply apparatus 39 which is connected through the lead 40 to a switching relay 42. The armature 44 is biased by a spring 43 to make contact on a lead 26A feeding the igniter means in the main combustion chamber. The closure of contacts 34 energizes relay coil 45 causing the armature 44 to connect the lead 40 with the lead 25A feeding the igniter means in the auxiliary combustion chamber. After a predetermined time, the time control mechanism opens the contacts 32, 33, which causes the relay 35 and high tension supply apparatus 39 to be de-energized. The fuel and air supply to the auxiliary combustion chamber is then shut off. When the auxiliary turbine drives a compressor supplying combustion air to the auxiliary combustion chamber the solenoid 38 and the valve operated'by it may be dispensed with. In a mcdification of this arrangement the solenoid 38 may be replaced by an electric starting motor for the auxiliary turbine. The time control mechanism may be replaced by a centrifugally operated switch responsive to the speed of the auxiliary turbine, or by a temperature responsive switch responsive to the temperature of the exhaust gases of the auxiliary turbine. In a preferred arrangement, the time control mechanism is retained and the centrifugally operated switch or temperature responsive switch is arranged in series with the contacts 34 to de-energize the relay coil 45 and so connect the lead 40 with the lead 26A. An overspeed centrifugally operated switch driven by the auxiliary turbine may be placed in the lead between the battery and contacts 33 to shut down the auxiliary turbine when it reaches a preselected speed.
GB3161652D 1952-12-12 1952-12-12 Improvements relating to starting and ignition systems for gas turbine engines Expired GB740090A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3161652D GB740090A (en) 1952-12-12 1952-12-12 Improvements relating to starting and ignition systems for gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3161652D GB740090A (en) 1952-12-12 1952-12-12 Improvements relating to starting and ignition systems for gas turbine engines

Publications (1)

Publication Number Publication Date
GB740090A true GB740090A (en) 1955-11-09

Family

ID=10325808

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3161652D Expired GB740090A (en) 1952-12-12 1952-12-12 Improvements relating to starting and ignition systems for gas turbine engines

Country Status (1)

Country Link
GB (1) GB740090A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004099604A2 (en) * 2003-05-05 2004-11-18 Aloys Wobben Operating method for a wind park
FR3015571A1 (en) * 2013-12-23 2015-06-26 Turbomeca METHOD AND SYSTEM FOR RELIABLY STARTING TURBOMACHINE
US10316689B2 (en) 2016-08-22 2019-06-11 Rolls-Royce Corporation Gas turbine engine health monitoring system with shaft-twist sensors

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9303625B2 (en) 2003-05-05 2016-04-05 Aloys Wobben Operating method for a wind park
WO2004099604A3 (en) * 2003-05-05 2005-01-27 Aloys Wobben Operating method for a wind park
CN100357590C (en) * 2003-05-05 2007-12-26 艾劳埃斯·乌本 Operating method for a wind park
US8108079B2 (en) 2003-05-05 2012-01-31 Aloys Wobben Operating method for a wind park
WO2004099604A2 (en) * 2003-05-05 2004-11-18 Aloys Wobben Operating method for a wind park
FR3015571A1 (en) * 2013-12-23 2015-06-26 Turbomeca METHOD AND SYSTEM FOR RELIABLY STARTING TURBOMACHINE
WO2015097361A1 (en) * 2013-12-23 2015-07-02 Turbomeca Method and system for more reliable starting of a turbo machine
CN105849390A (en) * 2013-12-23 2016-08-10 涡轮梅坎公司 Method and system for more reliable starting of a turbo machine
JP2017503954A (en) * 2013-12-23 2017-02-02 ターボメカTurbomeca Method and system for reliably starting a turbine engine
RU2666029C2 (en) * 2013-12-23 2018-09-05 Турбомека Method and system for reliable starting turbine engine
CN105849390B (en) * 2013-12-23 2019-06-07 涡轮梅坎公司 Method and system for reliably starting turbine engine
US10450962B2 (en) 2013-12-23 2019-10-22 Safran Helicopter Engines Method and a system for reliably starting a turbine engine
US10316689B2 (en) 2016-08-22 2019-06-11 Rolls-Royce Corporation Gas turbine engine health monitoring system with shaft-twist sensors

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