GB2376721A - Fuel injection system for a gas turbine - Google Patents

Fuel injection system for a gas turbine Download PDF

Info

Publication number
GB2376721A
GB2376721A GB0224080A GB0224080A GB2376721A GB 2376721 A GB2376721 A GB 2376721A GB 0224080 A GB0224080 A GB 0224080A GB 0224080 A GB0224080 A GB 0224080A GB 2376721 A GB2376721 A GB 2376721A
Authority
GB
United Kingdom
Prior art keywords
fuel injection
injection system
gas turbine
gas
supply conduit
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
GB0224080A
Other versions
GB0224080D0 (en
GB2376721B (en
Inventor
Johnny Rehn
Jan Magnusson
Alf Andersson
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.)
TURBEC AB
Original Assignee
TURBEC AB
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 TURBEC AB filed Critical TURBEC AB
Publication of GB0224080D0 publication Critical patent/GB0224080D0/en
Publication of GB2376721A publication Critical patent/GB2376721A/en
Application granted granted Critical
Publication of GB2376721B publication Critical patent/GB2376721B/en
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • F02C7/22—Fuel supply systems
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/263—Control of fuel supply by means of fuel metering valves

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Feeding And Controlling Fuel (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)

Abstract

A gas turbine has a fuel injection system for supplying pressurized fuel gas to a combustion chamber (2) of a gas turbine, the fuel injection system having at least one electrically controllable magnetic valve (3, 4, 5) working with pulse-width-modulation, i.e. controlling the gas flow by varying the length of its opening time pulses in relation to its closing time, in a gas supply conduit (15). The fuel injection system has at least one electrically controllable magnetic main valve (3, 4) arranged in the supply conduit (15). Moreover, at least one pilot valve (5) is connected to the supply conduit with its upstream end after the main valve and with its downstream end connected to a conduit (17) leading into a pilot flame chamber (19) inside the combustion chamber (2).

Description

(57) A gas turbine has a fuel injection system for supplying pressurized
fuel gas to a combustion chamber (2) of a gas turbine, the fuel injection system having at least one electrically controllable magnetic valve (3, 4, 5) working with pulse-width-modulation, i.e. controlling the gas flow by varying the length of its opening time pulses in relation to its closing time, in a gas supply conduit (15). The fuel injection system has at least one electrically controllable magnetic main valve (3, 4) arranged in the supply conduit (15. Moreover, at least one pilot valve (5) is connected to the supply conduit with its upstream end after the main valve and with its downstream end connected to a conduit {17} leading into a pilot flame chamber (19) inside the combustion chamber (21.
GB0224080A 2000-04-28 2001-04-27 Fuel injection system for a gas turbine Expired - Fee Related GB2376721B (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE0001552A SE522267C2 (en) 2000-04-28 2000-04-28 Fuel injection for a gas turbine
PCT/SE2001/000931 WO2001083965A1 (en) 2000-04-28 2001-04-27 Fuel injection system for a gas turbine

Publications (3)

Publication Number Publication Date
GB0224080D0 GB0224080D0 (en) 2002-11-27
GB2376721A true GB2376721A (en) 2002-12-24
GB2376721B GB2376721B (en) 2004-07-07

Family

ID=20279462

Family Applications (1)

Application Number Title Priority Date Filing Date
GB0224080A Expired - Fee Related GB2376721B (en) 2000-04-28 2001-04-27 Fuel injection system for a gas turbine

Country Status (5)

Country Link
AU (1) AU2001252845A1 (en)
DE (1) DE10196104B8 (en)
GB (1) GB2376721B (en)
SE (1) SE522267C2 (en)
WO (1) WO2001083965A1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE521293C2 (en) * 2001-02-06 2003-10-21 Volvo Aero Corp Method and apparatus for supplying fuel to a combustion chamber
ITMI20111576A1 (en) * 2011-09-02 2013-03-03 Alstom Technology Ltd METHOD TO SWITCH A COMBUSTION DEVICE
DE102011118688A1 (en) * 2011-11-16 2013-05-16 Daimler Ag Flow-driven device
DE102018123785B4 (en) 2018-09-26 2023-07-27 Deutsches Zentrum für Luft- und Raumfahrt e.V. Method of operating a gas turbine assembly and gas turbine assembly

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4926629A (en) * 1988-10-28 1990-05-22 Allied-Signal Inc. Low cost fuel supply system for gas turbine engines
EP0423919A2 (en) * 1989-08-04 1991-04-24 Williams International Corporation Continuous flow fuel control system
US5913807A (en) * 1998-03-30 1999-06-22 Williams International Corp. L.L.C. Turbojet engine start system
WO1999032771A1 (en) * 1997-12-19 1999-07-01 Sundstrand Corporation Pulse width modulated low pressure fuel control

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2751743C2 (en) * 1977-11-19 1985-04-18 Pierburg Luftfahrtgeräte Union GmbH, 4040 Neuss Method and control device for metering flowing media
JP2758301B2 (en) * 1991-11-29 1998-05-28 株式会社東芝 Gas turbine combustor
DE19620874A1 (en) * 1996-05-23 1997-11-27 Bmw Rolls Royce Gmbh Fuel injection for a staged gas turbine combustor

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4926629A (en) * 1988-10-28 1990-05-22 Allied-Signal Inc. Low cost fuel supply system for gas turbine engines
EP0423919A2 (en) * 1989-08-04 1991-04-24 Williams International Corporation Continuous flow fuel control system
WO1999032771A1 (en) * 1997-12-19 1999-07-01 Sundstrand Corporation Pulse width modulated low pressure fuel control
US5913807A (en) * 1998-03-30 1999-06-22 Williams International Corp. L.L.C. Turbojet engine start system

Also Published As

Publication number Publication date
SE522267C2 (en) 2004-01-27
DE10196104B8 (en) 2011-05-05
AU2001252845A1 (en) 2001-11-12
DE10196104B4 (en) 2011-02-10
GB0224080D0 (en) 2002-11-27
DE10196104T1 (en) 2003-04-30
SE0001552L (en) 2001-10-29
WO2001083965A1 (en) 2001-11-08
GB2376721B (en) 2004-07-07
SE0001552D0 (en) 2000-04-28

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Legal Events

Date Code Title Description
732E Amendments to the register in respect of changes of name or changes affecting rights (sect. 32/1977)
PCNP Patent ceased through non-payment of renewal fee

Effective date: 20120427