JPS5751914A - Fuel controller for gas turbine engine - Google Patents

Fuel controller for gas turbine engine

Info

Publication number
JPS5751914A
JPS5751914A JP12531380A JP12531380A JPS5751914A JP S5751914 A JPS5751914 A JP S5751914A JP 12531380 A JP12531380 A JP 12531380A JP 12531380 A JP12531380 A JP 12531380A JP S5751914 A JPS5751914 A JP S5751914A
Authority
JP
Japan
Prior art keywords
time
fuel
gas generator
flow rate
point
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.)
Pending
Application number
JP12531380A
Other languages
Japanese (ja)
Inventor
Tadashi Kobayashi
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.)
Nissan Motor Co Ltd
Original Assignee
Nissan Motor Co Ltd
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 Nissan Motor Co Ltd filed Critical Nissan Motor Co Ltd
Priority to JP12531380A priority Critical patent/JPS5751914A/en
Publication of JPS5751914A publication Critical patent/JPS5751914A/en
Pending legal-status Critical Current

Links

Landscapes

  • Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)

Abstract

PURPOSE: To suppress cycle maximum temperature to a low level without worsening acceleration performance of a gas generator, by adequately controlling a fuel flow rate at the time of starting a gas turbine engine.
CONSTITUTION: From the point of time at the beginning of an engine start to the point of time at firing decision, a voltage signal V1, feeding fuel at an optimum firring flow rate for preset self sustaining operation, is output from a setter circuit 20 to a fuel control valve 10 through a switching circuit 9. And from the point of time at the firing decision until speed of a gas generator shaft reaches a preset value N2, a voltage signal V2, suppressing fuel feed to constant, is output to the fuel control valve 10. Further from the time for the gas generator shaft speed to reach said preset value N2 to the time to reach a closed loop control start, a voltage signsl V3, gradually increasing a feed flow rate of fuel, is similarly output to obtain stable acceleration performance of the gas generator shaft.
COPYRIGHT: (C)1982,JPO&Japio
JP12531380A 1980-09-11 1980-09-11 Fuel controller for gas turbine engine Pending JPS5751914A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP12531380A JPS5751914A (en) 1980-09-11 1980-09-11 Fuel controller for gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP12531380A JPS5751914A (en) 1980-09-11 1980-09-11 Fuel controller for gas turbine engine

Publications (1)

Publication Number Publication Date
JPS5751914A true JPS5751914A (en) 1982-03-27

Family

ID=14907007

Family Applications (1)

Application Number Title Priority Date Filing Date
JP12531380A Pending JPS5751914A (en) 1980-09-11 1980-09-11 Fuel controller for gas turbine engine

Country Status (1)

Country Link
JP (1) JPS5751914A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003060303A1 (en) * 2002-01-09 2003-07-24 Ebara Corporation A gas turbine apparatus and a starting method thereof
JP2019056365A (en) * 2017-06-30 2019-04-11 ゼネラル・エレクトリック・カンパニイ Propulsion system for aircraft
CN110735721A (en) * 2019-10-22 2020-01-31 北京动力机械研究所 liquid ramjet air scoop oil path fuel oil flow closed-loop control method

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003060303A1 (en) * 2002-01-09 2003-07-24 Ebara Corporation A gas turbine apparatus and a starting method thereof
US7000405B2 (en) 2002-01-09 2006-02-21 Ebara Corporation Gas turbine apparatus and a starting method thereof
JP2019056365A (en) * 2017-06-30 2019-04-11 ゼネラル・エレクトリック・カンパニイ Propulsion system for aircraft
CN110735721A (en) * 2019-10-22 2020-01-31 北京动力机械研究所 liquid ramjet air scoop oil path fuel oil flow closed-loop control method

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