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GB1452487A - Reheat fuel control systems - Google Patents

Reheat fuel control systems

Info

Publication number
GB1452487A
GB1452487A GB3290373A GB3290373A GB1452487A GB 1452487 A GB1452487 A GB 1452487A GB 3290373 A GB3290373 A GB 3290373A GB 3290373 A GB3290373 A GB 3290373A GB 1452487 A GB1452487 A GB 1452487A
Authority
GB
United Kingdom
Prior art keywords
buzz
signal
pressure
filter
transducer
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
GB3290373A
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.)
SECR DEFENCE
UK Secretary of State for Defence
Original Assignee
SECR DEFENCE
UK Secretary of State for Defence
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 SECR DEFENCE, UK Secretary of State for Defence filed Critical SECR DEFENCE
Priority to GB3290373A priority Critical patent/GB1452487A/en
Publication of GB1452487A publication Critical patent/GB1452487A/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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure

Landscapes

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

Abstract

1452487 Automatic control systems DEFENCE SECRETARY OF STATE FOR 3 July 1974 [10 July 1973] 32903/73 Heading G3R The buzz (high frequency pressure variations) in an aircraft gas turbine engine re-heat section is controlled by varying the fuel supply to the section according to the comparison between a predetermined buzz amplitude and the measured buzz. The latter is obtained from a pressure transducer in the re-heat section via a filter that passes only the pressure variations at buzz frequency. As shown, the buzz signal is obtained from the pressure transducer 30 using a band-pass filter 31, with a characteristic as Fig. 3 (not shown), halfwave rectifier 32 and first order filter 33. The output of transducer 30 is also used by a high frequency filter 36 to derive a signal dependent upon the mean pressure PJ. Circuit 37 divides the sampled buzz signal by the mean pressure to form a normalized buzz signal which is compared with pre-set levels, Fig. 4 (not shown), the comparison being used to control the re-heat fuel supply. According to whether the buzz is below or above a first level (50) the fuel flow is respectively either unchanged or reduced in increments, the aircraft throttle being over-ridden. If a second buzz level (51) is exceeded e.g. for three samples the fuel flow is reduced by a larger amount.
GB3290373A 1973-07-10 1973-07-10 Reheat fuel control systems Expired GB1452487A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3290373A GB1452487A (en) 1973-07-10 1973-07-10 Reheat fuel control systems

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3290373A GB1452487A (en) 1973-07-10 1973-07-10 Reheat fuel control systems

Publications (1)

Publication Number Publication Date
GB1452487A true GB1452487A (en) 1976-10-13

Family

ID=10345744

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3290373A Expired GB1452487A (en) 1973-07-10 1973-07-10 Reheat fuel control systems

Country Status (1)

Country Link
GB (1) GB1452487A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2126382A (en) * 1982-08-10 1984-03-21 Nissan Motor Gas turbine engine control system
FR2657921A1 (en) * 1990-01-02 1991-08-09 Gen Electric
EP0735263A1 (en) * 1995-03-29 1996-10-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Avoiding combustion instabilities in a reheat combustor

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2126382A (en) * 1982-08-10 1984-03-21 Nissan Motor Gas turbine engine control system
US4545198A (en) * 1982-08-10 1985-10-08 Nissan Motor Company, Limited Gas turbine engine control system
FR2657921A1 (en) * 1990-01-02 1991-08-09 Gen Electric
EP0735263A1 (en) * 1995-03-29 1996-10-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Avoiding combustion instabilities in a reheat combustor
FR2732407A1 (en) * 1995-03-29 1996-10-04 Snecma PROCESS FOR AVOIDING COMBUSTION INSTABILITIES IN A TURBO-JET
US5699663A (en) * 1995-03-29 1997-12-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Method of preventing instabilities produced by combustion in a turbojet engine
JP3349885B2 (en) 1995-03-29 2002-11-25 ソシエテ・ナシオナル・デテユード・エ・ドウ・コンストリユクシオン・ドウ・モトール・ダヴイアシオン、“エス．エヌ．ウ．セ．エム．アー．” How to prevent instability caused by turbojet engine combustion

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee