FR2365024A1 - Procede et dispositif pour calculer la temperature a l'entree de la turbine d'une turbomachine a gaz - Google Patents

Procede et dispositif pour calculer la temperature a l'entree de la turbine d'une turbomachine a gaz

Info

Publication number
FR2365024A1
FR2365024A1 FR7727426A FR7727426A FR2365024A1 FR 2365024 A1 FR2365024 A1 FR 2365024A1 FR 7727426 A FR7727426 A FR 7727426A FR 7727426 A FR7727426 A FR 7727426A FR 2365024 A1 FR2365024 A1 FR 2365024A1
Authority
FR
France
Prior art keywords
temperature
turbine
inlet
burner
air flow
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.)
Withdrawn
Application number
FR7727426A
Other languages
English (en)
Inventor
John Kniat
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of FR2365024A1 publication Critical patent/FR2365024A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • F05D2270/01—Purpose of the control system
    • F05D2270/11—Purpose of the control system to prolong engine life
    • F05D2270/112—Purpose of the control system to prolong engine life by limiting temperatures
    • 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
    • F05D2270/3013—Outlet pressure
    • 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
    • F05D2270/303—Temperature
    • 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
    • F05D2270/70—Type of control algorithm
    • F05D2270/71—Type of control algorithm synthesized, i.e. parameter computed by a mathematical model

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Measuring Volume Flow (AREA)
  • Regulation And Control Of Combustion (AREA)
  • Investigating Or Analyzing Materials Using Thermal Means (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
  • Control Of Turbines (AREA)
  • Measuring Temperature Or Quantity Of Heat (AREA)

Abstract

Procédé et dispositif pour calculer la température à l'entrée de la turbine d'une turbomachine à gaz. On établit le rapport entre les pressions statique et totale à la sortie du compresseur 14; un genérateur de fonction en tire la valeur corrigée du débit d'air au brûleur qui, à l'aide de calculs convenables, donne le débit d'air calculé au brûleur. L'équation empirique suivante permet alors de calculer la température (T4 ) à l'entrée de la turbine 18 T4 = T3 + K1 (K2 T3 +K3 ) f/a + K4 où T3 est la température mesurée à la sortie du compresseur, f/a est le rapport entre le débit mesuré du combustible et le débit calculé de l'air au brûleur, K1 , K2 , L3 et K 4 sont des constantes de construction. L'invention fournit une meilleure valeur de la température d'entrée à la turbine, et permet donc un meilleur contrôle.
FR7727426A 1976-09-15 1977-09-12 Procede et dispositif pour calculer la temperature a l'entree de la turbine d'une turbomachine a gaz Withdrawn FR2365024A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US05/723,364 US4055997A (en) 1976-09-15 1976-09-15 Means for calculating turbine inlet temperature of a gas turbine engine

Publications (1)

Publication Number Publication Date
FR2365024A1 true FR2365024A1 (fr) 1978-04-14

Family

ID=24905917

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7727426A Withdrawn FR2365024A1 (fr) 1976-09-15 1977-09-12 Procede et dispositif pour calculer la temperature a l'entree de la turbine d'une turbomachine a gaz

Country Status (11)

Country Link
US (1) US4055997A (fr)
JP (1) JPS5335809A (fr)
BE (1) BE858556A (fr)
BR (1) BR7706043A (fr)
CA (1) CA1108761A (fr)
CH (1) CH629590A5 (fr)
DE (1) DE2739434A1 (fr)
FR (1) FR2365024A1 (fr)
GB (1) GB1580638A (fr)
IL (1) IL52915A (fr)
SE (1) SE7709976L (fr)

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2011091B (en) * 1977-12-22 1982-04-28 Gen Electric Method and apparatus for calculating turbine inlet temperature
JPS54137509A (en) * 1978-04-19 1979-10-25 Mitsubishi Heavy Ind Ltd Gas turbine inlet temperature estimation circuit
US4336713A (en) * 1980-08-06 1982-06-29 The United States Of America As Represented By The Secretary Of The Air Force Compensated temperature sensing device
US4744670A (en) * 1986-05-05 1988-05-17 Honeywell, Inc. Method and apparatus for monitoring the temperature of the propulsion gas at the inlet to a high-performance turbine wheel
JP2543549B2 (ja) * 1987-12-22 1996-10-16 株式会社日立製作所 ガスタ―ビンの燃焼監視方法、及び同監視装置
US5080496A (en) * 1990-06-25 1992-01-14 General Electric Company Method and apparatus for compensated temperature prediction
JPH0472430A (ja) * 1990-07-10 1992-03-06 Toyota Motor Corp ガスタービン機関の制御方法
US5397181A (en) * 1993-10-21 1995-03-14 General Electric Company Compressor discharge temperature sensing system
DE4443812A1 (de) * 1994-12-09 1996-06-13 Bosch Gmbh Robert Verfahren zur Bildung eines Signals bezüglich der Temperatur der von einer Brennkraftmaschine angesaugten Luft
US5622042A (en) * 1995-02-27 1997-04-22 Compressor Controls Corporation Method for predicting and using the exhaust gas temperatures for control of two and three shaft gas turbines
US6952639B2 (en) * 2002-11-12 2005-10-04 General Electric Company Method and system for temperature estimation of gas turbine combustion cans
CA2626035C (fr) 2005-10-18 2014-12-02 Alstom Technology Ltd Methode de protection des parties de gaz chaudes d'une installation a turbine a gaz contre une surchauffe et de detection d'une extinction de flamme dans la chambre de combustion
DE102006037560B4 (de) * 2006-02-06 2008-06-19 Siemens Ag Verfahren und Vorrichtung zum vorausschauenden Bestimmen einer Temperaturverteilung in einer Wand einer Turbinenanlage
GB2437296B (en) * 2006-04-22 2008-06-11 Rolls Royce Plc Fuel control system
US20070245707A1 (en) * 2006-04-22 2007-10-25 Rolls-Royce Plc Fuel control system
US20110154821A1 (en) * 2009-12-24 2011-06-30 Lincoln Evans-Beauchamp Estimating Pre-Turbine Exhaust Temperatures
EP2357339A1 (fr) * 2010-02-12 2011-08-17 Siemens Aktiengesellschaft Procédé de détermination de la température de sortie d'une chambre de combustion et procédé de commande de turbine à gaz
JP5615052B2 (ja) * 2010-06-16 2014-10-29 三菱重工業株式会社 ガスタービンプラント及びガスタービンプラントの制御方法
US20130074519A1 (en) * 2011-09-26 2013-03-28 Honeywell International Inc. Auxiliary power unit inlet door position control system and method
US9335046B2 (en) * 2012-05-30 2016-05-10 General Electric Company Flame detection in a region upstream from fuel nozzle
US9850823B2 (en) * 2013-12-26 2017-12-26 Siemens Aktiengesellschaft Control system and method for controlling a gas turbine engine during transients
GB201414662D0 (en) * 2014-08-19 2014-10-01 Rolls Royce Plc Method of operation of a gas turbine engine
US11111858B2 (en) 2017-01-27 2021-09-07 General Electric Company Cool core gas turbine engine
EP3561269A1 (fr) * 2018-04-23 2019-10-30 Siemens Aktiengesellschaft Commande de système de combustion
US11703890B2 (en) 2018-10-30 2023-07-18 Hamilton Sundstrand Corporation Determining and controlling a weight flow in an environmental control system
GB201908972D0 (en) 2019-06-24 2019-08-07 Rolls Royce Plc Compression in a gas turbine engine
GB201908978D0 (en) 2019-06-24 2019-08-07 Rolls Royce Plc Gas turbine engine transfer efficiency
US11542875B2 (en) 2020-03-16 2023-01-03 Pratt & Whitney Canada Corp. Method and system for determining an engine temperature
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2809492A (en) * 1952-12-23 1957-10-15 Simmonds Aerocessories Inc Apparatus for measuring and/or controlling fuel/air ratio of gas turbines without direct gravimetric fuel metering
US3377848A (en) * 1966-08-22 1968-04-16 Gen Electric Temperature indicating means for gas turbine engines
US3789665A (en) * 1972-02-22 1974-02-05 Avco Corp Inferred measurement of the turbine inlet temperature of a gas turbine engine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2809492A (en) * 1952-12-23 1957-10-15 Simmonds Aerocessories Inc Apparatus for measuring and/or controlling fuel/air ratio of gas turbines without direct gravimetric fuel metering
US3377848A (en) * 1966-08-22 1968-04-16 Gen Electric Temperature indicating means for gas turbine engines
US3789665A (en) * 1972-02-22 1974-02-05 Avco Corp Inferred measurement of the turbine inlet temperature of a gas turbine engine

Also Published As

Publication number Publication date
GB1580638A (en) 1980-12-03
CA1108761A (fr) 1981-09-08
BR7706043A (pt) 1978-06-06
US4055997A (en) 1977-11-01
IL52915A (en) 1979-09-30
SE7709976L (sv) 1978-03-16
BE858556A (fr) 1978-01-02
JPS5335809A (en) 1978-04-03
CH629590A5 (de) 1982-04-30
DE2739434A1 (de) 1978-03-16

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