GB2011091A - Method and apparatus for calculating turbine inlet temperature - Google Patents

Method and apparatus for calculating turbine inlet temperature

Info

Publication number
GB2011091A
GB2011091A GB7841650A GB7841650A GB2011091A GB 2011091 A GB2011091 A GB 2011091A GB 7841650 A GB7841650 A GB 7841650A GB 7841650 A GB7841650 A GB 7841650A GB 2011091 A GB2011091 A GB 2011091A
Authority
GB
United Kingdom
Prior art keywords
inlet
combustor
turbine
temperature
inlet temperature
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
GB7841650A
Other versions
GB2011091B (en
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB2011091A publication Critical patent/GB2011091A/en
Application granted granted Critical
Publication of GB2011091B publication Critical patent/GB2011091B/en
Expired legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K13/00—Thermometers specially adapted for specific purposes
    • G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
    • G01K13/028—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow for use in total air temperature [TAT] probes
    • 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
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K13/00—Thermometers specially adapted for specific purposes
    • G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
    • 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
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Investigating Or Analyzing Materials Using Thermal Means (AREA)

Abstract

Turbine inlet temperature is calculated in terms of combustor inlet temperature, combustor inlet pressure, fuel flow into the combustor, and flow area of the turbine inlet by applying the formula: <IMAGE> where T4 = the total temperature of the gases at the inlet to the turbine; T3 = the total temperature of the gases at the inlet of the combustor; Wf = the weight flow of fuel into the combustor; PS3 = the static pressure at the inlet to the combustor; A4 = the flow area of the inlet to the turbine; and k1, k2, k3 and k4 = constant coefficients which are calculated for a particular engine design by the use of an iterative process. The formula is evaluated in the circuit shown, an output 58 of the circuit controlling the fuel feed so as to control the turbine inlet temperature. <IMAGE>
GB7841650A 1977-12-22 1978-10-23 Method and apparatus for calculating turbine inlet temperature Expired GB2011091B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US86348377A 1977-12-22 1977-12-22

Publications (2)

Publication Number Publication Date
GB2011091A true GB2011091A (en) 1979-07-04
GB2011091B GB2011091B (en) 1982-04-28

Family

ID=25341170

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7841650A Expired GB2011091B (en) 1977-12-22 1978-10-23 Method and apparatus for calculating turbine inlet temperature

Country Status (5)

Country Link
JP (1) JPS5490409A (en)
DE (1) DE2850625A1 (en)
FR (1) FR2412891A1 (en)
GB (1) GB2011091B (en)
IT (1) IT1100560B (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0273849A2 (en) * 1986-12-08 1988-07-06 United Technologies Corporation Inlet total temperature synthesis for gas turbine engines
EP0684370A2 (en) * 1994-05-27 1995-11-29 ROLLS-ROYCE plc Gas turbine engine fuel control system
EP0728919A1 (en) * 1995-02-27 1996-08-28 Compressor Controls Corporation The fuel supply for a gas turbine regulated in accordance with a synthesized turbine inlet temperature
WO2004033874A1 (en) * 2002-10-10 2004-04-22 Mitsubishi Heavy Industries, Ltd. Combustor controller
GB2397395A (en) * 2003-01-16 2004-07-21 Rolls Royce Plc Controlling a fuel supply to a combustor of a gas turbine engine
EP1482150A2 (en) 2003-05-30 2004-12-01 United Technologies Corporation Method and system of synthesizing turbine inlet temperature of a turbo machine
CN100365256C (en) * 2005-12-26 2008-01-30 王菲 Pulsating flow gas turbine
EP2357339A1 (en) * 2010-02-12 2011-08-17 Siemens Aktiengesellschaft Method of determining a combustor exit temperature and method of controlling a gas turbine
CN113378328A (en) * 2021-07-05 2021-09-10 中国航发湖南动力机械研究所 Gas turbine front temperature calculation method for control system

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2626035C (en) 2005-10-18 2014-12-02 Alstom Technology Ltd Method for protecting the hot gas parts of a gas turbine installation from overheating and for detecting flame extinction in the combustion chamber
DE102006037560B4 (en) * 2006-02-06 2008-06-19 Siemens Ag Method and device for predictive determination of a temperature distribution in a wall of a turbine plant

Family Cites Families (4)

* 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
US4055997A (en) * 1976-09-15 1977-11-01 United Technologies Corporation Means for calculating turbine inlet temperature of a gas turbine engine

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0273849A2 (en) * 1986-12-08 1988-07-06 United Technologies Corporation Inlet total temperature synthesis for gas turbine engines
EP0273849A3 (en) * 1986-12-08 1988-07-20 United Technologies Corporation Inlet total temperature synthesis for gas turbine engines
EP0684370A2 (en) * 1994-05-27 1995-11-29 ROLLS-ROYCE plc Gas turbine engine fuel control system
EP0684370A3 (en) * 1994-05-27 1998-05-06 ROLLS-ROYCE plc Gas turbine engine fuel control system
EP0728919A1 (en) * 1995-02-27 1996-08-28 Compressor Controls Corporation The fuel supply for a gas turbine regulated in accordance with a synthesized turbine inlet temperature
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
WO2004033874A1 (en) * 2002-10-10 2004-04-22 Mitsubishi Heavy Industries, Ltd. Combustor controller
CN100360776C (en) * 2002-10-10 2008-01-09 三菱重工业株式会社 Combustor controller
US7191588B2 (en) 2002-10-10 2007-03-20 Mitsubishi Heavy Industries, Ltd Combustor controller
GB2397395B (en) * 2003-01-16 2006-04-05 Rolls Royce Plc Controlling the fuel supply to a combustor of a gas turbine engine
US7007485B2 (en) 2003-01-16 2006-03-07 Rolls-Royce Plc Controlling the fuel supply to a combustor of a gas turbine engine
GB2397395A (en) * 2003-01-16 2004-07-21 Rolls Royce Plc Controlling a fuel supply to a combustor of a gas turbine engine
EP1482150A2 (en) 2003-05-30 2004-12-01 United Technologies Corporation Method and system of synthesizing turbine inlet temperature of a turbo machine
EP1482150A3 (en) * 2003-05-30 2008-05-28 United Technologies Corporation Method and system of synthesizing turbine inlet temperature of a turbo machine
CN100365256C (en) * 2005-12-26 2008-01-30 王菲 Pulsating flow gas turbine
EP2357339A1 (en) * 2010-02-12 2011-08-17 Siemens Aktiengesellschaft Method of determining a combustor exit temperature and method of controlling a gas turbine
WO2011098193A1 (en) * 2010-02-12 2011-08-18 Siemens Aktiengesellschaft Method of determining a combustor exit temperature and method of controlling a gas turbine
US9284890B2 (en) 2010-02-12 2016-03-15 Siemens Aktiengesellschaft Method of determining a combustor exit temperature and method of controlling a gas turbine
CN113378328A (en) * 2021-07-05 2021-09-10 中国航发湖南动力机械研究所 Gas turbine front temperature calculation method for control system
CN113378328B (en) * 2021-07-05 2022-04-22 中国航发湖南动力机械研究所 Gas turbine front temperature calculation method for control system

Also Published As

Publication number Publication date
IT1100560B (en) 1985-09-28
GB2011091B (en) 1982-04-28
FR2412891A1 (en) 1979-07-20
JPS5490409A (en) 1979-07-18
IT7829989A0 (en) 1978-11-21
DE2850625A1 (en) 1979-06-28
FR2412891B1 (en) 1984-06-22

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee