GB2011091A - Method and apparatus for calculating turbine inlet temperature - Google Patents
Method and apparatus for calculating turbine inlet temperatureInfo
- 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
Links
- 239000000446 fuel Substances 0.000 abstract 3
- 239000007789 gas Substances 0.000 abstract 2
- 238000012804 iterative process Methods 0.000 abstract 1
- 230000003068 static effect Effects 0.000 abstract 1
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>
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)
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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2007045528A1 (en) | 2005-10-18 | 2007-04-26 | Alstom Technology Ltd | Method for protecting the hot gas carrying 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)
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 |
-
1978
- 1978-10-23 GB GB7841650A patent/GB2011091B/en not_active Expired
- 1978-11-21 FR FR7832714A patent/FR2412891A1/en active Granted
- 1978-11-21 IT IT29989/78A patent/IT1100560B/en active
- 1978-11-22 DE DE19782850625 patent/DE2850625A1/en not_active Withdrawn
- 1978-11-22 JP JP14348478A patent/JPS5490409A/en active Pending
Cited By (20)
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 |
---|---|
JPS5490409A (en) | 1979-07-18 |
IT1100560B (en) | 1985-09-28 |
FR2412891A1 (en) | 1979-07-20 |
FR2412891B1 (en) | 1984-06-22 |
IT7829989A0 (en) | 1978-11-21 |
GB2011091B (en) | 1982-04-28 |
DE2850625A1 (en) | 1979-06-28 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PCNP | Patent ceased through non-payment of renewal fee |