Determination of a signal indicative of shaft power
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-001/00
F02C-009/54
F02C-009/28
출원번호
US-0514766
(2006-09-01)
등록번호
US-9273614
(2016-03-01)
발명자
/ 주소
Martis, Dan
Fletcher, Paul
Rebhi, Betka
Perez, Vincent
Doke, Robert
출원인 / 주소
INDUSTRIAL TURBINE COMPANY (UK) LIMITED
대리인 / 주소
Beusse Wolter Sanks & Maire
인용정보
피인용 횟수 :
0인용 특허 :
12
초록▼
A gas turbine engine provides mechanical shaft power. Two parameters relating to engine operation are sensed that are representative of two different pressures, two different temperatures, or a pressure and a temperature associated with the engine. A value representative of the shaft power is determ
A gas turbine engine provides mechanical shaft power. Two parameters relating to engine operation are sensed that are representative of two different pressures, two different temperatures, or a pressure and a temperature associated with the engine. A value representative of the shaft power is determined during engine operation as a function of these two parameters. This value may be used for engine monitoring including making one or more adjustments to operational aspects of the engine, regulating/controlling engine function, and/or providing one or more power indicators.
대표청구항▼
1. A method, comprising: providing a gas turbine engine structured to rotate a shaft to generate mechanical power;sensing a gas pressure of a working gas within the gas turbine engine during gas turbine engine operation;determining a signal representative of a computed estimate of mechanical power p
1. A method, comprising: providing a gas turbine engine structured to rotate a shaft to generate mechanical power;sensing a gas pressure of a working gas within the gas turbine engine during gas turbine engine operation;determining a signal representative of a computed estimate of mechanical power provided by rotation of the shaft, the computed estimate formulated as a function of the gas pressure and a temperature, the temperature within the computed estimate used to compensate for gas turbine engine variation over time in the function; andcontrolling the gas turbine engine operation in accordance with the signal;wherein the function comprises the relationship (T20/Tref)A*(P30/Pamb), whereinT20 represents a detected inlet temperature of a compressor of the gas turbine engine or an ambient temperature detected proximate the gas turbine engine or within a plenum of the gas turbine engine;Tref represents a reference ambient temperature;“A” represents an experimentally derived value corresponding to the gas turbine engine;P30 represents the gas pressure detected at a discharge of a compressor of the gas turbine engine or at an entry of a combustor of the gas turbine engine; andPamb represents an ambient air pressure detected proximate the gas turbine engine or within a plenum of the gas turbine engine. 2. The method of claim 1, wherein the signal corresponds to a number, and further comprising: detecting a turbine inlet temperature of the gas turbine engine; andincluded in the determining of the signal, calculating the number from the function, the function including a further relationship (T44/T20)B as a factor of the function, whereinT44 represents the detected turbine inlet temperature of the gas turbine engine;“B” represents an experimentally derived value corresponding to the gas turbine engine; andthe further relationship being selected to correct for the gas turbine engine variation over time. 3. The method of claim 2, further comprising: detecting the ambient pressure represented by Pamb; andincluded in the determining of the signal, calculating the number from the function wherein the relationship (P30/Pamb) corresponds to an uncorrected mechanical power. 4. The method of claim 1, wherein the controlling of the gas turbine engine operation includes one or more of: changing a variable geometry of the gas turbine engine in response to the signal;adjusting a fuel control device of the gas turbine engine in response to the signal; andindicating engine power output with an indicator responsive to the signal. 5. A method, comprising: operating a gas turbine engine with a rotatable shaft structured to provide mechanical shaft power;sensing a first gas pressure within the gas turbine engine during an operation of the gas turbine engine;determining a value that approximates the shaft power of the gas turbine engine in accordance with a relationship between the first gas pressure and a second gas pressure; andin response to the value, performing one or more adjustments to alter the operation of the gas turbine engine;wherein the relationship comprises P30/Pamb, whereinP30 represents the first gas pressure and is detected at a discharge of a first compressor of the gas turbine engine or at an entry of a combustor of the gas turbine engine; andPamb represents the second gas pressure and is an ambient air pressure detected proximate the gas turbine engine or within a plenum of the gas turbine engine. 6. The method of claim 5 further comprising: detecting two temperatures represented by T44 and T20; wherein the relationship further comprises (T44/T20)B as a factor, whereinT44 represents a temperature of a working gas detected at a discharge of a first turbine of the gas turbine engine or at an inlet of a second turbine of the gas turbine engine downstream from the first turbine;T20 represents a detected inlet temperature of a second compressor of the gas turbine engine or a detected ambient temperature; and“B” represents an experimentally derived value corresponding to the gas turbine engine. 7. The method of claim 6, wherein the factor (T44/T20)B compensates the value for a variation in a wear condition of the gas turbine engine. 8. The method of claim 6, wherein the gas turbine engine includes two or more compressors, two or more turbines, and a controller; and wherein the method further includes: monitoring of the operation of the gas turbine engine with the controller including one or more of:changing a variable geometry of the gas turbine engine;adjusting a fuel control valve of the gas turbine engine;and providing an engine power indicator. 9. The method of claim 5, wherein the one or more adjustments include one or more of: changing a variable geometry of the gas turbine engine;controlling a fuel control valve of the gas turbine engine;and changing an engine power indicator. 10. A method, comprising: providing a gas turbine engine structured to provide mechanical shaft power;sensing parameters relating to gas turbine engine operation;calculating a signal representative of the shaft power provided by rotation of the shaft during the gas turbine engine operation, the calculating including mathematically interrogating a function of the parameters; and monitoring the gas turbine engine operation with the signal; andcontrolling the gas turbine engine operation in accordance with the signal;wherein the function corresponds to the relationship θA*(P1/P2)*(T1/T2)B;wherein P1 corresponds to a first one of the parameters and represents a discharge pressure of a first compressor, P2 corresponds to a second one of the parameters and represents ambient pressure, T1 corresponds to a third one of the parameters and represents a turbine inlet temperature, T2 corresponds to a fourth one of the parameters and represents an inlet temperature of a second compressor, θ is a temperature compensation factor for temperature T2, and A and B are constants based on design of the gas turbine engine. 11. The method of claim 10, wherein θ is a function of T2 and a constant.
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이 특허에 인용된 특허 (12)
Meisner, Richard, Adaptive acceleration schedules for gas turbine engine control systems.
Philip L. Andrew ; Chung-hei Yeung ; Joseph A. Cotroneo ; John David Stampfli, Method of air-flow measurement and active operating limit line management for compressor surge avoidance.
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