Control system and method for controlling a gas turbine engine during transients
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-009/54
F02D-041/30
F02C-009/28
출원번호
US-0140606
(2013-12-26)
등록번호
US-9850823
(2017-12-26)
발명자
/ 주소
Miduturi, Krishna C.
Kozachuk, Danny W.
출원인 / 주소
SIEMENS AKTIENGESELLSCHAFT
인용정보
피인용 횟수 :
0인용 특허 :
28
초록▼
A control system and method for a gas turbine engine are provided A controller (40) is responsive to at least one parameter to control an air-to-fuel ratio. The parameter may be a measured engine exhaust temperature from a temperature sensor (42). During a transient, such as a ramping condition of t
A control system and method for a gas turbine engine are provided A controller (40) is responsive to at least one parameter to control an air-to-fuel ratio. The parameter may be a measured engine exhaust temperature from a temperature sensor (42). During a transient, such as a ramping condition of the engine, a measured value of such parameter may have a time lag affecting one or more control settings during the transient condition. The controller is programmed to predictively determine a bias for the measured value of the parameter to correct such control settings and avoid combustion instabilities and high emissions during such transient conditions.
대표청구항▼
1. A control system for a gas turbine engine comprising: a controller responsive to at least one parameter to control an air-to-fuel ratio, wherein during a transient condition of the engine, a measured value of said at least one parameter comprises a time lag affecting at least one control setting
1. A control system for a gas turbine engine comprising: a controller responsive to at least one parameter to control an air-to-fuel ratio, wherein during a transient condition of the engine, a measured value of said at least one parameter comprises a time lag affecting at least one control setting during the transient condition of the engine, wherein the controller is programmed to predictively determine a bias to correct said at least one control setting;wherein a determination of the bias is based at least in part on a ramp rate of the engine during the transient condition;wherein said controller provides control that in part is based on engine exhaust temperature measurements and said at least one parameter comprises a measured engine exhaust temperature;wherein a determination of the bias is based on the time lag determined by the difference between the idealized engine exhaust temperature response and the measured engine exhaust temperature; andfurther comprising inlet guide vanes to control inlet air flow to a compressor, wherein said at least one control setting comprises a control setting to position said inlet guide vanes during the transient condition of the engine. 2. The control system of claim 1, wherein the time lag is based on comparing the measured engine exhaust temperature to an idealized engine exhaust temperature response. 3. The control system of claim 1, wherein the bias is applied to a steady-state exhaust temperature value at a present engine condition. 4. The control system of claim 1, wherein a determination of the bias is based on the following equation: Texhbias,1=a×(MWrate×Δtlag×(TexhSS,1−TexhSS,2))+b where, Texhbias,l=bias to a steady-state exhaust temperature (Texh) value at a present engine condition,TexhSS,1=the steady-state Texh value at the present engine condition,TexhSS,2=a steady-state Texh value at a target engine condition,MWrate=ramp rate of the engine,Δtlag=value of the lag time,a =a proportionality factor, andb =a site-specific constant. 5. The control system of claim 1, further comprising a fuel system to control at least one fuel flow to a combustor, wherein said at least one control setting further comprises a demand for said at least one fuel flow. 6. The control system of claim 1, further comprising a bias adjustor configured to adjust the bias as a function of ambient temperature. 7. The control system of claim 1, further comprising a bias adjustor configured to adjust the bias as a function of engine load. 8. The control system of claim 1, further comprising a bias adjustor configured to adjust the bias as a function of ambient temperature and/or engine load. 9. A method for controlling a gas turbine engine, the method comprising: controlling an air-to-fuel ratio with a controller responsive to at least one parameter;measuring a value of said at least one parameter, which during a transient condition of the engine comprises a time lag affecting at least one control setting during the transient condition of the engine; andpredictively determining a bias to correct said at least one control setting; wherein the determining of the bias is based at least in part on a ramp rate of the engine during the transient condition;wherein said controlling comprises controlling that in part is based on engine exhaust temperature measurements and said at least one parameter comprises a measured engine exhaust temperature;wherein the determining of the bias is based on the time lag determined by the difference between the idealized engine exhaust temperature response and the measured engine exhaust temperature; andfurther comprising controlling inlet air flow to a compressor with inlet guide vanes, wherein said at least one control setting comprises a control setting to position said inlet guide vanes during the transient condition of the engine. 10. The method of claim 9, wherein the time lag is based on comparing the measured engine exhaust temperature to an idealized engine exhaust temperature response. 11. The method of claim 9, further comprising applying the bias to a steady-state exhaust temperature value at a present engine condition. 12. The method of claim 9, wherein the determining of the bias is based on the following equation: Texhbias,1=a×(MWrate×Δtlag×(TexhSS,1−TexhSS,2))+b where, Texhbais,1=bias to a steady-state exhaust temperature (Texh) value at a present engine condition,TexhSS,1=the steady-state Texh value at the present engine condition,TexhSS,2=a steady-state Texh value at a target engine condition,MWrate=ramp rate of the engine,Δttag=value of the lag time,a =a proportionality factor, andb =a site-specific constant. 13. The method of claim 9, further comprising controlling at least one fuel flow to a combustor, wherein said at least one control setting further comprises a demand for said at least one fuel flow. 14. The method of claim 9, adjusting the bias as a function of ambient temperature. 15. The method of claim 9, adjusting the bias as a function of engine load.
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