IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0539271
(2003-12-10)
|
등록번호 |
US-7634914
(2010-01-08)
|
우선권정보 |
IT-MI2002A2660(2002-12-17) |
국제출원번호 |
PCT/EP03/014174
(2003-12-10)
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§371/§102 date |
20060424
(20060424)
|
국제공개번호 |
WO04/055340
(2004-07-01)
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발명자
/ 주소 |
- Casoni, Andrea
- Groppi, Stefano
- Russo, Alessandro
|
출원인 / 주소 |
- Nuovo Pignone Holding S.p.A.
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대리인 / 주소 |
Potomac Patent Group PLLC
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
2 |
초록
▼
A control method for a gas turbine engine is described. The control method includes, for example, corrected control parameters which are adjusted for environmental and/or operating parameters. Control of a fuel valve and a bleed valve in the gas turbine are described relative to various control algo
A control method for a gas turbine engine is described. The control method includes, for example, corrected control parameters which are adjusted for environmental and/or operating parameters. Control of a fuel valve and a bleed valve in the gas turbine are described relative to various control algorithms.
대표청구항
▼
The invention claimed is: 1. A control method for a gas turbine comprising: controlling opening of at least one fuel valve to maintain a temperature (Tfire) of gas at an inlet of the gas turbine and a fuel-air ratio (F/A) within predetermined limits by: calculating a set point exhaust temperature (
The invention claimed is: 1. A control method for a gas turbine comprising: controlling opening of at least one fuel valve to maintain a temperature (Tfire) of gas at an inlet of the gas turbine and a fuel-air ratio (F/A) within predetermined limits by: calculating a set point exhaust temperature (TX) as a sum of a reference temperature (TXbase) and a plurality of correction values each of which are associated with a different operating parameter; wherein corrections values are calculated by computer simulations of the gas turbine, the simulations being conducted by specifying attainment of one of: a maximum of the set point exhaust temperature (TXmaxTfire) and a maximum of the fuel-air ratio (F/A), for each condition differing from a reference condition; further wherein said plurality of correction values includes four corrections values and wherein said step of calculating further comprises calculating: TX=TXbase+DeltaTX_Dpin+DeltaTX_Dpout+DeltaTX_Hum+DeltaTX_PCNLP where: TX is said set point exhaust temperature: DeltaTX_Dpin is a correction value for the set point exhaust temperature (TX) associated with a variation of pressure drops in intake pipes with respect to a nominal value of 0 mmH2O, DeltaTX_Dpout is a correction value for the set point exhaust temperature (TX) associated with a variation of pressure drops in exhaust pipes with respect to a nominal value of 0 mmH2O, DeltaTX_Hum is a correction value for the set point exhaust temperature (TX) associated with a variation of a relative humidity of air with respect to a nominal value of 60%, and DeltaTX_PCNLP is a correction value for the set point exhaust temperature (TX) associated with a variation of a speed of a low pressure shaft with respect to a nominal value of 100%. 2. The control method of claim 1, wherein a maximum exhaust temperature curve is generated for each of a plurality of speeds associated with said gas turbine. 3. The control method of claim 2, wherein said reference temperature (TXbase) is a reference temperature associated with one of said plurality of speeds associated with said gas turbine (Txbase(PCNLP)). 4. The control method of claim 3, wherein there are two values of TXbase(PCNLP), a first value related to a curve of maximum temperature (Tfire) and a second value related to a curve of maximum increase of temperature (Trise) of a gas in a combustion chamber of the gas turbine. 5. The control method of claim 4, further comprising calculating said first value as: TXmaxTfire=TxbasemaxTfire(PCNLP,PR)+DeltaTX_DPin +DeltaTX_Dpout+DeltaTX_Hum, and calculating said second value as: TXmaxTrise=TxbasemaxTrise(PCNLP,PR) +DeltaTX_DPin+DeltaTX_Dpout+DeltaTX_Hum, where: TXmaxTfire is said maximum of the set point exhaust temperature; TxbasemaxTfire is a temperature curve associated with said maximum of the set point exhaust temperature; TxbasemaxTrise is a temperature curve associated with a maximum permissible rise in temperature; PR indicates values having a dependence on a compression ratio (PR). 6. The control method of claim 5, further comprising the step of: providing said temperature curves TXbasemaxTfire and TXbasemaxTrise as two-dimensional tables, with the compression ratio (PR) and the gas turbine speed (PCNLP) as independent variables. 7. The control method of claim 5, wherein said maximum temperature (TXmaxTfire), as a function of the compression ratio PR which enables said maximum (TXmaxTfire) to be attained, is a set of curves, each curve associated with a specific value of speed PCNLP, each successive curve generally having an increasingly negative slope as speed increases, and decreasing with a rise in compression ratio PR. 8. The control method of claim 5, wherein said maximum temperature (TXmaxTrise), as a function of the compression ratio PR which enables the maximum (TXmaxTrise) to be attained, is a set of curves, each curve associated with a specific value of speed PCNLP, each successive curve generally having an increasingly negative slope as speed increases, and decreasing with a rise in the compression ratio PR. 9. The control method of claim 1, wherein the correction value DeltaTX_Hum depends on a specific humidity (SH) and is expressed as a function of a difference (DeltaSH), which difference (DeltaSH) is defined as a difference between a current specific humidity (SH current) and a specific humidity (SH_60%RH) at a relative humidity RH of 60%. 10. The control method of claim 9, wherein there is a linear correlation between the correction value DeltaTX_Hum and the difference (DeltaSH). 11. The control method of claim 10, further comprising the step of: determining the specific humidity (SH 60%RH) at a relative humidity of RH 60% as a function of atmospheric temperature by interpolating the following values, where the temperature is expressed in degrees Rankine: SH_60% RH (T = 419.67) = 0.000070 SH_60% RH (T = 428.67) = 0.000116 SH_60% RH (T = 437.67) = 0.000188 SH_60% RH (T = 446.67) = 0.000299 SH_60% RH (T = 455.67) = 0.000464 SH_60% RH (T = 464.67) = 0.000707 SH_60% RH (T = 473.67) = 0.001059 SH_60% RH (T = 482.67) = 0.001560 SH_60% RH (T = 491.67) = 0.002263 SH_60% RH (T = 500.67) = 0.003324 SH_60% RH (T = 509.67) = 0.004657 SH_60% RH (T = 518.67) = 0.006367 SH_60% RH (T = 527.67) = 0.008670 SH_60% RH (T = 536.67) = 0.011790 SH_60% RH (T = 545.67) = 0.015966 SH_60% RH (T = 554.67) = 0.021456 SH_60% RH (T = 563.67) = 0.028552 SH_60% RH (T = 572.67) = 0.037585 SH_60% RH (T = 581.67) = 0.048949. 12. The control method of claim 1, wherein the correction value DeltaTX_Dpout is expressed directly as a function of a measured pressure drop (DPout). 13. The control method of claim 12, wherein there is a linear correlation between the correction value DeltaTX_Dpout and the measured pressure drop (Dpout). 14. A control method for a gas turbine comprising: controlling opening of a vent valve to maintain a temperature rise (Trise) of gas in a combustion chamber of the gas turbine within predetermined limits using values of an exhaust temperature (TX) as a function of a compression ratio (PR), which values have been obtained for a plurality of operating conditions of the gas turbine; and calculating the exhaust temperature (TX) as a linear approximation of a sum of a reference temperature (Txbase) plus correction values associated with an environmental or operating parameter. wherein there are four of the correction values such that the exhaust temperature (TX) is expressed as: TX=TXbase+DeltaTX_DPin+DeltaTX_Dpout+DeltaTX_Hum+DeltaTX_PCNLP where: TXbase is determined as: TXbase=TTX/((518.67/TCD)x), where: 518.67 is a reference temperature; TCD is an exhaust temperature of a compressor, expressed in a unit of measurement compatible with that of the reference temperature; x is a nondimensional exponent calculated to minimize a mean quadratic deviation between values of TTX and the single control function; and TTX is a transformed exhaust temperature; DeltaTX_Dpin is a correction value for the exhaust temperature (TX) associated with a variation of pressure drops in intake pipes with respect to a nominal value of 0 mm H2O; DeltaTX_Dpout is a correction value for the exhaust temperature (TX) associated with a variation of pressure drops in exhaust pipes with respect to a nominal value of 0 mm H2O; DeltaTX_Hum is a correction value for the exhaust temperature (TX) associated with a variation of relative humidity of air with respect to a nominal value of 60%; and DeltaTX_PCNLP is a correction value for the exhaust temperature (TX) due to a variation of a low pressure shaft speed with respect to a nominal value of 100%. 15. The control method of claim 14, wherein said values are associated with a control function that is defined for each of a plurality of values of atmospheric temperature. 16. The control method of claim 15, wherein said control functions represent a relationship between the exhaust temperature (TX) for partial loads at a given speed of a low pressure shaft of the gas turbine and the compression ratio (PR), wherein each control function is associated with a value of atmospheric temperature, each control function generally having higher values as temperature rises and decreasing as the compression ratio (PR) decreases. 17. The control method of claim 14, wherein said values are associated with a single control function without a dependence on atmospheric temperature. 18. The control method of claim 17, further comprising: determining a set point associated with said controlling step based on inverse of the transformation for a known compression ratio (PR). 19. The control method of claim 14, wherein a set of functions, one for each value of speed (PCNLP), is expressed in terms of the maximum temperature (TX) as a function of the compression ratio (PR). 20. The control method of claim 19, further comprising: evaluating said exhaust temperature (TX) by calculating: TX=TXbase(PCNLP)+DeltaTX_DPin+DeltaTX_Dpout+DeltaTX_RH where: TXbase(PCNLP) is a reference temperature associated with a speed of the gas turbine; and DeltaTX_RH is a change in exhaust temperature associated with relative humidity. 21. The control method of one of claims 18 or 20, wherein the exponent X is a function of a speed of a low pressure wheel of the gas turbine. 22. The control method of claim 21, wherein the exponent X, for intermediate speeds (PCNLP), is calculated by interpolation of values of X which have been calculated at other speeds (PCNLP) as follows: if PCNLP=105%, X=0.323; if PCNLP=100%, X=0.33225; if PCNLP=90%, X=0.34; if PCNLP=80%, X=0.34425; if PCNLP=70%, X=0.351; if PCNLP=60%, X=0.348; or if PCNLP=50%, X=0.3505. 23. The control method of claim 20, wherein the correction value DeltaTX_RH is calculated based on three ambient temperatures, three levels of relative humidity, and load characteristics according to a cubic law. 24. The control method of claim 23, wherein nine simulations are conducted, each associated with different fuel-air ratio F/A values, to determine a reference level, current values of TX are then plotted as functions of PR, while a difference between the functions and base curves yields the correction value DeltaTX_RH, as expressed in the formula: DeltaTX_RH =TX-TXbase. 25. The control method of claim 24, wherein said values of the correction value DeltaTX_RH are plotted as a function of a difference (DeltaSH) between a current value of specific humidity (SH_current) and a specific humidity at a relative humidity of 60% (SH_60%RH) such that: DeltaSH=SH_current-SH_60% RH. 26. The control method of claim 25, wherein the function comprises two straight lines rising with an increase in the difference (DeltaSH), of which a first one of said straight lines is valid when DeltaSH is less than 0 and has a greater slope than a second one of said straight lines which is valid when DeltaSH is greater than 0, the two straight lines passing through a point near an origin of the function's axes. 27. The control method of claim 14, wherein the correction value DeltaTX_Dpin is a function of a measured pressure drop (DPin). 28. The control method of claim 27, further comprising the step of: determining said correction value DeltaTX_Dpin taking into account three ambient temperatures, three pressure drops in an intake and load characteristics according to a cubic law. 29. The control method of claim 28, wherein nine simulations are conducted, each associated with different fuel-air ratio F/A values, to reach a reference level, current values of TX are then plotted as functions of PR, while a difference between the functions and base curves yields the correction value DeltaTX_Dpin, as expressed in the formula: DeltaTX_Dpin=TX-TXbase. 30. The control method of claim 29, wherein said correction values (DeltaTX_Dpin) are linearly correlated with the measured pressure drop Dpin such that the correction values of DeltaTX_Dpin increase with a rise in the measured pressure drop Dpin. 31. The control method of claim 14, wherein the correction value (DeltaTX_Dpout) is a function of the measured pressure drop DPout. 32. The control method of claim 31, further comprising: determining said correction value DeltaTX_Dpout taking into account three ambient temperatures, three pressure drops in the exhaust and load characteristics according to a cubic law. 33. The control method of claim 32, wherein nine simulations are conducted, each associated with different fuel-air ratio F/A values, to reach a reference level, the current values of TX are then plotted as functions of PR, while a difference between the functions and base curves yields the correction value DeltaTX_Dpout, as expressed in the formula: DeltaTX_Dpout=TX-TXbase. 34. The control method of claim 33, wherein the correction values DeltaTX_Dpout are linearly correlated with the exhaust pressure Dpout, such that the correction values DeltaTX_Dpout increase with a rise in the exhaust pressure Dpout. 35. The control method of claims 26, 30 or 34, wherein a correlation for calculating the maximum exhaust temperature TX is: TX=TTX(PCNLP, PR)/((518.67/TCD)x(PCNLP)+DeltaTX_RH (DeltaSH)+DeltaTX_Dpin (Dpin)+DeltaTX_Dpout (Dpout). 36. The control method of claim 1 or 14, wherein said control method is used to control a two-shaft gas turbine and further comprising the step of: providing said two-shaft gas turbine with a dry nitrogen oxide (NOx) reduction system. 37. A control method for a gas turbine comprising: controlling opening of at least one fuel valve to maintain a temperature (Tfire) of gas at an inlet of the gas turbine and a fuel-air ratio (F/A) within predetermined limits by: calculating a set point exhaust temperature (TX) as a sum of a reference temperature (TXbase) and a plurality of correction values each of which are associated with a different operating parameter; wherein said plurality of correction values includes four corrections values and wherein said step of calculating further comprises calculating: TX=TXbase+DeltaTX_Dpin+DeltaTX_Dpout+DeltaTX_Hum+DeltaTX_PCNLP where: TX is said set point exhaust temperature: DeltaTX_Dpin is a correction value for the set point exhaust temperature (TX) associated with a variation of pressure drops in intake pipes with respect to a nominal value of 0 mmH2O, DeltaTX_Dpout is a correction value for the set point exhaust temperature (TX) associated with a variation of pressure drops in exhaust pipes with respect to a nominal value of 0mmH2O, DeltaTX_Hum is a correction value for the set point exhaust temperature (TX) associated with a variation of a relative humidity of air with respect to a nominal value of 60%, and DeltaTX_PCNLP is a correction value for the set point exhaust temperature (TX) associated with a variation of a speed of a low pressure shaft with respect to a nominal value of 100%; and controlling opening of a vent valve to maintain a temperature rise (Trise) of gas in a combustion chamber of the gas turbine within predetermined limits using values of an exhaust temperature (TX) as a function of a compression ratio (PR), which values have been obtained for a plurality of operating conditions of the gas turbine.
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