IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0458539
(2009-07-15)
|
등록번호 |
US-8740548
(2014-06-03)
|
우선권정보 |
GB-0813413.2 (2008-07-23) |
발명자
/ 주소 |
- Rowe, Arthur L.
- Pons Perez, Marc
- Davies, Cerith
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
11 |
초록
▼
A compressor variable stator vane arrangement comprises at least one stage of variable stator vanes. A speed sensor measures the rotational speed of the compressor rotor. A pressure sensor measures the outlet pressure of the compressor. A second pressure sensor, a temperature sensor and a third pres
A compressor variable stator vane arrangement comprises at least one stage of variable stator vanes. A speed sensor measures the rotational speed of the compressor rotor. A pressure sensor measures the outlet pressure of the compressor. A second pressure sensor, a temperature sensor and a third pressure sensor measure the total inlet pressure, the temperature and the ambient pressure at the inlet of the gas turbine engine. A processor determines a target operating line as a function of ambient pressure and total inlet pressure. The target operating line is defined to ensure the gas turbine engine operates simultaneously at both the minimum required compressor speed and the minimum required compressor outlet pressure when commanded to idle to minimize idle thrust and fuel burn. The processor determines if the operating point of the compressor, defined in terms of corrected outlet pressure and corrected rotational speed of the compressor rotor is above or below the target operating line of the compressor. The processor adjusts the angle of the variable stator vanes to make the operating point operate on the target operating line.
대표청구항
▼
1. A gas turbine engine compressor variable stator vane arrangement comprising: a gas turbine engine including: a gas turbine engine compressor;a compressor rotor,a compressor casing, andat least one stage of variable stator vanes, the at least one stage of variable stator vanes being pivotally moun
1. A gas turbine engine compressor variable stator vane arrangement comprising: a gas turbine engine including: a gas turbine engine compressor;a compressor rotor,a compressor casing, andat least one stage of variable stator vanes, the at least one stage of variable stator vanes being pivotally mounted in the compressor casing,an actuating arrangement arranged to rotate stator vanes of the at least one stage of variable stator vanes,a control arrangement comprising a first speed sensor arranged to measure a rotational speed of the compressor rotor, a temperature sensor to measure an inlet temperature of the gas turbine engine, a first pressure sensor to measure an outlet pressure of the gas turbine engine compressor, a second pressure sensor to measure an ambient pressure at an inlet of the gas turbine engine, a third pressure sensor to measure a total inlet pressure of the gas turbine engine,a processor configured to determine a current operating point of the gas turbine engine compressor from a measured rotational speed of the compressor rotor and a measured outlet pressure of the gas turbine engine compressor, anda comparator to compare the current operating point of the gas turbine engine compressor with a target operating line of the gas turbine engine compressor, andthe processor further configured to adjust an angle of the at least one stage of variable stator vanes if the comparator determines that the current operating point of the gas turbine engine compressor is not on the target operating line of the gas turbine engine compressor, such that the current operating point of the gas turbine engine compressor is moved nearer towards or onto the target operating line of the gas turbine engine compressor,wherein, at idle conditions, the gas turbine engine compressor is simultaneously operating at the minimum required outlet pressure of the gas turbine engine compressor and at the minimum required rotational speed of the compressor rotor,wherein the target operating line corresponds to a ratio between the rotational speed and the outlet pressure of the gas turbine engine compressor, the target operating line including a point comprising the minimum required rotational speed and a minimum required outlet pressure. 2. A compressor variable stator vane arrangement as claimed in claim 1 further comprising a second temperature sensor arranged at the inlet of the gas turbine engine compressor. 3. A compressor variable stator vane arrangement as claimed in claim 1 wherein a second speed sensor is arranged to measure the rotational speed of a fan rotor and the processor is configured to determine the inlet temperature of the gas turbine engine compressor, the processor comprises a calculator to determine the inlet temperature of the gas turbine engine compressor by multiplying the inlet temperature of the gas turbine engine by a function of a corrected non-dimensional speed of rotation of the fan rotor. 4. A compressor variable stator vane arrangement as claimed in claim 3 wherein the calculator determines the corrected non-dimensional speed of the fan rotor by dividing the rotational speed of the fan rotor by the square root of (the temperature at the inlet of the gas turbine engine divided by sea level ISA temperature). 5. A compressor variable stator vane arrangement as claimed in claim 1 wherein the calculator is arranged to determine a corrected outlet pressure of the gas turbine engine compressor by dividing the outlet pressure by (the pressure at the inlet of the gas turbine engine divided by sea level ISA pressure). 6. A compressor variable stator vane arrangement as claimed in claim 5 wherein the calculator is arranged to determine a corrected non-dimensional speed of the compressor rotor by dividing the speed of the compressor rotor by (the square root of the inlet temperature of the gas turbine engine divided by sea level ISA temperature). 7. A compressor variable stator vane arrangement as claimed in claim 1 wherein the comparator is arranged to adjust the angle of the at least one stage of variable stator vanes in order to increase a corrected outlet pressure of the gas turbine engine compressor at a rotational speed of the compressor rotor or the comparator is arranged to adjust the at least one stage of variable stator vanes in order to decrease the corrected outlet pressure of the gas turbine engine compressor at a rotational speed of the compressor rotor. 8. A compressor variable stator vane arrangement as claimed in claim 1 wherein the at least one stage of variable stator vanes comprises a plurality of circumferentially arranged and radially extending variable stator vanes. 9. A compressor variable stator vane arrangement as claimed in claim 1 wherein the at least one stage of variable stator vanes comprises a plurality of stages of variable stator vanes. 10. A compressor variable stator vane arrangement as claimed in claim 1 wherein the gas turbine engine compressor is selected from a group comprising an intermediate pressure compressor, a booster compressor and a high pressure compressor. 11. A compressor variable stator vane arrangement as claimed in claim 1 wherein the processor is further configured to determine the target operating line and arrange the target operating line to pass through a point where a line of minimum required outlet pressure of the gas turbine engine compressor and a line of minimum required rotational speed of the compressor rotor intersect. 12. A compressor variable stator vane arrangement as claimed in claim 1 wherein the compressor rotor is arranged to drive an electrical generator, andthe compressor is arranged to pressurise an air system,wherein the minimum required rotational speed of the compressor rotor is a minimum electrical generator speed, and the minimum outlet pressure is an outlet pressure required to maintain adequate air system pressure ratios. 13. A method of operating a gas turbine engine compressor variable stator vane arrangement, the gas turbine engine compressor variable stator vane arrangement comprising a gas turbine engine including 1) a gas turbine engine compressor, 2) a compressor rotor, 3) a compressor casing, and 4) at least one stage of variable stator vanes, the at least one stage of variable stator vanes being pivotally mounted in the compressor casing, and an actuating arrangement arranged to rotate stator vanes of the at least one stage of variable stator vanes, the method comprising: measuring a rotational speed of the compressor rotor,measuring an inlet temperature of the gas turbine engine,measuring an outlet pressure of the gas turbine engine compressor,measuring an ambient pressure at an inlet of the gas turbine engine,measuring a total inlet pressure of the gas turbine engine,determining a current operating point of the gas turbine engine compressor from the rotational speed of the gas turbine engine compressor and the outlet pressure of the gas turbine engine compressor,comparing the current operating point of the gas turbine engine compressor with a target operating line of the gas turbine engine compressor, andadjusting an angle of the at least one stage of variable stator vanes if it is determined that the current operating point of the gas turbine engine compressor is not on the target operating line of the gas turbine engine compressor such that the current operating point of the gas turbine engine compressor is moved nearer towards or onto the target operating line of the gas turbine engine compressor;wherein, at idle conditions, the gas turbine engine compressor is simultaneously operating at the minimum required outlet pressure of the gas turbine engine compressor and at the minimum required rotational speed of the compressor rotor,wherein the target operating line corresponds to a ratio between the rotational speed and the outlet pressure of the gas turbine engine compressor, the target operating line including a point comprising the minimum required rotational speed and a minimum required outlet pressure. 14. A method as claimed in claim 13 comprising: measuring the temperature at the inlet of the gas turbine engine,measuring a rotational speed of a fan rotor, andmultiplying the temperature at the inlet of the gas turbine engine by a function of a corrected non-dimensional speed of rotation of the fan rotor to determine the inlet temperature of the gas turbine engine compressor. 15. A method as claimed in claim 14 comprising determining the corrected non-dimensional speed of rotation of the fan rotor by dividing the rotational speed of the fan rotor by the square root of (the temperature at the inlet of the gas turbine engine divided by sea level ISA temperature). 16. A method as claimed in claim 13 comprising: determining a corrected outlet pressure of the gas turbine engine compressor by dividing the outlet pressure by (the pressure at the inlet of the gas turbine engine divided by sea level ISA pressure). 17. A method as claimed in claim 16 comprising determining a corrected non-dimensional speed of the compressor rotor by dividing the rotational speed of the compressor rotor by (the square root of the inlet temperature of the gas turbine engine divided by sea level ISA temperature). 18. A method as claimed in claim 17 comprising selecting the angle of the stator vanes of the at least one stage of variable stator vanes as a function of the rotational speed of the gas turbine engine compressor rotor divided by (the square root of the inlet temperature of the gas turbine engine divided by sea level ISA temperature). 19. A method as claimed in claim 13 comprising adjusting the angle of the at least one stage of variable stator vanes in order to increase a corrected outlet pressure of the gas turbine engine compressor at a rotational speed of the compressor rotor or adjusting the at least one stage of variable stator vanes in order to decrease the corrected outlet pressure of the gas turbine engine compressor at a rotational speed of the compressor rotor. 20. A method as claimed in claim 13 wherein the at least one stage of variable stator vanes comprises a plurality of circumferentially arranged and radially extending variable stator vanes. 21. A method as claimed in claim 20 wherein the at least one stage of variable stator vanes comprises a plurality of stages of variable stator vanes. 22. A method as claimed in claim 13 comprising arranging the target operating line to pass through a point where a line of minimum required outlet pressure of the gas turbine engine compressor and a line of minimum required rotational speed of the compressor rotor intersect. 23. A method as claimed in claim 13 comprising: arranging the compressor rotor to drive an electrical generator, andarranging the gas turbine engine compressor to pressurise an air system,wherein the minimum required rotational speed of the compressor rotor is a minimum electrical generator speed, and the minimum outlet pressure is an outlet pressure required to maintain adequate air system pressure ratios. 24. A gas turbine engine compressor variable stator vane arrangement comprising: a gas turbine engine including: a gas turbine engine compressor,a compressor rotor,a compressor casing, andat least one stage of variable stator vanes, the at least one stage of variable stator vanes being pivotally mounted in the compressor casing,an actuating arrangement arranged to rotate stator vanes of the at least one stage of variable stator vanes,a control arrangement comprising a speed sensor arranged to measure a rotational speed of the compressor rotor,a pressure sensor to measure an outlet pressure of the gas turbine engine compressor,a processor configured to determine a current operating point of the gas turbine engine compressor from a measured rotational speed of the compressor rotor and the outlet pressure of the gas turbine engine compressor,the processor is arranged to select a point of intersection of the minimum required outlet pressure of the gas turbine engine compressor and the minimum required rotational speed of the compressor rotor as a point on a target operating line of the gas turbine engine compressor,a comparator is arranged to compare the current operating point of the gas turbine engine compressor with the target operating line of the gas turbine engine compressor,the processor is arranged to adjust an angle of the at least one stage of variable stator vanes if the comparator determines that the current operating point of the gas turbine engine compressor is not on the target operating line of the gas turbine engine compressor such that the current operating point of the gas turbine engine compressor is moved nearer towards or onto the target operating line of the gas turbine engine compressor, andsuch that at idle conditions the gas turbine engine compressor is simultaneously operating at the minimum required outlet pressure of the gas turbine engine compressor and at the minimum required rotational speed of the compressor rotor,wherein the target operating line corresponds to a ratio between the rotational speed and the outlet pressure of the gas turbine engine compressor, the target operating line including a point comprising the minimum required rotational speed and a minimum required outlet pressure. 25. A method of operating a gas turbine engine compressor variable stator vane arrangement, the gas turbine engine compressor variable stator vane arrangement comprising a gas turbine engine including 1) a gas turbine engine compressor, 2) a compressor rotor, 3) a compressor casing, and 4) at least one stage of variable stator vanes, the at least one stage of variable stator vanes being pivotally mounted in the compressor casing, and an actuating arrangement arranged to rotate stator vanes of the at least one stage of variable stator vanes, the method comprising: measuring a rotational speed of the compressor rotor,measuring an outlet pressure of the gas turbine engine compressor,determining a current operating point of the gas turbine engine compressor from the rotational speed of the compressor rotor and the outlet pressure of the gas turbine engine compressor,selecting a point of intersection of the minimum required outlet pressure of the gas turbine engine compressor and the minimum required rotational speed of the compressor rotor as a point on a target operating line of the gas turbine engine compressor,comparing the current operating point of the gas turbine engine compressor with the target operating line of the gas turbine engine compressor,adjusting an angle of the at least one stage of variable stator vanes if the comparator determines that the current operating point of the gas turbine engine compressor is not on the target operating line of the gas turbine engine compressor such that the current operating point of the gas turbine engine compressor is moved nearer towards or onto the target operating line of the gas turbine engine compressor, andsuch that at idle conditions the gas turbine engine compressor is simultaneously operating at the minimum required outlet pressure of the compressor and at the minimum required rotational speed of the compressor rotor,wherein the target operating line corresponds to a ratio between the rotational speed and the outlet pressure of the gas turbine engine compressor, the target operating line including a point comprising the minimum required rotational speed and a minimum required outlet pressure. 26. A gas turbine engine compressor variable stator vane arrangement comprising: a gas turbine engine compressor including: a compressor rotor,a compressor casing, andat least one stage of variable stator vanes, the at least one stage of variable stator vanes being pivotally mounted in the compressor casing,the compressor rotor is arranged to drive an electrical generator,the gas turbine engine compressor is arranged to pressurise an air system,an actuating arrangement arranged to rotate stator vanes of the at least one stage of variable stator vanes,a control arrangement comprising a speed sensor arranged to measure a rotational speed of the compressor rotor,a pressure sensor to measure an outlet pressure of the compressor,a processor arranged to determine a current operating point of the gas turbine engine compressor from the rotational speed of the compressor rotor and the outlet pressure of the gas turbine engine compressor,the processor is arranged to determine a minimum required rotational speed of the compressor rotor and a minimum required outlet pressure of the gas turbine engine compressor,wherein the minimum required rotational speed of the compressor rotor is a minimum electrical generator speed and the minimum outlet pressure is an outlet pressure required to maintain adequate air system pressure ratios,the processor is arranged to select a point of intersection of the minimum required outlet pressure of the gas turbine engine compressor and the minimum required rotational speed of the compressor rotor as a point on a target operating line of the gas turbine engine compressor,a comparator is arranged to compare the current operating point of the gas turbine engine compressor with the target operating line of the gas turbine engine compressor,the processor is arranged to adjust an angle of the variable stator vanes if the comparator determines that the current operating point of the compressor is not on the target operating line of the gas turbine engine compressor such that the current operating point of the gas turbine engine compressor is moved nearer towards or onto the target operating line of the gas turbine engine compressor andsuch that at idle conditions the gas turbine engine compressor is simultaneously operating at the minimum required outlet pressure of the compressor and at the minimum required rotational speed of the compressor rotor,wherein the target operating line corresponds to a ratio between the rotational speed and the outlet pressure of the gas turbine engine compressor, the target operating line including a point comprising the minimum required rotational speed and a minimum required outlet pressure. 27. A method of operating a gas turbine engine compressor variable stator vane arrangement, the compressor comprising a gas turbine engine compressor including 1) a compressor rotor, 2) a compressor casing, and 3) at least one stage of variable stator vanes, the at least one stage of variable stator vanes being pivotally mounted in the compressor casing, the compressor rotor is arranged to drive an electrical generator, the gas turbine engine compressor is arranged to pressurise an air system, and an actuating arrangement arranged to rotate stator vanes of the at least one stage of variable stator vanes, the method comprising: measuring a rotational speed of the compressor rotor,measuring an outlet pressure of the gas turbine engine compressor,determining a current operating point of the gas turbine engine compressor from the rotational speed of the gas turbine engine compressor and the outlet pressure of the gas turbine engine compressor,determining a minimum required rotational speed of the compressor rotor and a minimum required outlet pressure of the gas turbine engine compressor,wherein the minimum required rotational speed of the compressor rotor is a minimum electrical generator speed and the minimum outlet pressure is an outlet pressure required to maintain adequate air system pressure ratios,selecting a point of intersection of the minimum required outlet pressure of the gas turbine engine compressor and the minimum required rotational speed of the compressor rotor as a point on a target operating line of the gas turbine engine compressor,comparing the current operating point of the gas turbine engine compressor with the target operating line of the gas turbine engine compressor,adjusting an angle of the at least one stage of variable stator vanes if the comparator determines that the current operating point of the gas turbine engine compressor is not on the target operating line of the gas turbine engine compressor such that the current operating point of the gas turbine engine compressor is moved nearer towards or onto the target operating line of the gas turbine engine compressor, andsuch that at idle conditions the gas turbine engine compressor is simultaneously operating at the minimum required outlet pressure of the gas turbine engine compressor and at the minimum required rotational speed of the compressor rotor,wherein the target operating line corresponds to a ratio between the rotational speed and the outlet pressure of the gas turbine engine compressor, the target operating line including a point comprising the minimum required rotational speed and a minimum required outlet pressure.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.