Method, system, and apparatus for reducing a turbine clearance
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-031/06
F01D-011/24
출원번호
US-0077731
(2016-03-22)
등록번호
US-9758252
(2017-09-12)
발명자
/ 주소
Adibhatla, Sridhar
Nolte, Steven Edward
Moeller, Gerhard Walter
Gallagher, Christopher Timothy
Hanify, John William
Ingram, Grant Alan
출원인 / 주소
General Electric Company
대리인 / 주소
General Electric Company
인용정보
피인용 횟수 :
0인용 특허 :
7
초록▼
A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. The method includes determining that an airplane is in a first flight condition, and adjusting the turbine clearance gap to a first clearance gap dist
A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. The method includes determining that an airplane is in a first flight condition, and adjusting the turbine clearance gap to a first clearance gap distance associated with the first flight condition. The method also includes determining a demand for a second flight condition, and adjusting an engine responsiveness to a first engine responsiveness for a first predetermined change in a power parameter of the engine. The method further includes reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine, and closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the engine.
대표청구항▼
1. A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine, said method comprising: determining, with a flight operation controller, that an airplane is in a first flight condition;adjusting the turbine clearance gap to
1. A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine, said method comprising: determining, with a flight operation controller, that an airplane is in a first flight condition;adjusting the turbine clearance gap to a first clearance gap distance associated with the first flight condition;determining, with the flight operation controller, a demand for a second flight condition;adjusting an engine responsiveness to a first engine responsiveness level for a first predetermined change in a power parameter of the turbine engine;wherein the power parameter includes fan speed, and wherein adjusting an engine responsiveness to a first engine responsiveness level for a first predetermined change in a power parameter of the engine comprises adjusting the engine responsiveness to the first engine responsiveness level for a first predetermined change in fan speed over a first predetermined change in power level;reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the turbine engine; andclosing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the turbine engine. 2. The method in accordance with claim 1, reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine comprises reducing the engine responsiveness to the second engine responsiveness level for a second predetermined change in fan speed over a second predetermined change in power level greater than the first predetermined change in power level. 3. The method in accordance with claim 1, wherein closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the engine comprises closing one or more clearance control valves in flow communication with the shroud. 4. The method in accordance with claim 1, wherein determining that an airplane is in a first flight condition includes determining that the airplane is in a steady-state cruise condition. 5. The method in accordance with claim 1, wherein reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine comprises limiting engine acceleration in response to a throttle increase. 6. A clearance control system for reducing a turbine clearance gap between a plurality of blades of a turbine engine and a shroud of the turbine engine, said clearance control system comprising a flight operation controller configured to: determine that an airplane is in a first flight condition;adjust the turbine clearance gap to a first clearance gap distance associated with the first flight condition;determine a demand for a second flight condition;adjust an engine responsiveness to a first engine responsiveness level for a first predetermined change in a power parameter of the turbine engine;wherein the power parameter includes fan speed, and wherein the flight operation controller is further configured to adjust the engine responsiveness to the first engine responsiveness level for a first predetermined change in fan speed over a first predetermined change in power levelreduce the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the turbine engine; andclose a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the turbine engine. 7. The clearance control system in accordance with claim 6, wherein the flight operation controller is further configured to reduce the engine responsiveness to the second engine responsiveness level for a second predetermined change in fan speed over a second predetermined change in power level greater than the first predetermined change in power level. 8. The clearance control system in accordance with claim 6, wherein the flight operation controller is further configured to close one or more clearance control valves in flow communication with the shroud. 9. The clearance control system in accordance with claim 6, wherein the first flight condition is a steady-state cruise condition. 10. The clearance control system in accordance with claim 6, wherein the second engine responsiveness level limits engine acceleration in response to a throttle increase. 11. An airplane comprising: a plurality of turbine engines; anda clearance control system for reducing a turbine clearance gap between a plurality of blades and a shroud of at least one of the plurality of turbine engines, the clearance control system comprising a flight operation controller configured to:determine that the airplane is in a first flight condition;adjust the turbine clearance gap to a first clearance gap distance associated with the first flight condition;determine a demand for a second flight condition;adjust an engine responsiveness to a first engine responsiveness level for a first predetermined change in a power parameter of the at least one of the plurality of turbine engines;wherein the power parameter includes fan speed, and wherein the flight operation controller is further configured to adjust the engine responsiveness to the first engine responsiveness level for a first predetermined change in fan speed over a first predetermined change in power level;reduce the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the at least one of the plurality of turbine engines; andclose a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the at least one of the plurality of turbine engines. 12. The airplane in accordance with claim 11, wherein the flight operation controller is further configured to reduce the engine responsiveness to the second engine responsiveness level for a second predetermined change in fan speed over a second predetermined change in power level greater than the first predetermined change in power level. 13. The airplane in accordance with claim 11, wherein the flight operation controller is further configured to close one or more clearance control valves in flow communication with the shroud. 14. The airplane in accordance with claim 11, wherein the first flight condition is a steady-state cruise condition.
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이 특허에 인용된 특허 (7)
Walker Roger C. (Fairfield OH) Reese Scott P. (West Chester OH) Joyce David L. (Middletown OH) Kastrup David A. (Cincinnati OH), Active clearance control for gas turbine engine.
Schwarz Fred M. (Glastonbury CT) Crawley ; Jr. Clifton J. (Glastonbury CT) Rauseo Anthony F. (Middletown CT) Lagueux Ken R. (Berlin CT), Active clearance control with cruise mode.
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