Turbine component cooling with closed looped control of coolant flow
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-011/24
F01D-017/02
F01D-017/08
F01D-005/08
F02C-003/13
F02C-007/12
F02C-007/18
F02C-009/18
F02C-006/08
출원번호
US-0682280
(2012-11-20)
등록번호
US-9249729
(2016-02-02)
우선권정보
GB-1121428.5 (2011-12-14)
발명자
/ 주소
Bacic, Marko
출원인 / 주소
ROLLS-ROYCE plc
대리인 / 주소
Oliff PLC
인용정보
피인용 횟수 :
0인용 특허 :
7
초록▼
A gas turbine engine has, in flow series, a compressor section, a combustor, and a turbine section. The engine further has a cooling system which diverts a cooling air flow received from the compressor section to a heat exchanger and then to the turbine section to cool a component thereof. The cooli
A gas turbine engine has, in flow series, a compressor section, a combustor, and a turbine section. The engine further has a cooling system which diverts a cooling air flow received from the compressor section to a heat exchanger and then to the turbine section to cool a component thereof. The cooling air flow by-passes the combustor and is cooled in the heat exchanger. The cooling system has a valve arrangement which regulates the cooling air flow. The engine further has a closed-loop controller which estimates and/or measures one or more temperatures of the cooled component, compares values derived from the estimated and/or measured temperatures with one or more corresponding targets, and issues a demand signal to the valve arrangement based on the comparison and a value of the demand signal at a previous time step.
대표청구항▼
1. A gas turbine engine having, in flow series, a compressor section, a combustor, and a turbine section, and further having: a cooling system which diverts an air flow received from the compressor section to a heat exchanger and then to the turbine section to cool a component thereof, the air flow
1. A gas turbine engine having, in flow series, a compressor section, a combustor, and a turbine section, and further having: a cooling system which diverts an air flow received from the compressor section to a heat exchanger and then to the turbine section to cool a component thereof, the air flow by-passing the combustor and being cooled in the heat exchanger, and the cooling system having a valve arrangement which regulates the air flow downstream of the heat exchanger; anda closed-loop controller apparatus operable to control operation of the valve arrangement by sending for a current time step of a series of time steps, a current demand signal, the closed-loop controller comprising:at least one sensor for monitoring a real-time parameter of the component over the series of time steps,a processor for calculating a demand signal at each time step to operate the valve arrangement to control the air flow,a memory for storing one or more most recent demand signals calculated at the most recent in the series of time steps,the processor configured for determining an error between a pre-defined target parameter and the real-time parameter sensed at the current time step and determining the current demand signal to cause the valve arrangement to control the air flow to address the error, wherein the step of determining the current demand signal involves a calculation using, the error and a most recent demand signal of the one or more most recent demand signals stored in the memory of the controller. 2. The gas turbine engine according to claim 1, wherein the at least one sensor monitors a temperature of the component, the gas turbine engine further having one or more temperature measuring devices adapted to measure the temperature of the component at one or more locations thereof. 3. The gas turbine engine according to claim 1, comprising one or more sensors adapted to measure at least the temperature of the air flow which has been cooled in the heat exchanger and the temperature of the air flow exiting the compressor section, the processor estimating a real-time temperature of the component on the basis of at least a measured temperature of the air flow which has been cooled in the heat exchanger, and a measured temperature of the air flow exiting the compressor section and using an estimate of the real-time temperature of the component as the real-time parameter for the purpose of determining the current demand signal. 4. The gas turbine engine according to claim 1, wherein the closed-loop controller apparatus monitors one or more stresses in the component. 5. The gas turbine engine according to claim 4, wherein the at least one sensor is a temperature sensor and the processor uses a reduced order model to calculate from temperatures sensed by the temperature sensor the one or more stresses in the component. 6. The gas turbine engine according to claim 1, wherein the component is a turbine disc. 7. The gas turbine engine according to claim 1, wherein the valve arrangement includes one or more switched vortex valves. 8. The gas turbine engine according to claim 1, wherein the heat exchanger is located in a bypass air stream of the gas turbine engine. 9. A method of operating a gas turbine engine having, in flow series, a compressor section, a combustor, and a turbine section, the method including the steps of: cooling the air flow in the heat exchanger by diverting an air flow received from the compressor section to a heat exchanger, by-passing the combustor, and then to the turbine section to cool a component thereof;monitoring a real-time parameter of the component over a series of time steps;calculating a demand signal at each time step configured to operate a valve arrangement to control the air flow;storing one or more demand signals calculated at a most recent in the series of time steps;determining a target parameter and an error between the target parameter and the real-time parameter and determining a current demand signal operable to cause the valve arrangement to control the air flow to address the error, wherein the step of determining the current demand signal involves a calculation using the most recent demand signal in the series of time steps and the error; and,communicating the current demand signal to the valve arrangement. 10. The method according to claim 9, further including a step of: measuring and/or estimating one or more temperatures of the component anddetermining one or more stresses in the component based on estimated and/or measured temperatures;determining a target stress and determining an error between a real-time stress and the target stress.
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이 특허에 인용된 특허 (7)
Elovic Ernest (Cincinnati OH), Cooling air cooler for a gas turbofan engine.
Schwarz Frederick M. (162 Butler Dr. Glastonbury CT 06033) Candelori David J. (109 Hubbard St. Glastonbury CT 06033) Brooke Richard D. (243-A New State Rd. Manchester CT 06040), Modulated gas turbine cooling air.
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