Approach to extending life of gas turbine engine
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0142240
(2002-05-09)
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발명자
/ 주소 |
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출원인 / 주소 |
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인용정보 |
피인용 횟수 :
1 인용 특허 :
8 |
초록
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Methods of increasing lifetimes of components in a gas turbine engine. Ordinarily, components are replaced after they experience a certain number of thermal cycles, or a certain operating temperature limit is exceeded. Under one form of the invention, the components are not replaced at that time, bu
Methods of increasing lifetimes of components in a gas turbine engine. Ordinarily, components are replaced after they experience a certain number of thermal cycles, or a certain operating temperature limit is exceeded. Under one form of the invention, the components are not replaced at that time, but are subjected to increased cooling, which decreases the highest temperature reached in subsequent thermal cycles. Also, many components are replaced when acceleration of an engine falls below a target. In one form of the invention, the components are not replaced, but (1) scheduled fuel flow is increased and (2) compressor stall margin also increased, in order to attain the target acceleration.
대표청구항
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1. Method of operating a gas turbine engine having a turbine blade which requires cooling, comprising:a) delivering cooling air to the turbine blade;b) determining whether thermal history of the turbine blade has reached a limit indicating that the turbine blade should be replaced and, if so,c) incr
1. Method of operating a gas turbine engine having a turbine blade which requires cooling, comprising:a) delivering cooling air to the turbine blade;b) determining whether thermal history of the turbine blade has reached a limit indicating that the turbine blade should be replaced and, if so,c) increasing cooling of the turbine blade.2. Method of operating a gas turbine engine having a component which requires cooling, comprising:a) delivering cooling air to the component;b) determining whether thermal history of the component has reached a limit indicating that the component should be replaced and, if so,c) increasing cooling of the component;d) demanding a predetermined type of acceleration in which fuel flow is scheduled according to engine parameters;e) ascertaining whether rate of acceleration meets a target and, if not,f) increasing scheduled fuel flow.3. Method according to claim 2, wherein the increasing of scheduled fuel flow causes a decrease in compressor stall margin, and further comprisingg) taking actions which increase compressor stall margin if the acceleration fails to meet the target.4. Method according to claim 3, wherein compressor stall margin is increased by increasing compressor bleed.5. Method of operating a gas turbine engine having a component which requires cooling, comprising:a) delivering cooling air to the component;b) determining whether a predetermined degree of deterioration of the engine has occurred and, if so;c) increasing cooling of the component,wherein the process of determining whether deterioration has occurred is based on one, or more, sensor outputs which report engine operating parameters and wherein one sensor output reports exhaust gas temperature.6. Method of operating a gas turbine engine having a component which requires cooling, comprising:a) delivering cooling air to the component;b) determining whether a predetermined degree of deterioration of the engine has occurred and, if so;c) increasing cooling of the component,wherein the process of determining whether deterioration has occurred is based on one, or more, sensor outputs which report engine operating parameters and wherein the sensor outputs report rotor speeds, pressures, and temperatures.
이 특허에 인용된 특허 (8)
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Uram Robert (East Pittsburgh PA), Accurate, stable and highly responsive gas turbine startup speed control with fixed time acceleration especially useful.
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Pisano, Alan David; Conaty, James Patrick; Wiseman, Matthew William; Sequeira, Sabrina Anne, Control strategy for gas turbine engine.
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Rowe Arthur L,GB2 ; Kurz Nikolaus,DEX, Control system for a ducted fan gas turbine engine.
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Irwin Craig W. ; Khalid Syed J., Controlling stall margin in a gas turbine engine during acceleration.
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Kurosawa Soichi (Hitachi JPX) Kumata Kazuhiko (Katsuta JPX), Cooling air flow controlling apparatus for gas turbine.
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Putman Robert L. (Palm City FL) Hovan Edward J. (Manchester CT), Method for maintaining blade tip clearance.
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Schwarz Frederick M. (Glastonbury CT) Crawley ; Jr. Clifton J. (Glastonbury CT) Rauseo Anthony F. (Middletown CT), Method of restoring exhaust gas temperature margin in a gas turbine engine.
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Weimer Matthew M. (Indianapolis IN) Jaeger Joseph A. (Greenwood IN), System for detecting and accommodating gas turbine engine fan damage.
이 특허를 인용한 특허 (1)
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Lebel, Jean-Francois; Davies, Alex; Haselbach, Frank; Fletcher, Paul, Method and apparatus for controlling modulated cooling of a gas turbine component.
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