[특허]Method and apparatus for an aerodynamic stability management system

General Electric Company

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특허 상세정보

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Method and apparatus for an aerodynamic stability management system

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-009/20 F02C-009/50
미국특허분류(USC)	060/772; 060/039.27; 060/794; 415/017; 700/100
출원번호	UP-0528015 (2006-09-27)
등록번호	US-7827803 (2010-11-25)
발명자 / 주소	Wadia, Aspi Rustom Christensen, David K. Breeze-Stringfellow, Andrew Chung, Kiyoung Wiseman, Matthew William Szucs, Peter Nicholas
출원인 / 주소	General Electric Company
대리인 / 주소	Andes, Esq., William Scott
인용정보	피인용 횟수 : 8 인용 특허 : 22

초록
▼

A method for using an aerodynamic stability management system is disclosed. The method includes placing at least one pressure sensor in a compressor, the at least one pressure sensor communicating with an aerodynamic stability management system controller and monitoring gas turbine engine performance using the aerodynamic stability management system controller. The controller includes a memory, an input/output interface and a processor. The method also includes defining a correlation threshold value and calculating a correlation measure using a plurality of pressure signals generated by the at least one pressure sensor and comparing the correlation measure with the correlation threshold value. When the correlation measure is less than the correlation threshold value a corrective action is implemented.

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What is claimed is: 1. A method for using an aerodynamic stability management system comprising: placing at least one pressure sensor in a compressor, the at least one pressure sensor being in communication with an aerodynamic stability management system controller; monitoring a gas turbine engine performance using the aerodynamic stability management system controller, the controller including a memory, an input/output interface and a processor; defining a correlation threshold value and calculating a correlation measure using a plurality of pressure signals generated by the at least one pressure sensor, wherein calculating the correlation measure includes calculating the correlation measure according to a formula given by C ⁡ ( n ) = ∑ i = n - wnd n ⁢ ⁢ ( p i · p i_shaft ) ( ∑ i = n - wnd n ⁢ p i 2 ) · ( ∑ i = n - wnd n ⁢ p i_shaft 2 ) where C(n) is the correlation measure, p is a high-passed pressure signal, i is an index, shaft is a number of samples in one shaft revolution, n is a current sample index and wnd is a correlation window in number of samples; and comparing the correlation measure with the correlation threshold value, when the correlation measure is less than the correlation threshold value implementing a corrective action. 2. The method in accordance with claim 1 wherein placing the at least one pressure sensor in the compressor includes placing the at least one pressure sensor on an inside surface of the compressor over a stage of a plurality of rotor blades disposed on a rotor blade shaft. 3. The method in accordance with claim 1 wherein placing the at least one pressure sensor in the compressor includes placing the at least one pressure sensor on a rotor blade. 4. The method in accordance with claim 1 wherein implementing a corrective action includes sending an electrical signal to an engine control system and the engine control system implements the corrective action using a plurality of control devices. 5. The method in accordance with claim 4 wherein using the plurality of control devices includes adjusting a fuel flow, adjusting at least one of a plurality of variable stator vanes and using a compressor active clearance control scheme. 6. The method in accordance with claim 1, further comprising counting the total number of corrective actions. 7. The method in accordance with claim 6, further comprising using the total number of corrective actions for scheduling maintenance for the gas turbine engine. 8. The method in accordance with claim 1, further comprising counting a plurality of rotor blades, wherein each of the plurality of rotor blades corresponds to a lower pressure pulse reading. 9. The method in accordance with claim 1 wherein calculating the correlation measure further comprises computing the correlation measure between a first set of the plurality of pressure signals and a second set of the plurality of pressure signals, the first and second sets correspond to two sequential revolutions of a rotor blade shaft. 10. An aerodynamic stability management system comprising: a plurality of variable stator vanes; a correlation threshold value; and an aerodynamic stability management system controller, wherein the controller calculates a correlation measure using a plurality of pressure signals generated by an at least one pressure sensor, and compares the correlation measure with the correlation threshold value, such that when the correlation measure is less than the correlation threshold value a corrective action is implemented, wherein the correlation measure is calculated according to a formula given by C ⁡ ( n ) = ∑ i = n - wnd n ⁢ ⁢ ( p i · p i_shaft ) ( ∑ i = n - wnd n ⁢ p i 2 ) · ( ∑ i = n - wnd n ⁢ p i_shaft 2 ) where C(n) is the correlation measure, p is a high-passed pressure signal, i is an index, shaft is a number of samples in one shaft revolution, n is a current sample index and wnd is a correlation window in number of samples. 11. The system in accordance with claim 10 wherein at least one pressure sensor is disposed on an inside surface of the compressor over a stage of a plurality of rotor blades disposed on a rotor blade shaft. 12. The system in accordance with claim 10 wherein at least one pressure sensor is disposed on a rotor blade. 13. The system in accordance with claim 10 wherein an electrical signal is sent from the aerodynamic stability management system controller to an engine control system and the engine control system implements the corrective action using a plurality of control devices. 14. The system in accordance with claim 13 wherein using the plurality of control devices includes a fuel flow system, at least one of a plurality of variable stator vanes and a compressor active clearance control scheme. 15. The system in accordance with claim 10 wherein the aerodynamic stability management system controller is configured to count a total number of the corrective actions implemented. 16. The system in accordance with claim 15 wherein the total number of corrective actions implemented is used to schedule gas turbine engine maintenance. 17. The system in accordance with claim 10, further comprising a plurality of rotor blades, wherein each of the plurality of rotor blades corresponds to a lower pressure pulse reading. 18. The system in accordance with claim 10 wherein calculating the correlation measure further comprises computing the correlation measure between a first set of the plurality of pressure signals and a second set of the plurality of pressure signals, the first and second sets correspond to two sequential revolutions of a rotor blade shaft. 19. An aerodynamic stability management system controller comprising: a memory for storing data; an input/output interface configured to send and receive signals; and a processor programmed for calculating a correlation measure using a plurality of pressure signals generated by an at least one pressure sensor, a total number of corrective actions taken and a number of rotor blades, wherein calculating the correlation measure comprises comparing the correlation measure with a correlation threshold value, and when the correlation measure is less than the correlation threshold value, implementing a corrective action, wherein the correlation measure is calculated according to a formula given by C ⁡ ( n ) = ∑ i = n - wnd n ⁢ ⁢ ( p i · p i_shaft ) ( ∑ i = n - wnd n ⁢ p i 2 ) · ( ∑ i = n - wnd n ⁢ p i_shaft 2 ) where C(n) is the correlation measure, p is a high-passed pressure signal, i is an index, shaft is a number of samples in one shaft revolution, n is a current sample index and wnd is a correlation window in number of samples. 20. The controller in accordance with claim 19, wherein an electrical signal is sent from the input/output interface to an engine control system and the engine control system takes corrective action using a plurality of control devices to avoid engine stalling.

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Method and apparatus for an aerodynamic stability management system

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Method and apparatus for an aerodynamic stability management system

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