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특허 상세정보

Gas turbine engine control based on inlet pressure distortion

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-009/16   
미국특허분류(USC) 60/3929 ; 60/242 ; 364/43102 ; 415/26
출원번호 US-0074431 (1993-06-09)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 26  인용 특허 : 0
초록

Circumferential and radial inlet pressure distortion on an aircraft gas turbine engine are detected by a plurality of static pressure sensors and a signal processor, which computes the total pressure for each sensor to determine a pressure distortion pattern which the processor correlates with stored data for the engine and inlet to determine if the airflow geometry should be altered during flight. Time varying changes in the pressure from one or more of the pressure sensors is used to determine a stall condition, causing a change in engine airflow geome...

대표
청구항

A gas turbine engine comprising a control for modifying engine airflow geometry as a function of engine operating conditions comprising signal processing means, characterized by: means on a main air inlet to the compressor for providing a plurality of static pressure signals at a plurality inlet locations along inner and outer diameters of the inlet; and the signal processing means comprising means for converting each static pressure signal to a total pressure signal, for computing, from each total pressure signal, pressure variation values for radial an...

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