|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 10 인용 특허 : 4|
A gas turbine engine control system modulates a compressor bleed valve between full open and full closed during transient engine operation as a function of the rate of change of compressor speed biased by flight conditions, such as altitude, and corrected for engine power level. A hysteresis construct may be applied to the rate of change of compressor speed before such rate is used to determine the new bleed valve position.
In a gas turbine engine having a compressor and a compressor bleed valve, means for controlling said valve during an engine transient comprising: function generator means for generating, during the engine transient, a transient bleed reset position signal for use in reducing a shift in the compressor operating line toward the compressor stall line during the transient, the signal having a value which is (1) a function of the rate of change of compressor speed, (2) independant of any schedule of maximum allowable rate of change of compressor speed, and (3...