A pressure sensor (12) is located in the compressor stage of a gas turbine engine (10) to provide a pressure signal (PR1) that shows the compressor flow characteristics. The pressure signal (PR1) is applied to a bandpass filter (16) with roll-offs above and below N2. The difference between the filter output and a stored value for the pressure signal is integrated, and compressor bleed valves (18) are opened if the integral exceeds a stored threshold. The health of a compressor stage is determined by analyzing the magnitude of compressor pressure variations at N2 while accelerating the engine and by comparing the magnitude with values obtained from a compressor with a known stall margin.
申请公布号
EP0777828(B1)
申请公布日期
2002.08.21
申请号
EP19960920104
申请日期
1996.04.17
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
GERTZ, JEFFREY, B.;SHARMA, OM, PARKASH;EVEKER, KEVIN, M.;NETT, CARL, N.;GYSLING, DANIEL L.;FEULNER, MATTHEW, R.