Unstable operation of a gas turbine engine subject to variable shaft loading and bleed air loading may be avoided in a gas turbine (12, 22, 40) having first and second stage compressors (12, 22) on a common shaft (10) with a turbine wheel (40) and by providing the inlet (14) to the first stage compressor (12) with variable inlet guide vanes (16). Bleed air flow is controlled by a bleed air valve (60) connected to the interface (24) of the first stage compressor outlet (18) and the second stage compressor inlet (20). A controller (66) is operative to cont...
A turbine engine and control system therefor comprising: a turbine engine adapted to be coupled to a load and including interconnected first and second stage compressors, a turbine wheel connected in driving relation thereto, an exhaust from said turbine wheel, a combustor interposed between the turbine wheel and the second stage compressor, and variable inlet guide vanes at the inlet to said first stage compressor; means defining a controllable bleed air flow path connected between said first and second stage compressor and including a bleed air flow se...
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