Patent ID: 7536864

Claim:
A gas turbine engine system, comprising: a compressor section; the compressor section comprising a first compressor stage and a second compressor stage; a turbine section; the turbine section comprising a first turbine stage and a second turbine stage; one or more pressure sensors located within the turbine section; a first flow path connecting the first compressor stage and the first turbine stage; a second flow path connecting the second compressor stage and the second turbine stage; a crossover flow path connecting the first flow path and the second flow path; and an ejector positioned about the crossover flow path and the first flow path; the ejector comprising a mechanically variable motive nozzle ejector with a movable ram positioned therein operable by an actuator in communication with the one or more pressure sensors; wherein the actuator varies the position of the movable ram based upon a sensed pressure.