Method and device to avoid turbo instability in a gas turbine engine

  • US 8,313,280 B2
  • Filed: 10/12/2006
  • Issued: 11/20/2012
  • Est. Priority Date: 10/12/2006
  • Status: Active Grant
First Claim
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1. A turbofan engine control system for managing a turbofan operating line comprising:

  • a spool including a turbine housed in a core nacelle;

    a turbofan coupled to the spool;

    a fan nacelle surrounding the turbofan and core nacelle and providing a bypass flow path having a nozzle exit area; and

    a controller programmed to effectively change the nozzle exit area in response to an undesired stability margin for the turbofan by lowering the turbofan operating line and increasing the turbofan stability margin, wherein the controller detects the undesired stability margin.

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