GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO

GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO

  • CN 104,011,359 A
  • Filed: 12/28/2012
  • Published: 08/27/2014
  • Est. Priority Date: 12/30/2011
  • Status: Active Application
First Claim
Patent Images

1. for a cabin assembly for high bypass gas turbine engine, comprising:

  • Core cabin, described core cabin is defined around engine center bobbin thread;

    Fan cabin, described fan cabin is mounted around described core cabin at least in part, to be defined for the fan by-pass flow path of fan by-pass air stream;

    AndFan variable area nozzle, described fan variable area nozzle can move with respect to described fan cabin, to change fan nozzle discharge area and regulate the fan pressure ratio of described fan by-pass air stream during power operation, described fan pressure ratio is less than about 1.45.

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