Patent ID: 8887485
Filing Date: 2014-11-18
Classification: F02C,F02K,F05D,Y10T

Abstract:
1. An apparatus comprising: a gas turbine engine having three spools including a first pressure spool, a second pressure spool, and a third pressure spool; a fan having a first fan stage and a second fan stage, the fan rotatingly coupled with a first pressure shaft of the first pressure spool; a compressor bypass operable to bypass a compressed air past a third pressure compressor of the third pressure spool, the compressor bypass in fluid communication with a core combustor of the gas turbine engine such that working fluid that flows through the compressor bypass passes directly to and through the core combustor of the gas turbine engine before flowing through a bladed turbine rotor of the gas turbine engine; a turbine bypass operable to bypass a portion of a combustion flow past a third pressure turbine of the third pressure spool; and a clutch coupling the third pressure turbine to a second pressure shaft of the second pressure spool, wherein work produced from the third pressure turbine is used to rotate a second pressure compressor when the clutch engages the third pressure turbine to the second pressure shaft.