F - Mech Eng,Light,Heat,Weapons – 02 – C
Patent
F - Mech Eng,Light,Heat,Weapons
02
C
F02C 3/073 (2006.01) F01D 5/14 (2006.01) F02C 3/067 (2006.01) F02C 3/10 (2006.01)
Patent
CA 2548133
A turbofan engine (10) includes a fan (14), compressor (18), combustor (20), high pressure turbine (22), and low pressure turbine (24) joined in serial flow communication. The high pressure turbine (22) includes two stages of rotor blades (46) to effect corresponding exit swirl in the combustion gases discharged therefrom. A transition duct (50) includes fairings extending between platforms (54,56) for channeling the combustion gases to the low pressure turbine (24) with corresponding swirl. First stage rotor blades (66) in the low pressure turbine (24) are oriented oppositely to the rotor blades (46) in the high pressure turbine (22) for counterrotation.
Beacock Robert John
Cherry David Glenn
Clifford William Larson
Lee Ching-Pang
Moniz Thomas Ory
Company General Electric
Craig Wilson And Company
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