F - Mech Eng,Light,Heat,Weapons – 02 – C
Patent
F - Mech Eng,Light,Heat,Weapons
02
C
F02C 3/04 (2006.01) B64C 11/48 (2006.01) F01D 1/26 (2006.01) F02C 3/067 (2006.01) F02C 7/00 (2006.01) F02K 3/072 (2006.01)
Patent
CA 2436664
A low pressure turbine section (26) for an aircraft gas turbine engine (10) includes a low pressure turbine flowpath and counter rotatable low pressure inner and outer shaft rotors (200 and 202) having inner and outer shafts (130 and 140), respectively. The low pressure inner and outer shaft rotors (200 and 202) include low pressure first and second turbine blade rows (138 and 148) disposed across the turbine flowpath and drivingly connected to first and second fan blade rows (13 and 15), respectively. The first low pressure turbine blade rows (138) are disposed downstream of the second low pressure turbine blade rows (148) along said low pressure turbine flowpath (28). Rows of non-rotatable low pressure vanes (210) are disposed across the low pressure turbine flowpath (28) between the first low pressure turbine blade rows (138) and between the second low pressure turbine blade rows (148). An annular vaneless gap (58) may be located between an aftmost row (52) of the second low pressure turbine blade rows (148) and a forwardmost row (50) of the first low pressure turbine blade rows (138).
Moniz Thomas Ory
Orlando Robert Joseph
Company General Electric
Craig Wilson And Company
LandOfFree
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