F - Mech Eng,Light,Heat,Weapons – 02 – C
Patent
F - Mech Eng,Light,Heat,Weapons
02
C
F02C 3/067 (2006.01) F01D 9/04 (2006.01) F01D 11/00 (2006.01) F01D 25/16 (2006.01) F01D 25/18 (2006.01) F01D 25/24 (2006.01) F02C 7/20 (2006.01) F02K 3/072 (2006.01)
Patent
CA 2414992
An aircraft gas turbine engine assembly includes an inter-turbine frame (60) axially located between high and low pressure turbines (24, 26). Low pressure turbine (26) has counter rotating low pressure inner and outer rotors (200,202) with low pressure inner and outer shafts (130,140) which are at least in part rotatably disposed co- axially within a high pressure rotor (33). Inter-turbine frame (60) includes radially spaced apart radially outer first and inner second structural rings (86, 88) disposed co- axially about a centerline (8) and connected by a plurality of circumferentially spaced apart struts (90). Forward and aft sump members (104, 106) having forward and aft central bores (84, 85) are fixedly joined to axially spaced apart forward and aft portions (108, 110) of the inter-turbine frame (60). Low pressure inner and outer rotors (200,202) are rotatably supported by a second turbine frame bearing (76) mounted in aft central bore (85) of aft sump member (106). A mount (120) for connecting the engine to an aircraft is located on first structural ring (86).
Brauer John C.
Dunbar Lawrence W.
Gliebe Philip R.
Johnson James E.
Moniz Thomas
Company General Electric
Craig Wilson And Company
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