发明名称 |
AIRCRAFT ENGINE WITH INTER-TURBINE ENGINE FRAME SUPPORTED COUNTER ROTATING LOW PRESSURE TURBINE ROTORS |
摘要 |
An aircraft gas turbine engine assembly includes an inter-turbine frame (6 0) axially located between high and low pressure turbines (24, 26). Low pressur e 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 rotatab ly 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 an d aft central bores (84, 85) are fixedly joined to axially spaced apart forward an d 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).
|
申请公布号 |
CA2414992(A1) |
申请公布日期 |
2003.09.01 |
申请号 |
CA20022414992 |
申请日期 |
2002.12.19 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
JOHNSON, JAMES E.;MONIZ, THOMAS;SEDA, JORGE F.;SZUCS, PETER N.;STEINMETZ, GREGORY T.;BRAUER, JOHN C.;DUNBAR, LAWRENCE W.;GLIEBE, PHILIP R. |
分类号 |
B64D27/10;F01D9/04;F01D11/00;F01D11/02;F01D25/16;F01D25/18;F01D25/24;F02C3/067;F02C7/20;F02K3/06;F02K3/072;(IPC1-7):F02C3/067 |
主分类号 |
B64D27/10 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|