公开(公告)号：DE3660564D1

公开(公告)日：1988-09-22

申请号：DE3660564

申请日：1986-05-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DENNISON WILLIAM THOMAS ,  BRODELL ROBERT FRANK

IPC: F02K3/04 ,  F01D7/00 ,  F01D25/16 ,  F02C7/06 ,  F02K3/06 ,  F02C7/36

Abstract: In a gas turbine engine with a bypass duct, a rotating stage of airfoils (42) in the bypass duct is supported through and driven by torque transmitting members (84) extending across the core stream flow path, but which are sufficiently flexible in the radial direction to avoid passing centrifugal loads from the rotating stage (42) across the core stream flow path. The rotating bypass stream stage (42) is also supported through a bearing (52) secured directly to the engine main support structure radially outwardly of the core stream flow path. The majority of aircraft maneuver loads are reacted at this bearing (52), and a minor portion of the maneuver loads pass across the core stream to a bearing (85) located radially inwardly thereof. The airfoils (42) may be either variable pitch airfoils or fixed airfoils. If variable pitch, they may be used to reverse the flow in the bypass duct for thrust reversing.