Patent attributes
A method of isolating a turbine shroud from propeller loads in an engine having an outer case with a mount defining a mount plane and an attachment location within the mount plane, the mount configured for attachment of the engine to an aircraft at the attachment location to transfer the propeller loads. The shaft of the engine is supported with a portion of the outer case extending from the mount and defining a load path for the propeller loads. The turbine support case is attached to extend free of the load path, by attaching the turbine support case to the outer case only through a connection along the plane, the connection defining a pivot point allowing a limited relative pivoting motion around the pivot point between the turbine support case and the mount. The turbine shroud is located by directly connecting it to the turbine support case.
