Turboprop engine with compressor turbine shroud

摘要

A turboprop engine including an annular outer case including a mount ring for attachment to an aircraft along a plane to transfer loads from a propeller and having an annular flange extending radially inwardly therefrom within the plane, an annular turbine support case received within the outer case and connected to the outer case only through a direct connection with the annular flange allowing a limited relative pivoting motion between the turbine support case and the mount ring, and a turbine section including a rotor closely surrounded by a shroud with an annular tip clearance being defined therebetween, the shroud being directly connected to and located by the turbine support case. A method of isolating a turbine shroud from propeller loads in a propeller engine is also disclosed.

主权项

1. A turboprop engine comprising:
an outer case including a mount ring, the mount ring defining a mount plane and an attachment location for attachment to an aircraft within the mount plane, the outer case being annular, the mount ring configured for attachment to the aircraft at the attachment location to transfer loads from a propeller, the mount ring having a flange extending radially inwardly therefrom within the mount plane, the flange being annular; a turbine support case received within the outer case and being annular, the turbine support case being connected to the outer case only through a direct connection with the flange of the mount ring, the direct connection defining a pivot point, the turbine support case and the mount ring being relatively movable around the pivot point allowing a limited relative pivoting motion; and a turbine section including a rotor closely surrounded by a shroud with an annular tip clearance being defined therebetween, the shroud being directly connected to and located by the turbine support case.