Gas-driven propulsor with tip turbine fan

摘要

An engine comprises a gas generator having an exhaust plenum and a propulsor comprising a propulsion fan coaxially mounted within an annular turbine. The annular turbine comprises a turbine duct and a plurality of turbine rotor blades rotationally coupled to the propulsion fan. A plurality of hollow struts extend axially and radially from the gas generator to the annular turbine. The hollow struts comprise flow ducts connecting the exhaust plenum to the turbine duct.

主权项

1. An assembly for an aircraft engine comprising:
a gas generator having an exhaust plenum; a propulsor comprising a propulsion fan coaxially mounted within an annular turbine assembly, wherein the propulsion fan comprises first and second fan stages coaxially mounted within the annular turbine assembly, wherein the first and second fan stages are counter-rotating, wherein the first and second fan stages comprise different numbers of fan blades, and wherein the annular turbine assembly comprises a turbine duct and a plurality of turbine rotor blades rotationally coupled to the propulsion fan; and a plurality of hollow struts extending axially and radially from the gas generator to the annular turbine assembly, the hollow struts comprising flow ducts connecting the exhaust plenum to the turbine duct.