TURBOFAN AERO ENGINES AND PROPULSION NOZZLES THEREFOR

摘要

1535598 Gas turbine ducted fan engines ROLLS-ROYCE Ltd 19 May 1977 [27 May 1976] 21970/76 Heading F1J In a gas turbine ducted fan engine the exit area 22 of the by-pass air propulsion nozzle is defined between the downstream end of the bypass duct casing 24 and the lobes of the core engine propulsion nozzle 20. In a modification Figs. 1a, b (not shown) the lobes extend radially beyond the by-pass duct casing.