COWLING FOR TURBO-FAN ENGINE OF AIRCRAFT AND BRANCHED FAN-DUCT ASSEMBLY

摘要

PURPOSE: To reduce airflow losses and to provide a strong, lightweight, fire resistant core engine cowl by disposing an annular core cowl extending between a fan frame and a turbine frame, and fan duct bifurcated sidewalls extending axially at a peripheral end of the cowl. CONSTITUTION: A fan 12 of a fan-jet engine 10 pressurizes and feeds air to a fan bypass duct 14 disposed between and inner fan case 16 and an outer fan case 18 and to a booster 120 located at a forward portion of a core engine flow path 13. Further, the booster 120 rotates on a low pressure rotor 122 driven by a low pressure turbine 123 and further compresses air that is then ducted to a compressor 124 of a core engine 126. The core engine 126 is disposed in a cavity 39 circumscribed by an annular inner cowl 38. Then, the inner cowl 38 of a bifurcated fan duct 37 is disposed between a fan frame 50 and a turbine frame 70, and sidewalls 40 extend until an end of the fan duct 14.