| 摘要 |
1,211,192. Gas turbine by-pass type jet engines. GENERAL ELECTRIC CO. June 25, 1965 [July 1, 1964], No.27143/65. Heading F1J. An aircraft turbofan engine has an axial flow compressor 10 for generating a relatively high volume, low pressure propulsive gas stream, the compressor 10 being enclosed in a coaxial cowl 2 in which a nacelle or pod 3 housing a gas turbine engine 32 is partially telescoped, the pod 3 terminating at its aft end in an exhaust nozzle 44 for the discharge of the exhaust gases from the engine 32, and the cowl 2 having a forward end portion defining an air inlet 12 and an aft end portion forming with the pod 3 a convergent exhaust nozzle for the compressor 10, wherein the pod 3 has a circumference 50 of maximum diameter in the exhaust nozzle plane of the compressor 10 forming a throat 16, the pod 3 being convergent downstream of the throat 16 to form a recompression surface 52 for the exhaust gases of the compressor 10, and wherein the aft end inner surface of the cowl 2 defines an angle of from 4 degrees to 7 degrees with the engine axis, the pod 3 downstream of the circumference 50 defining an angle of from 4 degrees to 7 degrees with the engine axis. A conical plug 4 is partially disposed within the exhaust nozzle 44, having its circumference 66 of maximum diameter in the exit plane of the nozzle and providing a recompression surface 68 for the exhaust gases of the gas turbine engine 32. The aft end inner surface of the exhaust nozzle 44 defines an angle of from 4 degrees to 7 degrees with the engine axis and the conical surface of the plug 4 downstream of its circumference 66 defines an angle of from 7 degrees to 10 degrees with the engine axis. The pod 3 comprises inner and outer walls 26 and 28, respectively, the space between which houses aircraft and engine auxiliaries. One of these auxiliaries comprises collapsible flow turning members for the low pressure compressor exhaust flow (shown in broken outline). The engine is attached to the wing or fuselage of an aircraft by means of a pylon 62 attached to the engine, the leading edge 60 of the pylon 62 extending into the throat 16 and being affixed to the forward body portion of the pod 3. |
