| 摘要 |
<p>1,258,331. Gas turbine ducted fan engines. GENERAL ELECTRIC CO. March 28, 1969 [March 28, 1968], No. 16294/69. Heading F1J. The invention relates to gas turbine ducted fan engines and particularly to means for mixing the turbine exhaust gas flow and the fan air-flow. The engine shown comprises a gas turbine gas generator 12, and a separate turbine 14 connected through shaft 15 to drive the fan 16 air delivered by the fan passing in part to the compressor 24 and in part through the annular duct 22, the turbine exhaust gases and the fan air passing through a mixing device 30 before discharging through propulsion nozzle 32. The turbine exhaust gases pass through a series of chutes 34 and the fan air from annular duct 22 passes through the spaces 36 between adjacent chutes. Each chute 34 is defined by a pair of side walls 42, 44, an inner wall 38 and an outer wall 40, the wall 40 diverging from the wall 38 in the direction of gas flow and the walls, 42, 44 which are substantially radial, converging in the direction of gas flow, the resulting sections at lines III, IIIA, IIIB, IIIC in Fig. 2 being as shown in Fig. 3 and the sections at lines IV, V, VI, VII being as in Figs.4, 5, 6, and 7 (only Fig. 6 is shown), the sections being of teardrop shape. The downstream portion of each wall 44 is defined by a pivotally mounted flap 48 whereby the area of the gas flow chute may be varied. Each flap 48 is operated by a link 52 and an axially-movable unison ring 54 which is movable by an actuator 56. A series of ports 60 are provided in the outer wall 101 of the gas flow duct between the turbines 28, 14 each port being controlled by a valve 62 operated by a piston device 68 such that when the valves are open a portion of gases pass through ports 60 into the annular fan air duct 22 whereby the fan turbine 14 supplies less power and the fan less air therefore. The ports 60 are located in line with the fan air spaces 36 between the chutes 34, Fig. 3. The radial walls 42, 44 of the chutes are utilized to transfer loading from the bearing 93 and structure 95 to a support ring 97 and turbine casing 99. A thrust reverse device comprising movable flap members 102 and blade cascades 100 is provided whereby the fan air may be discharged with a forward component for aircraft braking. A portion of fan air flows in the spaces between the outer walls 40 so as to provide cool air in this region.</p> |
