| 摘要 |
<p>1,057,201. Thrust reversers. UNITED AIRCRAFT CORPORATION. Jan. 27, 1965 [Feb. 12, 1964], No. 3541/65. Heading B7G. [Also in Division E2] A jet propulsion engine, e.g. a turbo-jet engine for supersonic flight, has a plug-type exhaust nozzle, the plug 26 containing pivoted flaps 100 forming a thrust reverser. The flaps are pivotally mounted at 102 on a sleeve 72 concentric with the axis 12 and fixed to a rear portion 34 of the plug, which is translatable by a ram 140 operated by hydraulic pressure or engine compressor pressure, and are opened by relative movement between the sleeve 72 and a further sleeve 74, to which the flaps are attached by links 110. The sleeves are held together by a rocker 90, mounted in the sleeve 74, which engages a recess 122 in the sleeve 122 and is held there by a sleeve 54, fixed to the fixed, upstream part 32 of the plug, until the rocker moving rearwardly with the sleeves 72, 74 and the portion 34, reaches the end 130 of the sleeve 54. The rocker may then detach from the recess 122 and the sleeve 72 move rearwardly relative to the sleeve 72, to extend the flaps 100 (Fig. 4, not shown). Adjacent flaps 100 overlap, have wedge-shaped tips 106 to deflect the gases forwardly, and may be connected to the links 110 at such points that the gas pressure tends to close them. The exhaust gases pass through an annular convergent duct 30 to the final nozzle 24.</p> |
