| 摘要 |
<p>712,351. Axial-flow compressors. UNITED AIRCRAFT CORPORATION. March 4, 1952 [March 7, 1951], No. 5630/52. Class 110(1) A multi-stage compressor comprises a casing having piloting surfaces on its inner face which are engaged by piloting flanges on vane-supporting rings which are positioned within the casing in end-to-end engagement, adjacent rings being maintained in concentric relation by locating pins. The inner casing comprises rings 50a-50g, Fig. 1, carrying guide vanes 12, and a ring 50h carrying straightening vanes 52. To facilitate assembly, the rings are split. A flange 60, Figs. 1 and 4, on ring 50a engages axially extending pins 62 carried by a flange 64 on ring 50b, and the ring 64 engages an inner surace 46 of an outer casing ring 40a. Rings 50c and 50d, Figs. 1 and 6, are connected by the engagement of a peripheral rebate 72 on the former with the end 79 of the latter, and a flange 75 on ring 50d is bolted between the adjacent flanged ends of outer casing rings 40a. 40b. At the remaining junctions between adjacent inner casing rings, the locating' and connecting means are similar to those between rings 50a and 50b, except that flanges 70 and 76 are of peripherally interrupted form. The annular manifolds 80 and 98 thus formed between the inner and outer casing communicate with bleed ports 82 and 96 respectively. The bleeding is controlled by piston-type valves 88. 100. The pressure for closing the valves may be derived from the compressor at a point downstream of the bleed ports.</p> |
