| 摘要 |
743,598. Controlling boundary layer. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. April 2, 1954 [April 15, 1953], No. 10351/53. Class 4. [Also in Group XXVI] An aircraft boundary layer suction system in which a different degree of suction is to be applied at each of a plurality of suction openings in the surface of the aircraft, comprises a compressor system having a plurality of compression stages arranged for series flow, an inlet to its first stage and further inlets each leading directly to one of its subsequent stages, said suction openings each being connected to a different one of said inlets. The wing comprises areas of porous skin 11, 12, 13, 14 communicating with cells or compartments 15, 16, 17, 18 having conduits 19, 20, 21, 22 connected to the inlet sides of different stages of an axial flow compressor 27 (see Group XXVI) whereby the area 12 subjected to highest pressure is connected to the low-pressure stage of the compressor, the remaining areas being connected in order of decreasing pressure with the successive stages of the compressor. A turbine 29 is drivingly connected to the shaft 28 of the compressor and it is connected by a conduit 76 and a valve 78 to the outlet side of a gas turbine engine 75. The valve 78 is coupled to mechanism 79a according to Specification 606,176, [Group XXVI], for reducing the area of the nozzle of the gas turbine when the turbine 29 is being driven. In a wing having two gas-turbine engines a further compressor may be connected to conduits 65, 66, 67, 68. A further embodiment is described in which the conduits from the wing are connected to the inlets of different stages of a multi-stage centrifugal compressor. An embodiment is described in which suction is applied to the surfaces of a thick section wing having a concave upper surface at the trailing edge.
|
