Patent GB-634332-A (GB)
Title: Improvements in and relating to rotary wing aircraft
IPC: B64C27/18
Filed: 1947-07-18
Abstract: 634,332. Rotary-wing aircraft. SOC. NATIONALE DE CONSTRUCTIONS AERONAUTIQUES DU CENTRE. July 18, 1947, Nos. 19226 and 19227. Convention dates, July 25, 1946, and June 18, 1947. [Class 4] [Also in Group XXVI] A rotary-wing aircraft is provided with a jet-driven lifting rotor, the compressed air for feeding the blade jets being drawn from the compressor of a turbo-jet engine, part of the combustion products of which are employed for translational propulsion of the aircraft. As shown in Fig. 2, the turbo-jet unit A is mounted in the fuselage 9, the jet 6 discharging below the tail control surfaces. Air for the blade jets 14 may be bled through a pipe 8 connected to a suitable stage of the compressor 2, Fig. 1 (not shown), or from the outlet thereof, Fig. 18, while in addition combustion - gases may be fed through a second pipe 58 either before or after passing through the turbine 5. In a further arrangement, Fig. 22 (not shown), a portion of the air from the compressor byepasses the turbine and is mixed with part of the turbine exhaust. Fig. 24 shows a construction in which a second compressor 70a is coupled to the turbine compressor 72a, its delivery being controlled by a valve 74 so that any desired proportion of its delivery may byepass the turbine. Such air may pass through a heat exchanger supplied with the turbine exhaust gases, Fig. 23 (not shown). The air or mixed air and combustion products are fed to a distributer at the top of the rotor shaft, and as shown in Fig. 7 the distributer 31 may be provided with a non- rotatable tiltable member 30 controlled by rods 33, 34 in order that the supply of gases to the blade jets may be subject to cyclical variation. A similar effect may be obtained by providing cyclically adjustable flaps to control the outlet area of the blade nozzles, Fig. 25 (not shown). Auxiliary fuel burners may be fitted in the ducts leading to the blade nozzles, or at the nozzles themselves. Boundary layer control may be effected through slots in the rotor blades, such slots being connected to points 42a, 42b, 42c ... in the compressor diffuser, Fig. 18, for suction effect, or to a suitable pressure stage of the compressor for blowing the boundary layer from the blades. Fig. 29 shows a rotor blade with suction slots 97 in the upper trailing edge of the inner portion of the blade length, the blade section being divided into two portions 98, 99, the former communicating with the slots 97 and the latter with the blade nozzle 101. For directional control purposes, the discharge nozzle of the main turbo-jet unit may be mounted for lateral movement about a vertical axis, or the jet may discharge over a movable rudder surface, Figs. 20 and 21 (not shown). The Specification as open to inspection under Sect. 91 comprises also an arrangement, Fig. 25 (Cancelled), in which an internal-combustion engine 78 drives a compressor 80, the discharge from which cools the engine and passes through byepasses 81 fitted with venturis 82 in the region of the engine exhaust pipes 83. An auxiliary fuel burner 84 may be fitted. In the arrangement according to Fig. 26 (Cancelled), the engine exhaust pipes have a common outlet 83a. This subject-matter does not appear in the Specification as accepted.