GB1010990A - Air intake for a supersonic jet engine - Google Patents

Abstract

1,010,990. Gas turbine jet engines. ROLLS-ROYCE Ltd. Oct. 23, 1964, No. 43415/64. Headings FIG and F1J. An air intake for a supersonic jet engine comprises a cylindrical outer casing within which is mounted at least one radially extending flexible vane which divides the interior of the casing into a number of passages for the flow of ram air therethrough, there being means for bending the or each vane axially so that the shape of each passage may be varied to suit the speed of the air flow therethrough. The jet engine shown in Fig. 1 comprises an air intake passage 23 of annular form through which air flows to the compressor 22. The air intake is formed by an outer wall 24 which comprises a series of ring members 27, and by an inner wall which comprises a series of ring members 30. A series of radially disposed flexible vanes 31 extends between the ring members to form a series of air flow passages 32, the vanes being secured to the ring members at their radially inner and outer edges whereby upon relative rotation of the adjacent ring members the shape of the air flow passages may be varied, for example as shown in Figs. 9 and 10, the configuration shown in Fig. 9 being that for subsonic conditions and that in Fig. 10 that for supersonic conditions. Each vane 31 is secured to each of the ring members 27 or 30 by means of a stud 33 as shown in Fig. 3. The adjacent ring members may be connected by means of a pin and inclined slot arrangement so that relative circumferential movement of adjacent ring members causes relative axial movement thereof. The relative circumferential movement of adjacent ring members is effected by means of an actuator 36 connected to two adjacent members. Each vane may be formed by two walls which lie adjacent each other in the subsonic position but which move apart circumferentially in the supersonic position so as to form a vane of varying thickness chordwise thereof.