Patent GB-1036134-A (GB)
Title: Improvements in gas turbine power plant for v.s.t.o.l. aircraft
Inventor: YOUNG PIERRE HENRY JOHN
IPC: B64C29/00
Filed: 1962-04-25
Abstract: 1,036,134. Gas turbine jet engines. BRISTOL SIDDELEY ENGINES Ltd. April 10, 1963 [April 25, 1962], No. 15803/62. Heading F1J. [Also in Division B7] A gas turbine power plant which is adapted to produce upthrust by downward discharge of working fluid comprises a compressor for producing the downward discharge, a turbine connected to drive the compressor, combustion equipment to which air under pressure and fuel are supplied, gases from the combustion equipment passing to the turbine. A variable datum speed governor device is provided to control the fuel supply to the combustion equipment so as to maintain the rotational speed of the turbine constant. Means are provided for bleeding compressed gas from a point upstream of the turbine at substantially combustion equipment pressure, also further means automatically responsive to the bleed flow which are arranged to act on the governor device in such a way as to lower the datum speed with increase of bleed flow. The aircraft shown is provided with a power plant of the vertical lift-forward thrust kind which comprises a low pressure compressor 14, a high pressure compressor 17, combustion equipment 18, a high pressure turbine 19 which drives the compressor 17 by means of shaft 20, and a low pressure turbine 21 which drives the low pressure compressor 14 by means of shaft 22. A portion of the air delivered by compressor 14 is discharged through the two lateral nozzles 16 which are angularly adjustable so that air under pressure may be discharged either rearwardly or downwardly. The exhaust gases from the turbine discharge through similar angularly adjustable nozzles 23. Gas under pressure may be tapped from the combustion equipment and flows through the flow meter 37 and shut-off valve 38 to the distribution ducting 39, the ducting supplying gas under pressure to control nozzles 33a, 33b disposed adjacent the aircraft wing tips and which control roll, also to control nozzles 34a, 34b disposed adjacent the forward and rearward ends of the aircraft fuselage to control pitch, and to control nozzles 35a, 35b disposed in the tail fin 13 and directed laterally to control yaw. The flow meter is connected by transmission 47 so as to vary the datum setting of a governor 44 which controls flow of fuel to the combustion equipment through the fuel control unit 45. The datum setting of the governor may also be varied by the pilot's throttle control 46. The control nozzles 33a, 33b, 34a, 34b have associated therewith shutters 40 and the nozzles 35a, 35b have associated therwith a shutter in the form of an angularly movable cylinder 42 with ports 43a, 43b. The movement of the shutters 40 and 42 is controlled by movement of the appropriate aircraft control surfaces. Thus lateral movement of the control column 26 controls movement of the ailerons 24a, 24b; should the control column be moved so as to lower the aileron 24a so as to raise the wing on which it is mounted, then the shutter 40 of the nozzle 33a is moved to open the nozzle whereby the gas discharging from the nozzle acts to produce a thrust also tending to raise the wing. Should the control column be moved so as to lower the elevators then the shutter 40 of the nozzle 34b is moved to open the nozzle and the resulting thrust acts to put the nose of the aircraft down. The shutter 40 of the nozzle 34a adjacent the nose of the aircraft is connected to the elevator transmission so that the nozzle is opened when the elevators are raised. The shutter 42 controlling the yaw control nozzles 35a, 35b is operatively connected to the rudder 26 so that the nozzle on the side to which the rudder is turned opens.