Patent GB-1408309-A (GB)
Title: Gas turbine jet engine for an aircraft
IPC: F02K3/077
Filed: 1972-10-04
Abstract: 1408309 Gas turbine ducted fan engines MOTOREN-UND TURBINEN-UNION MUNCHEN GmbH 4 Oct 1972 [5 Oct 1971] 45839/72 Heading F1J The invention relates to an aircraft gas turbine jet engine of the by-pass type in which an additional turbine is provided which may be rendered either operative or inoperative by controlling the gas flow thereto, the additional turbine when operative serving to drive a fan or compressor, air from which is utilized to produce increased lift. The engine shown in Fig. 1 comprises an LP compressor 3, HP compressor 13, 14, combustion equipment 19, HP turbine 16 which drives the HP compressor through shaft 15, and LP turbine 5, 6 which drives the LP compressor through shaft 4. The air from the LP compressor is divided, part passing to the HP compressor and the other part passing through by-pass duct 10 and discharging through annular nozzle 11. In normal flight a series of pivotally-mounted flaps 21 are disposed as shown in the full-line position so that exhaust gases from the LP turbine discharge through duct 20 to the annular nozzle 11. At aircraft take-off and landing, the flaps 21 are moved to the chainline position so that exhaust gases from the LP turbine now discharge through duct 20 to a further turbine 25, 26, this turbine being drivingly connected through shaft 27 to a fan 28 disposed upstream of the LP compressor. Air from the fan passes in part to the LP compressor 3 and in part to a duct 32 and outlet 33 from which it passes under control of valve 34 to vertical lift nozzles. When the further turbine 25, 26 and fan 28 are inoperative, the fan blades 30 and the outlet guide blades 31 are rotated to a feathered position so that air-flow to the LP compressor 3 is not affected. In Fig. 2 the fan duct 38 of the LP compressor 3 is short so that fan air is discharged separately from the turbine exhaust gases, the LP turbine 7 is single-stage, and the additional turbine 24 is also single-stage, reheat combustion equipment 35, 36 is disposed between the LP turbine and the additional turbine, a discharge duct 45 is disposed downstream of the LP turbine being opened when the flaps 21 are disposed in the full-line position. The fan 28 comprises spokes 39 disposed upstream of the LP compressor blades 2 so that air-flow to the latter is not affected; the blades 41 of the fan 28 are mounted around the tips of the spokes. The fan blades 41 discharge to duct 43 and outlet 44 from which air passes under control of valve 34 to vertical lift nozzles. In Fig. 3, LP and HP compressors 2 and 12 are driven by LP and HP turbines 7 and 17 through shafts 4 and 15, the exhaust gases from LP turbine 7 passing to a further turbine 47 which drives a fan 53 through shaft 48; the fan blades 52 are carried from the rotor 49 by means of spokes 50 which are disposed upstream of the LP compressor blades so as not to affect the air-flow passing thereto. Air-flow from the fan 53 discharges through an annular nozzle. Exhaust gases from the further turbine 47 pass under control of variable flaps 21 either to annular exhaust duct 45 and nozzle 11 or to a still further turbine 24, the turbine 24 driving through shaft 27 a fan 42 which comprises blades 41 carried on the disc 28 by means of spokes 39. The fan 42 supplies air to duct 43 and outlet 44 from which it passes under control of valve 34 to vertical lift nozzles. The spokes 39 are disposed upstream of fan blades 52 so that air-flow thereto is not affected. The flaps 21 are moved to the broken line position when the fan 42 is to be driven at aircraft take-off and landing.