GB1027530A - Gas turbine cycle improvement - Google Patents

Abstract

1,027,530. Gas turbine engines. V. DAVIDOVIC. March 2, 1964, No. 8716/64. Heading F1G. The invention relates to a gas turbine engine which comprises a liquid coolant or fuel container disposed between the compressor and flame tube of the engine, and means for causing air from the compressor to flow adjacent the container whereby the air is cooled, the air being then caused to flow adjacent the turbine casing which is thereby cooled. The engine shown comprises a centrifugal air compressor 1, combustion equipment B, a first turbine 6 which is connected to drive the compressor through shaft 2 and a second turbine 15 which is arranged to drive a useful load through shaft 17. Air from the compressor passes into a chamber C from which it passes into the single tubular flame tube 23 at the upstream end E thereof. A portion of air from the compressor passes through the hollow turbine inlet nozzle guide blades 8 and across the turbine casing before entering the flame tube. Secondary air enters the flame tube through the inlets I in the wall thereof. The combustion gases discharge from the flame tube through an outlet portion which terminates in an annular duct 24 across which the turbine inlet nozzle guide blades 8 extend. The gases act first on the blades 7 of the compressor drive turbine and are then directed by stator blades 9 on to the rotor blades 10 of the power turbine 15, the gases finally discharging through outlet duct F which may be in the form of a jet propulsion nozzle. A space A defined between the inner wall 12 of the plenum chamber C and the sleeve 11 surrounding the turbine-compressor shaft 2 is adapted to contain liquid coolant or fuel. The wall 24 of the flame tube discharge duct is formed with a plurality of small holes K, Fig. 6 (not shown) so as to maintain uniformity of pressures within the plenum chamber C and the interior of the flame tube. The turbine casing is provided with fins on its outer surface, Fig. 3 (not shown) to assist heat transfer. Gearing 16, 16<SP>1</SP> and electro-magnetic clutch 19 are disposed between the turbines 6 and 15 whereby the compressor drive turbine 6 may be connected to drive the output shaft 17. The turbine exhaust gases may be utilised to preheat the air being supplied to the flame tube B, Fig. 4 (not shown). The air preheater L receives turbine exhaust gases through inlet F<SP>1</SP> and discharges them through outlet O. Air from the plenum chamber C enters the preheater through inlets M, 32, 30 and the heated air passes into the flame tube through passages 29 and N. The gases may be reheated between the turbines 6 and 15 Fig. 5, not shown, wherein oil from the space A flows radially outwardly through the turbine motor 6 and blades 7<SP>1</SP> and then discharges axially through outlets 34 in the blades into the interstage ducting 18.