GB759037A - Improvements in or relating to gas turbine engines - Google Patents

Abstract

759,037. Gas turbine engines. ROLLSROYCE. Ltd. Aug. 20, 1954 [Sept. 7, 1953], No. 24738/53. Class 110(3) [Also in Group XXXIV] In a gas turbine engine provided with means for injecting a liquid into the cooling air flow, the injection is initiated when the temperature of the cooling air rises above the vaporizing temperature of the liquid. In the jet engine of Fig. 2 air from an intermediate stage of the compressor 10 is supplied to the interior of the hollow shaft 19 via ports in the latter and in the compressor rotor. This air flows through ports 30 in the shaft to a chamber 40 whence it is directed over the bearing housing 26 and passes to the atmosphere through the hollow inlet varies 33 of turbine 13. Air from the combustion chamber jacket 36 is fed through conduits 34 to a chamber 39 and after flowing over the bearing housing 27 flows over one side of the turbine disc 23 and enters the working fluid stream. Temperature-sensitive devices 50 are adapted to operate the control switches 49 of motors 46 driving water pumps 43 adapted to feed atomizing nozzles 41. The devices 50 are also adapted to close the valves 54 in the by-pass connections 59 to increase the water supply to the nozzles. In Fig. 3 the lubrication system for the bearings comprises a storage tank 63, supply and scavenge pumps 65, 73 and a coil 67 located in a cooling air duct. Operation of the motor 46 driving the water pump 58 is controlled by the heat-sensitive device 50. The pump feeds the atomizing nozzle 76. The device 50 also controls a valve in the by-pass connection 59. The water pumps may be engine driven. The invention may be applied to marine engines.