GB637598A - Improvements relating to gas turbine power plant installations - Google Patents

Abstract

637,598. De-icing air intakes. KENT, N. H. Aug. 27, 1947, No. 23770. [Class 4] [Also in Group XXVI] This invention relates to a gas-turbine plant having anti-icing means comprising a combustion chamber separate from the engine combustion equipment which is supplied with air tapped off from the compressor. In one arrangement the separate combustion chamber is located in a conical fairing forming a stationary extension of the compressor rotor and the hot gas is distributed through hollow struts which extend transversely of the air intake passage to the compressor. In another arrangement, the hot gas is distributed through passages in the rotor and stator blades of the compressor. Air, tapped from an intermediate stage of a compressor 11, Fig. 2, is led through ducts 19, an annular manifold 22, hollow struts 23 and a collector space 24 to a combustion chamber 26 located in a conical fairing 18. Fuel from the normal engine supply or from a separate system is supplied to the combustion chamber 26 through an injector 27. The hot gases from the combustion chamber flow through struts 30 to an annular chamber 31 formed in the leading edge of the nacelle 10. Both the struts 30 and chamber 31 are provided with outlets 32 through which the hot gases pass into the air flowing through the compressor intake 16. The air supply valves 20, the current to the sparking plug 28 and the supply of fuel to the injector 27 may be arranged for simultaneous operation. In a modification, the air is tapped from the air passages in the combustion chambers of the engine. In multi-engined aircraft each engine may be provided with a separate combustion chamber, the air and fuel supplies to which may be interconnected so that hot air may be supplied to an engine even though it is not running. In another modification, Figs. 4A and 4B, air is taken from the stator of a high pressure stage of the compressor 11 through ports 73, slots 71, radial passages formed between plates 70, ports 74, collector manifold 75 and conduit 76 to the inlet 80 of the separate sheet metal combustion chamber 81. The slots 71 are formed in rings 67b which space the thin disc-like members 63 carrying the blades 64. The hot gases leaving the combustion chamber 81 pass through ducts 85 to hollow struts 90 which discharge into a manifold on the outside of the compressor casing connected to a duct 93 at the inlet edge of the struts 90 and hollow stator blades 97. The hot gas from the duct 93 passes into the airstream through ports 94. The hot gas from the hollow stator blades 97 passes into hollow disc structures 65 and then into hollow rotor blades 66 which it leaves at the tips. A pipe 102 connecting the structures 65 is formed between two nested sleeves 103, the outer of which has ports communicating with passages formed between radial flanges 104 formed on a two-part spacer ring 67a to supply hot gas through ports 105 to the stator blades 69. Specification 618,224 is referred to.