GB680581A - Means for cooling the blades of gas turbine engines - Google Patents

Abstract

680,581. Gas turbine plant. OESTRICH, H. May 8, 1950 [May 9, 1949], No. 11368/50. Class 110 (iii) . In a gas turbine having internally air cooled blades, a liquid in an atomised form is injected into the cooling air. The liquid may be fuel or water or a mixture of these two liquids. A gas' turbine having hollow stator blades 16, Fig. 1, and rotor blades 4 has liquid injected into the cooling air by means of pipes 26 and 12. The stator blades have baffles 17 formed with projecting ribs 18, 19 engaging the inner surtace ot the blade to maintain the cooling air near the surface of the blade. The air leaves the blade through passages 23 formed in the trailing edge. The rotor blades also have a baffle 5 for the same purpose. The cooling air is supplied to the blade from a chamber 8 through orifices 10 and 11 formed in the root of the blade. The liquid from the tube 12 flows radially outwards over the cover plate 9 into an annular recess 13 from which it overflows over a sill 14 into the air stream. It is stated that this atomises the liquid. The coolant may leave the blade radially at the tip or through outlets 15 in the trailing edge. In a modification the recess 13 is formed integral with the rotor and holes are provided at the base of the recess to allow tha liquid to pass through. In a further modification, the recess is formed as an integral part of the cover plate 9. When the liquid is fuel it is burnt when it enters the motive fluid stream. This arrangement may be used to reheat the working fluid after the turbine. The baffles 5 may be provided with a cone member 30 having a reduced portion 31 which serves as a baffle for assisting the atomisation of the fuel. Specification 622,411 is referred to.