GB980572A - Improvements relating to cooled blades, e.g. for a gas turbine engine - Google Patents

Abstract

980,572. Gas turbine blades. ROLLSROYCE Ltd. Sept. 2, 1963, No. 34649/63. Heading FIT. A hollow aerofoil shaped gas turbine blade has an external wall, a cooling fluid passage extending internally of and immediately alongside the external wall and having at any cross section a width which is less than the thickness of the external wall at that cross section, fluid inlet means through which a cooling fluid may be supplied to the passage at a region which is adjacent to one side of the blade and is spaced from the leading edge thereof, and fluid outlet means through which the cooling fluid may be withdrawn from the passage, the passage being formed to cause the cooling fluid supplied to the region to flow therefrom and alongside the said one side to adjacent the leading edge and thereafter to flow in substantially the opposite direction from adjacent the leading edge and alongside the other side of the blade so as to pass to the fluid outlet means. A gas turbine nozzle guide blade 14 has an external wall 20 and an internal wall 21 dividing the blade into leading and trailing edge compartments 23, 24 respectively. A tube 25 extends radially through compartment 23 and is supplied at both ends with cooling air from the engine compressor. The air enters passage 30 between the tube 25 and the blade side 18 through slots 33 in the tube 25 and is deflected by a perforated baffle 32 to flow towards the leading edge 16 of the blade 14. The air then flows along passage 30 adjacent side 19, through holes 22 in the dividing wall 21 and into compartment 24 from which it leaves through holes 34 to cool the trailing edge 17. At any cross-section the width of the passage 30 is less than the thickness of the wall 20.