GB881816A - Improved gas turbine engine - Google Patents

Abstract

881,816. Gas-turbine plant. ROLLSROYCE Ltd. June 28, 1960 [July 3, 1959], No. 23033/59. Class 110 (3). A gas-turbine has a cooling air passage arranged around the stator vanes of a turbine of the engine, an annular manifold arranged about the cooling air passage and adapted to be supplied with gas under pressure and a plurality of conduits for directing the gas on to the rotor blades of the turbine to start it, the conduits extending in spaced relationship across the cooling air passage. The casing of a by-pass gas turbine jet-propulsion engine is provided with an annular manifold 20 disposed within the by-pass passage and supplied with pressurized gas. An annular passage 21 having a common wall with the manifold 20 is supplied with cooling air from the compressor to cool the inlet guide vanes 23 of the low-pressure turbine 12 by passing between struts 22 and through apertures 25 to a chamber 26. A plurality of spaced apart tubes 27 extend from the manifold 20 across the passage 21 and each terminates in a nozzle 28 which directs the pressurized gas on to the rotor blades 29 of the turbine. The nozzles 28 are cast integrally with the platforms provided on the outer ends of the stator blades 23. The turbine includes a high-pressure compressor driven by a high-pressure turbine and a low-pressure compressor driven by a low-pressure turbine.