GB1282142A - Improvements in or relating to gas turbine engines - Google Patents

Abstract

1282142 Gas turbine plant - cooling blades ROLLS ROYCE Ltd 25 March 1970 [29 March 1969] 16599/69 Headings F1G and F1T The invention relates to a method of cooling turbine blades of a gas turbine engine in which high pressure cooling air is divided into two flows, one flow being supplied to a passage located adjacent the leading edge of one or more blades of the turbine and the other flow being supplied to a passage located rearwardly of the first passage. In the engine shown the turbine rotor 18 has blades 20 mounted at the periphery thereof, each blade having a cooling air passage 26 disposed adjacent the leading edge and a series of passages 28 disposed rearwardly of the passage 26. The engine comprises stator structure 50, 54 which defines a chamber 62 to which air under pressure tapped from the engine compressor is supplied through passage 60. One flow of air from chamber 62 passes through passages 52 in the member 50 and then radially outwardly through an annular passage 40 defined between the disc 18 and a ring member 30 secured thereto by bolts 32, the air then flowing radially outwardly through passages 26 formed in the blades 20 adjacent the leading edges thereof. A second flow of air from chamber 62 passes through passages 58 defined between the members 50, 54 into the chamber 44, this air then flowing radially outwardly through passages 28 formed in the blades rearwardly of the passages 26. The air discharges through the blade tips. Seal means 33, 34 are provided between the ring member 30 and member 50, also at 46, 48 adjacent the shaft 22. In Fig.3, the ring member 30 is dispensed with and air flows from the passages 52 through bores 70 in the rotor disc 18 to the blade passages 26. The blade passages 26, 76 shown in Fig. 5 communicate with the leading and trailing edges of the blade through ducts 27, 78 respectively. Swirl devices may be disposed in the air passages 52 and 58.