| 摘要 |
1,144,036. Turbine and compressor blades; gas turbine engine cooling. GENERAL ELECTRIC CO. May 2, 1967 [Sept. 14, 1966], No.20227/67. Headings F1G and F1T. A hollow turbine or compressor blade for a gas turbine engine contains an insert or partition 61 dividing the blade interior into central, leading edge, and trailing edge chambers 66, 70 and 73 respectively, the insert 61 being located by radial ribs 64, 65 which also define passages 71, 72. As shown, the blade is a nozzle guide blade to the radially outer end 62 of which cooling air is supplied to flow inwards through chambers 66, 73 and passages 71, 72, a blanking plate 74 preventing direct flow of air to chamber 70. Some of the air in chamber 66 flows through radially spaced orifices 63 to enter chamber 70 before exhausting into the gas stream through orifices 80a, b, c. The remainder of the air in chamber 66 flows through apertures 75 in a plate 60 attached to a shroud band segment 35 to effect cooling of a seal member 39 secured to a flange 37 on the segment. Some of the air in the region 85 adjacent the seal 39 flows outwards through small passages 86 in the shroud segment 35 to effect cooling thereof. The air in chamber 73 flows mainly through passages 82 to cool the blade trailing edge 55, although some may flow through apertures 75. The passages and chambers in the blade may be formed by machining or during casting rather than by an insert. The blade could be a rotor blade. |
