| 摘要 |
1,271,819. Turbine and like blades. GENERAL ELECTRIC CO. Sept, 19. 1969 [Sept. 27, 1968], No.46220/69. Heading F1T. A gas turbine or compressor blade 24 or other member has a common chamber 42 supplying cooling air through passages 51, 53, 54 to effect film cooling of the external surfaces of the member. Since the convex surface 60 is subject to a lower static pressure than the concave surface 58 each passage 54 has a portion 64 of increased crosssectional area adjacent surface 60 to reduce the excessive coolant flow velocity which would otherwise result. The portions 62, 64 of passage 54 may be of circular, elliptical or rectangular cross-sections and the passages may be inclined in a radial direction. The blade 24 also includes chamber 40 inter-connected by passages 48 and supplied with coolant from further passages (46), Fig. 2 (not shown), in the blade root. Passages 50 cool the trailing edge 52.
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