| 摘要 |
1,256,040. Turbine blades. GENERAL MOTORS CORP. May 14, 1970 [Aug. 25, 1969], No. 23463/70. Heading F1T. A hollow turbine blade comprising layers of sheet metal 12 to 15 bonded together has spanwise rows of staggered cooling air holes at the leading edge 17. The outside layer 12 has three spanwise rows of holes 29 which overlie the inner three rows of five rows of larger holes 30 in the adjacent layer 13. The holes 30 partially overlie holes 31 in layer 14 and the latter holes similarly partially overlie holes 32 in the inside layer 15. The three innermost rows of holes 32 may have a diamond shape prior to folding of the layers into the rounded leading edge configuration so that after folding these holes are not completely constricted. The layers 12, 13 are spaced apart by bosses (36), Fig. 5 (not shown), on layer 13 and the gap formed thereby is supplied with cooling air through grooves 35 leading from the outermost rows of holes 30. Additional air may be supplied to this gap through further holes (38) in layer 13, the air exhausting through holes in layer 12. The holes may be formed by photoetching and the various layers joined together by diffusion bonding. The cooling air is supplied to the blade interior through a passage 23 in a root stalk 7. The tip of the blade is closed by a cast metal plug (25), Fig.1 (not shown), having a sealing lip (26). |
