发明名称 TURBINE GUIDE BLADE COOLING.
摘要 Partitions 8, 11 extending the length of the blade divide the cavity bounded by the outer wall 3 into first, second and third ducts 14, 15, 16. The leading edge area 2 is cooled by air flowing through radial passages 17 in this area and then through the first duct 14. The extrudes face area 5 is cooled by air flowing through radial passages 18 in this area and then through the second duct 15. The intrados face area 7 is cooled by air flowing through the third duct 16. The ducts 14, 15, 16 communicate with the outside of the blade 1 through slits 21, 22, 23 respectively. Cooling fins 20 may be provided in the passages 17. <IMAGE>
申请公布号 GB2257479(A) 申请公布日期 1993.01.13
申请号 GB19920012466 申请日期 1992.06.12
申请人 * SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS DE AVIATION S.N.E.C.M.A. 发明人 MISCHAEL FRANCOIS LOUIS * DERRIEN
分类号 F01D5/18 主分类号 F01D5/18
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