发明名称 COMMUNICATION PASSAGE OF COOLING PASSAGE OF ROTOR BLADE OF GAS TURBINE
摘要 PROBLEM TO BE SOLVED: To suppress to a minimum or to completely eliminate the stress concentration by forming a crossing passage of elliptical shape between external and internal flow passages adjacent to each other in the radial direction. SOLUTION: A closed cooling circuit inside a rotor blade comprises a plurality of radial passages in a meandering array. A refrigerant flowing into the rotor blade through an entrance passage 28 flows firstly outwardly in the radial direction along a trailing edge of the rotor blade through upward passages 30, 32 parallel to each other and separated from each other by an internal rib 33, and then, after changing the flowing direction, flows inwardly in the radial direction through a passage 34, and continuously flows through a plurality of meandering passages 36, 38, 40, 42, 44, 46 adjacent to each other, and finally flows out of the rotor blade through a passage 48. An opening 54 as a refrigerant crossing passage provided in internal ribs 33, 50 between radial refrigerant passages adjacent to each other of the closed circuit suppresses to a minimum the stress concentration at the rotor blade of elliptical shape, and are provided in a deviated manner in the radial direction between the ribs adjacent to each other so that the sectional area is not considerably reduced even at any portions inside the rotor blades.
申请公布号 JP2000265802(A) 申请公布日期 2000.09.26
申请号 JP19990332317 申请日期 1999.11.24
申请人 GENERAL ELECTRIC CO <GE> 发明人 WILLETT FRED THOMAS;LEWIS DOYLE C
分类号 F02C7/12;F01D5/18;F01D9/02;(IPC1-7):F01D5/18 主分类号 F02C7/12
代理机构 代理人
主权项
地址