发明名称 SEAL STRUCTURE OF GAS TURBINE
摘要 PROBLEM TO BE SOLVED: To reduce the quantity of combustion gas passing through between a rear edge part inner peripheral surface of an inside shroud and a front edge part outer peripheral surface of a platform by a small quantity of cooling air. SOLUTION: This seal structure has an arm part 41 arranged on the front edge side and/or the rear edge side of the platform 34d, and a recessed place 42 formed so as to surround a tip part of the arm part 41 on the rear edge side and/or the front edge side of the inside shroud 33c. The inner peripheral surface 41a positioned inside in the radial direction of the arm part 41, is formed as an inclined face of gradually diametrically expanding outside in the radial direction over a tip surface 41b from its base end part, and is positioned inside in the radial direction more than the tip surface 41b. A side surface 42d forming the recessed place 42 is formed so as to become substantially parallel to a rotary shaft of a moving blade disk attached with the platform 34d. COPYRIGHT: (C)2007,JPO&INPIT
申请公布号 JP2007247597(A) 申请公布日期 2007.09.27
申请号 JP20060074403 申请日期 2006.03.17
申请人 MITSUBISHI HEAVY IND LTD 发明人 IIDA KOICHIRO
分类号 F01D11/02;F01D11/10;F16J15/40 主分类号 F01D11/02
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