[12] Patent
[11] Patent No.:GC0007595  
[45] Date of Publishing the Grant of the Patent: 30/Apr /2018                48/2018  
Number of the Decision to Grant the Patent:2018/126080
Date of the Decision to Grant the Patent:16/Apr/2018

[21] Application No.:GC 2012-22954

[22] Filing Date:3/12/2012

[30] Priority:

[33] State [32] Priority date [31] Priority No.

[72] Inventors:1- Ichiro Miyoshi،2- Shinichi Higuchi،3- Masami Noda

[73] Owner: Mitsubishi Hitachi Power Systems, Ltd, Minatomiral 3-chome, Nishi-ku, 3-1,220-8401, yokohama, Japan

[74] Agent: Saud M. A. Shawwaf Law Office




F01D 5/18, 5/20

[56] Cited Documents:

-JP 2002-371802 A. (Mitsubishi Heavy Industries,Ltd.) 26 December 2002
-JP 10-252405 A (Mitsubishi Heavy Industries,Ltd.) 22 September 1998
-JP 10-82302 A (Toshiba Corp.) 31 March 1998
-JP 11-148308 A (Asea Brown Boveri AG.) 02 June 1999
Examiner: Eng. Mohammad W. AlHoshan

[57] Abstract: A turbine blade is provided that can reduce a total pressure loss at a blade cross-section on a tip side of the turbine rotor blade and suppress degradation in performance even if cooling air mixes in toward the rotor blade. The turbine rotor blade mounted to a rotor to form a turbine blade row rotating in a stationary member includes a platform forming a gas passage through which a mainstream gas flows and an airfoil extending from a gas passage plane in a radial direction vertical to the rotational axis of the rotor, the gas passage plane being a plane of the platform and forming the gas passage. A clearance between the tip-side end face which is a leading end-side end face of the airfoil and the stationary member facing the tip-side end face is defined so as to be smaller on the downstream side in the flow direction of the mainstream gas than on the upstream side.
No. of claims: 1     No. of figures: 15


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