Blade structure in a gas turbine

Details Blade structure in a gas turbine Blade structure in a gas turbine

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/14 (2006.01) F01D 9/02 (2006.01) F01D 11/10 (2006.01)

Patent

CA 2506293

In the blade structure in a gas turbine, inlet included angles are made large. As a result, a curve of a relative relationship between incidence angles ic1 and is1 and pressure loss becomes mild. Entrance metal angles, which are formed by an axial direction of the gas turbine and a tangential direction to a camber line at the front edge of the stationary blade, are made small. As a result, it becomes possible to make the incidence angles small. Chord length of a tip portion of a moving blade is made large. As a result, it becomes possible to make small the deceleration on a rear surface of the tip portion of the moving blade. Accordingly, it becomes possible to make the pressure loss small, and therefore, it becomes possible to improve the turbine efficiency.

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