Blade structure in a gas turbine
AssigneeMitsubishi Heavy Industries, Ltd.
InventorsEisaku Ito, Eiji Akita
Life of this patent
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Abstract
In the blade structure in a gas turbine, front-edge including 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 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.
Claims3
A blade structure in a gas turbine, comprising:
- stationary blades arrayed in a circle on a casing;
- moving blades arrayed in a circle on a rotor, wherein a clearance is provided between chips of the moving blades and the casing, wherein
- a chord length at a chip portion of the moving blade having the chip clearance is larger than a minimum chord length at other portions than the chip portion of the moving blade.
Dependencies are inferred from the claim text.