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.
Claims2
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 tips of the moving blades and the casing, wherein
- an entrance metal angle at a tip portion of the stationary blade that is the stationary blade at a rear stage of the moving blade having the tip clearance is smaller than an entrance metal angle at other portions than the tip portion of the stationary blade.
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 tips of the moving blades and the casing, wherein
- a front-edge including angle at a tip portion of the stationary blade that is the stationary blade at a rear stage of the moving blade having the tip clearance is larger than a front-edge including angle at other portions than the tip portion of the stationary blade, and also an entrance metal angle at a tip portion of the stationary blade is smaller than an entrance metal angle at other portions than the tip portion of the stationary blade.
Dependencies are inferred from the claim text.