High-load static blade of gas turbine

Abstract

The invention belongs to the technical field of gas turbines, and discloses a high-load stationary blade of a gas turbine, which comprises a blade profile, and the blade profile comprises a blade profile front edge, a blade profile middle edge and a blade profile tail edge; the blade type front edge comprises a front edge partial pressure surface arc, a front edge middle arc and a front edge partial suction surface arc; the blade profile middle edge comprises a suction surface third-order Bezier curve and a pressure surface third-order Bezier curve; the blade-shaped trailing edge comprises a first trailing edge transition arc, a trailing edge fin straight line and a second trailing edge transition arc; the front edge partial pressure surface circular arc, the front edge middle circular arc, the front edge partial suction surface circular arc, the suction surface third-order Bezier curve, the first trailing edge transition circular arc, the trailing edge fin straight line, the trailing edge transition circular arc and the pressure surface third-order Bezier curve are sequentially connected end to end, and the tangent slopes of the joints are equal. The blade profile is reasonably designed and optimized, so that high aerodynamic efficiency is still kept under the condition of a small number of blades, and the production cost and cold air consumption of the looped blades are effectively reduced.

Description

technical field [0001] The invention belongs to the technical field of gas turbines, and in particular relates to a high-efficiency, high-load stationary vane used for the first stage of a gas turbine turbine. Background technique [0002] With the continuous increase of the inlet gas temperature of the gas turbine turbine, the thermal load environment faced by the high temperature components of the turbine is getting worse. The high-temperature and high-pressure gas at the outlet of the combustion chamber consumes a large amount of cooling air. The amount of cold air consumed by the design of the cooling system is positively correlated with the surface area of ​​the blades, so the design with fewer blades can reduce the consumption of cold air. [0003] But on the other hand, the reduction in the number of blades will increase the aerodynamic load borne by a single blade, and high aerodynamic load will increase the overall flow velocity in the flow channel and increase the...

AI Technical Summary

Problems solved by technology

The technical solution of this application is mainly aimed at optimizing the aerodynamic performance of the stator blades, but this technical solution does not reduce the number of blades on the premise of ensuring aerodynamic efficiency. Therefore, if it is applied to a gas turbine turbine, it is difficult to solve the problem of large cooling air consumption

[0005] In order to reduce cooling air consumption and solve the problem of low aerodynamic efficiency caused by high aerodynamic load in the design of fewer blades, this application provides a high-load stationary blade of a gas turbine. Under the premise of efficiency, reduce the number of blades and increase the aerodynamic load of a single blade, thereby reducing the consumption of single-stage cooling gas; and optimize the curvature distribution of the leading edge to rationally organize the end wall flow and weaken the cross flow of the horseshoe vortex at the leading edge , which ultimately guarantees its good aerodynamic efficiency

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