Manufacturing method of air outlet edge of stationary blade of hollow blade of gas turbine

Abstract

The invention relates to the technical field of machining of stationary blades of hollow blades of gas turbines, and particularly discloses a manufacturing method of an air outlet edge of the stationary blade of the hollow blade of the gas turbine. The method specifically comprises the following steps of machining a mold core, wherein the mold core comprises a mold core body provided with a mold core front edge and a mold core trailing edge, the distance between the mold core trailing edge and a blade trailing edge cold air outlet area is A, and A is greater than or equal to 0.5 mm and is lessthan or equal to 1.5 mm; conducting blade precision casting; machining a trailing edge air outlet edge cooling structure; on the basis that a blade profile of the hollow stationary blade is not changed, communicating a trailing edge cold air outlet area with a cavity in the blade through a spark erosion drilling machine, and machining a complete trailing edge air outlet edge cooling structure; and completing the machining. According to the method, the structure of the trailing edge of the mold core is adjusted, a pure precision casting method is replaced with a method of combining an electricspark machining technology and precision casting to manufacture the blade, on the premise that the completeness of a trailing edge cooling structure is effectively guaranteed, the technological process of manufacturing the hollow stationary blade is greatly optimized, and the percent of pass of blade manufacturing is increased.

Description

technical field [0001] The invention relates to the technical field of gas turbine hollow blade stationary vane processing, in particular to a method for manufacturing a gas outlet edge of a gas turbine hollow blade stationary vane. Background technique [0002] The gas turbine stator is the core component of the gas turbine. It converts the internal energy of the working medium into kinetic energy, and then impacts the rotor to drive the rotor to rotate and output shaft work. Turbine vanes are subjected to high-temperature, high-speed gas impact, and the working environment is extremely harsh. In order to ensure the safe operation of the blades and improve the efficiency of the gas turbine, it is necessary to effectively cool the turbine vanes. The cooling methods of turbine blades mainly include internal cooling and external cooling, and internal cooling is to design turbine blades as hollow blades with complex internal structures. Such blades are difficult to manufacture ...

AI Technical Summary

Problems solved by technology

In order to ensure the integrity of the cooling structure of the blade trailing edge, it is necessary to make the trailing edge of the core thin and long, but such a structure makes the core extremely prone to cracks, defects or even breaks during the production and later use. This will greatly increase the difficulty of blade manufacturing and reduce the qualified rate of blade manufacturing

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