A Non-Uniform Horizontal and Longitudinal Slot Turbine Outer Ring Structure

Abstract

A non-uniform horizontal and vertical groove turbine outer ring structure, including an impact body, the impact body is composed of an inner shell, an outer shell and a connecting body, a number of impact holes are arranged on the outer shell, and a number of impact holes are arranged on the inner wall of the inner shell Rib grooves, the rib grooves include circumferential rib grooves and axial rib grooves, the inner wall of the inner shell at the inlet of the cascade is provided with circumferential rib grooves along the circumferential direction, and several circumferential rib grooves are unevenly or evenly distributed On the inner wall of the inner casing, the inner wall of the inner casing at the outlet of the cascade is provided with axial rib grooves in the axial direction, and several axial rib grooves are evenly distributed on the inner wall of the inner casing, and the inner casing on the inner casing A number of air film holes are opened, and the outer shell and the inner shell are fixedly installed through the connecting body. When the gas passes through the rib groove, the gas velocity in the groove is obviously reduced because the rib groove hinders the gas. Compared with the turbine outer ring without rib groove structure, after adding the horizontal and vertical groove structure, the gap leakage flow is reduced by 1-3%.

Description

technical field [0001] The invention relates to a gas turbine turbine outer ring structure, in particular to a gas turbine outer ring structure with non-uniform horizontal and vertical grooves. Background technique [0002] The gas turbine rotates the rotor blades through the impact of gas on the rotor blades to output work, and the outer ring structure of the turbine separates the rotating rotor blades from the stationary parts. In the cascade passage, the gas temperature is already higher than the temperature resistance limit of the turbine components, which must be effectively cooled. The outer ring is usually cooled by film cooling, which separates the high-temperature gas in the cascade channel from the outer wall. After air film cooling is adopted, the leakage fluid in the tip clearance is mixed with the mainstream fluid in the channel, and the flow is very complicated. On the one hand, seepage will form in the leading edge area, resulting in energy loss of the mainst...

AI Technical Summary

Problems solved by technology

After air film cooling is adopted, the leakage fluid in the tip clearance is mixed with the mainstream fluid in the channel, and the flow is very complicated. On the one hand, seepage will form in the leading edge area, resulting in energy loss of the mainstream fluid. On the other hand, the blade pressure surface and suction surface The pressure difference will form a gap leakage flow, thereby disturbing the normal and stable flow of the main flow inside the cascade

Due to the smooth surface of the outer ring, the pressure between cascade stages is high, and the gas flow speed is fast, when the gas flows from the cascade inlet to the cascade outlet, a large amount of gas leakage will be caused, resulting in a decrease in the use efficiency of gas and the film cooling efficiency of the outer ring

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