Non-uniform transverse longitudinal groove turbine outer ring structure

Abstract

The invention discloses a non-uniform transverse longitudinal groove turbine outer ring structure. The structure comprises an impact body, wherein the impact body is composed of an inner shell body, an outer shell body and a connecting body, a plurality of impact holes are formed in the outer shell body, rib grooves are formed in the inner wall of the inner shell body, the rib grooves comprise circumferential rib grooves and axial rib grooves, the circumferential rib grooves are formed in the inner wall of the inner shell body along the circumferential direction at an inlet of a blade grid, the plurality of circumferential rib grooves are not uniformly or uniformly distributed on the inner wall of the inner shell body, the axial rib grooves are formed in the inner wall of the inner shell body in the axial direction at an outlet of the blade grid, the plurality of axial rib grooves are uniformly distributed on the inner wall of the inner shell body, a plurality of air film holes are formed in the inner shell body, and the outer shell body and the inner shell body are fixedly arranged through the connecting body. When the fuel gas passes through the rib grooves, due to the obstruction effect of the rib grooves on the fuel gas, the gas speed in the grooves is obviously reduced, compared with a turbine outer ring without a rib groove structure, after the transverse longitudinal groove structure is added, 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...

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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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