Impingement cooling structure based on array annular protruding target plate

Abstract

The invention relates to an impingement cooling structure based on an array annular protrusion target plate, and belongs to the field of engine turbines. The impingement cooling structure comprises an air inlet cavity, an impingement plate, the impingement target plate, array annular protrusions and a plurality of air film holes, wherein the array annular protrusions and the air film holes are arranged on the impingement target plate. The annular protrusions are located between adjacent impingement holes in the flow direction, and the spanwise distance and the flow direction distance of the array annular protrusions are consistent with those of the impingement holes. The air film holes are located in the downstream positions of the array annular protrusions on the impingement target plate in the flow direction. Cooling air is perpendicularly injected to the impingement target plate through the impingement holes, passes through the annular protrusions after being turned over by 90 degrees on the impingement target plate, flows to the downstream air film holes and flows out of the air film holes for external cooling. The heat exchange area is increased through the array annular protrusions, and therefore the purposes of increasing the heat exchange amount and enhancing the heat exchange effect are achieved. The annular protrusions can conduct secondary disturbance on fluid in the flow direction, and therefore disturbance is enhanced, and heat exchange is enhanced.

Description

technical field [0001] The invention belongs to the field of engine turbines, and in particular relates to an impingement cooling structure based on arrayed annular raised target plates. Background technique [0002] With the continuous development of aero-engine technology, the inlet temperature of the turbine has reached about 2000K, which has far exceeded the melting point of the materials used to manufacture high-temperature components. Necessary cooling of turbine blades, reducing their overall temperature level and local temperature difference, and ensuring no serious deformation or ablation within the required working range are of great significance to their long life and safe operation. Modern aero-engine turbine blades achieve the purpose of cooling the blades through reasonable coordination of internal cooling and external cooling. Among them, impingement cooling is the convective heat transfer form with the strongest heat transfer effect in internal cooling. [...

AI Technical Summary

Problems solved by technology

Therefore, the present invention solves the problems in the prior art that the pit structure disturbs the wall surface and the convex structure is single, resulting in greater pressure loss and the like.

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