A grid slot film cooling structure with spool type spoiler column and double rounded outlets

Abstract

The invention discloses a grid seam air film cooling structure with a spool-type spoiler column and double rounded outlets, which is composed of a lip plate, a spool-type spoiler column, and a bottom plate. The lip plate and the bottom plate form a two-dimensional seam structure. In the two-dimensional seam structure, the spool-type spoiler column is used to guide the flow and strengthen the structure; the spool-type spoiler column is arranged in a straight row or fork row, and the exit of the grid seam is a double-rounded structure, and the outside of the lip plate and the bottom plate The profile surface is even, reducing the impact on the aerodynamic performance of the blade. The spool-type spoiler column eliminates the low-speed reflux vortex behind the turbulent column, effectively improving the heat transfer intensity inside the grid seam; the spool-type spoiler column greatly increases the heat exchange area in the grid seam, and the Enhanced heat transfer; effectively reduce the aerodynamic loss of the cold air in the seam, and enhance the flow direction coverage of the cold air. The double-rounded structure of the outlet of the grid seam prevents the cold air from being directly injected into the mainstream after leaving the grid seam, and effectively adheres to the area near the wall surface, enhancing the adhesion ability of the air film behind the seam.

Description

technical field [0001] The invention relates to the technical field of cooling the turbine blades of gas turbines, in particular to a grid seam gas film cooling structure with a spool type spoiler column and double rounded outlets. Background technique [0002] With the improvement of gas turbine performance, the turbine inlet temperature continues to increase, and the inlet temperature of some advanced engines has reached more than 2000K. Therefore, effective cooling measures must be used to protect the turbine blades to avoid high temperature corrosion and damage to the blades. . Film cooling is one of the typical cooling methods used on blades. Air film cooling is to inject a low-temperature airflow along the tangent or at a certain angle near the wall to isolate the high-temperature gas from the wall and realize the cooling protection effect on the heated wall. [0003] Cylindrical air film holes are the earliest air film hole type. A large number of scholars at home a...

AI Technical Summary

Problems solved by technology

In 2003, C. Yuen et al. (Filmcooling characteristics of rows of round holes at various streamwise angles in a crossflow: Part I. Effectiveness. International Journal of Heat & Mass Transfer, 2003, 46(2), 221-235.) found in subsequent studies The spanwise coverage of the cylindrical hole jet is weak, and the jet gas is raised so that the near wall cannot form an effective gas film coverage

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