A hypersonic wind tunnel film cooling experimental system and experimental method

Abstract

The invention provides a hypersonic wind tunnel film cooling experiment system and an experiment method. The system comprises a two-dimensional cooling model (1), a film plenum chamber (2), a film spraying pipe (3), an air charging channel (4), a cooling widow (5), a particle broadcaster (6) and a cooling medium (7). The front edge of the two-dimensional cooling model (1) is aligned to the lower surface of the outlet of a wind tunnel spraying pipe. The film plenum chamber (2) is installed a surface A, through which the free incoming flow passes, of the two-dimensional cooling model (1), and a reverse step will not be formed after the film plenum chamber is installed. The film spraying pipe (3) is installed on the film plenum chamber (2) and the direction of the central line of a spraying opening is parallel to the surface A. The lower surface of the spraying opening of the film spraying pipe (3) is parallel to the upper surface of the cooling window (5), and reverse step will not be formed therebetween. In an experiment process, the cooling medium (7) enters the film plenum chamber (2) via the air charging channel (4) through the particle broadcaster (6), and then is sprayed out by the film spraying pipe (3), and a cooling shear mixing layer film is formed on the surface of the cooling window (5).

Description

technical field [0001] The invention relates to a hypersonic wind tunnel film cooling experiment technology, in particular to a film cooling efficiency and film flow field structure measurement experiment method. Background technique [0002] The early research on film cooling flow focused on the thermal protection of gas turbine blades, forming the basic concept of cooling efficiency, and the basic understanding of the cooling efficiency of cold jet air blowing ratio, momentum ratio, incident angle, and turbulence intensity. Since the 1960s, people began to study the use of film cooling flow for the blade protection of gas turbines, and improved the working life of components or the working efficiency of gas turbines by distributing holes on the surface of the blades and forming cold flow injection. Because the flow involves two temperature references, the temperature of the mainstream and the temperature of the cold jet flow, people put forward the concept of cooling effic...

AI Technical Summary

Problems solved by technology

In the fully developed region, the boundary layer flow of the cold jet stream gradually begins to dominate, and due to the development of the turbulent boundary layer, the temperature of the adiabatic wall surface increases rapidly, and the cooling efficiency of the cold jet stream decreases rapidly

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