High temperature nozzle wall array type enhanced heat transfer cooling structure of variable Mach number type linear wind tunnel

Abstract

A variable Mach number molded line wind tunnel high temperature nozzle wall array type enhanced heat exchange cooling structure comprises a cooling plate. An outer side of the cooling plate is an outer wall surface which is in contact with normal temperature air. An inner side of the cooling plate is a near wall surface which is in contact with a high-speed air flow. Two ends of the cooling plateare side walls of a supporting structure, and the outer wall surface, the near wall surface and the side walls form a cooling channel. The cooling channel is divided into a short rib area, a turbulentflow column area and a long rib area. The short rib area is formed by a plurality of short ribs arranged in an array or staggered arrangement. An inlet of the short rib area is a cooling medium inletend. An outlet of the short rib area is connected to an inlet edge of the turbulent flow column area. The turbulent flow column area is formed by multiple turbulent flow columns arranged in the arrayor staggered arrangement, an outlet edge of the turbulent flow column area is connected with an inlet of the long rib area. The long rib area is formed by multiple long ribs arranged in the array orstaggered arrangement, and the outlet of the long rib area is a cooling medium outlet end. In the invention, cooling is uniform and matrix transformation can be performed according to a cooling requirement.

Description

technical field [0001] The invention belongs to the technical field of high-temperature nozzles of variable Mach number-shaped line wind tunnels, and particularly relates to a wall array type enhanced heat exchange cooling structure of variable Mach number-shaped line wind tunnel high-temperature nozzles. Background technique [0002] The high-temperature nozzle of the variable Mach number line wind tunnel is mainly used in the ground experiment research of simulating the high-speed flight of aerospace vehicles. Sensitive to temperature generated by air movement. The high-temperature nozzle of the variable Mach number line wind tunnel can convert the subsonic airflow into the supersonic airflow during the flight of simulated high-speed aircraft. However, due to the high inlet temperature, it is restricted by the heat resistance of current materials. The near wall and outer wall of the high temperature nozzle are affected by high temperature, resulting in thermal deformation...

AI Technical Summary

Problems solved by technology

The high-temperature nozzle of the variable Mach number line wind tunnel can convert the subsonic airflow into the supersonic airflow during the flight of simulated high-speed aircraft. However, due to the high inlet temperature, it is restricted by the heat resistance of current materials. The near wall and outer wall of the high temperature nozzle are affected by high temperature, resulting in thermal deformation and rapid aging, so it is very necessary to uniformly cool the near wall and outer wall of the high temperature nozzle in the variable Mach number line wind tunnel

[0003] At present, the conventional cooling methods for the high-temperature nozzle of the variable Mach number profile wind tunnel are: first, spray water on the outer wall. Since the profile is a curve, this method will lead to uneven cooling and local expansion.

Second, the cooling water is passed into the interlayer between the outer wall and the near wall for cooling, and the water-cooling channel is divided into multiple channels for cooling. The temperature distribution of the high-temperature nozzle in the wind tunnel is different along the axial direction. This method is due to the wide and long interlayer of the nozzle. The method will lead to cold spots, and the local high temperature area still cannot meet the cooling requirements; at the same time, the high temperature nozzle of the variable Mach number type wind tunnel is an integrated structure, and the common cooling structure cannot be adjusted after setting, which is very important for simulating different working conditions. During the flight of the aircraft, with the change of the temperature distribution of the near wall and the outer wall of the high-temperature nozzle of the variable Mach number type wind tunnel, the common single-channel and multi-channel water-cooling structures can no longer meet the cooling requirements of the high-temperature area, resulting in uneven wall temperature. Deformation occurs and the corresponding working conditions cannot be simulated

Images