Baffling cooling device and application

Abstract

The invention discloses a baffling cooling device and application, and belongs to the field of aero-engines. Comprising a hot side flat plate, a baffle plate, an outer side cover plate, hollow turbulent flow columns, a baffle front plate and a baffle tail plate, a cold air channel is formed between the baffle plate and the outer side cover plate, and the hot side flat plate is located on one side of a high-temperature fuel gas channel; a plurality of hollow turbulent flow columns are arranged between the hot side flat plate and the baffle plate to form a middle channel containing the hollow turbulent flow columns; the baffle front plate is packaged at the front ends of the baffle plate and the outer side cover plate, and the baffle tail plate is packaged at the tail ends of the hot side flat plate and the outer side cover plate to form a semi-closed space; cooling air enters the middle channel to form cooling air flow, passes through the hollow turbulent flow columns and then is folded back at the baffling tail plate to form reverse baffling to enter the cold air channel, and finally flows into the high-temperature fuel gas channel through hollow holes in the hollow turbulent flow columns, and a cooling air film attached to the wall face is formed on the inner wall of the hot side flat plate. Due to baffling of cold air, the temperature of the whole cooling structure is uniform, and internal thermal stress is reduced.

Description

technical field [0001] The invention belongs to the field of aero-engines, and in particular relates to a baffle cooling device and its application. Background technique [0002] When military fighters take off at short distances and maneuver quickly, they often obtain additional thrust through afterburner beyond the maximum throttle opening of the engine. Due to the limited space in the afterburner, the still burning gas acts on the nozzle wall of the converging section of the engine in the form of oblique impact, which is likely to cause gas backflow. Studies have shown that the gas temperature of the tail nozzle will be as high as 2000K or more at this time. In addition, the pressure gradient from the inlet to the outlet of the engine nozzle is large, the gas pressure in the expansion section is low, and the cooling gas usually flows out of the nozzle heat shield at high speed. It is easy to aggravate the occurrence of the phenomenon of inversion in the convergence sect...

AI Technical Summary

Problems solved by technology

Although the existing double-wall cooling structure can achieve a better heat transfer effect, the internal flow resistance of the double-wall is relatively large, which is greatly affected by the change of the total pressure ratio of the primary and secondary flows, and it is not easy to flow out under the condition of a small pressure ratio.

At the same time, due to the large pressure gradient between the upstream and downstream of the nozzle, the impact gas film double-wall structure is used to easily form a large cross flow in the impact chamber, reducing the cooling efficiency of impact cooling

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