Regeneration cooling channel with truss structure

Abstract

The invention discloses a regeneration cooling channel with a truss structure. The regeneration cooling channel comprises an outer wall, the truss structure and a cooling channel body. A cavity is formed between the outer wall and the cooling channel body, and the truss structure is arranged in the cavity. The truss structure comprises a hollow frame structure formed by building a plurality of supporting rods. The truss structure comprises a plurality of base units which are connected with one another, and each base unit is a supporting body built by a plurality of supporting rods. In the longitudinal direction and the transverse direction, any two adjacent base units share one edge. Each base unit is a quadrangular pyramid composed of four triangles and a square. According to the regeneration cooling channel with the truss structure, on the basis of a traditional regeneration cooling structure, an air-like interlayer is constructed through the truss structure, a large amount of heat is isolated through the low heat conduction characteristic of air, the temperature of the outer wall of a combustion chamber is prevented from being too high, and the structural weight of the wall face of the combustion chamber is effectively reduced while the structural strength is guaranteed.

Description

technical field [0001] The present application relates to the technical field of ramjet combustion chambers, in particular to a regenerative cooling channel with a truss structure. Background technique [0002] Hypersonic vehicles propelled by ramjet engines have been a hot research and development issue in the aerospace field in recent years. Due to the extremely high aerodynamic and thermal loads brought about by the high flight Mach number and the extremely high temperature generated by the combustion of hydrocarbon fuel propellants, it exceeds the existing materials. One of the keys to designing a hypersonic vehicle is to solve the thermal protection problem of the vehicle, especially the cooling problem of the ramjet combustion chamber. Conventional turbine-based engines use cooling methods such as impact and air film, while the stagnation temperature of ramjet engines is extremely high, so it is difficult to use conventional air cooling methods and use regenerative coo...

AI Technical Summary

Problems solved by technology

This structure mainly has the following disadvantages: on the one hand, due to the risk of fuel coking, the flow channel in the traditional regenerative cooling structure should not be too flat, the space utilization rate in the direction of wall thickness is not good, and there is still a lot of room for weight reduction; on the other hand, in Metal materials with higher thermal conductivity in the thickness direction account for a larger proportion, resulting in a smaller equivalent thermal resistance in this direction, and the thermal insulation capacity needs to be improved

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