Large-scale hyshot scramjet engine and three-dimensional petal-shaped section combustor

Abstract

The invention provides a large-scale hyshot scramjet engine and a three-dimensional petal-shaped section combustor. The three-dimensional petal-shaped section combustor comprises a fuel injection section, a flame stabilization section and an expansion section, wherein the wall face of the flame stabilization section is in a lobe structure that bumps and recesses are alternatively formed on the circumference direction; the bumps of the lobe structure gradually approach towards a center axis along a flow direction; the lobe structure extends to the tail end of the fuel injection section, so as to form a petal-shaped structure; a second group of orifices are formed in each of the top points of the bumps at the tail end of the fuel injection section; a first group of orifices are formed in each of the top points of the recesses at the upstreams of the second group of the orifices, so as to form combined injection. According to the three-dimensional petal-shaped section combustor, the lobe structure can divide incoming flow air into a plurality of strands of air flows, so that the injection mixing of fuels is beneficial; bump injection and recess injection of a combustor are combined, so that the effect that the fuels are uniformly mixed in a short distance is realized. Furthermore, no support plates exist in the combustor, so that thermal protection limit is easy to realize.

Description

technical field [0001] The invention relates to a large-scale scramjet engine and a combustion chamber used therein. Background technique [0002] Large-scale hypersonic aircraft, even large aerospace aircraft, need to use large-scale scramjet engines. [0003] Usually, in a scramjet engine with a circular cross-section combustion chamber flying around 6Ma, the gas temperature is high (~2650K), the pressure is high (3~5atm), the heat flow is large, and the cooling fuel flow is small, which makes the thermal protection of the combustion chamber extremely difficult. , the requirement of thermal protection puts strong constraints on the design of the combustion chamber. [0004] The common use of direct injection of fuel on the wall can meet the requirements of thermal protection, but it is difficult to solve the problem of penetration and mixing contradictions, because the use of high injection pressure drop and large hole injection can achieve relatively high penetration, bu...

AI Technical Summary

Problems solved by technology

[0008] The object of the present invention is to provide a three-dimensional petal-shaped cross-section combustion chamber of a scramjet to solve the problems of penetration depth and uniform mixing of fuel injection, while taking into account the thermal protection of the combustion chamber

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