A rocket stamping composite full runner for wide range work

Abstract

The invention discloses a wide-range working rocket stamping combined full flow channel comprising an air inlet channel inner compression section, a combustion chamber and a tail spraying pipe which are sequentially connected from front to back. The combustion chamber comprises a supersonic combustion chamber section and a subsonic combustion chamber section from front to back; the supersonic combustion chamber section is divided into three independent flow channel bodies in the longitudinal direction of the supersonic combustion chamber section; and the flow channel bodies all communicate with the subsonic combustion chamber section. The front ends of the flow channel bodies are the air inlet ends, and three independent air inlets are formed correspondingly; the three independent flow channel bodies are formed by enclosing of two central supporting plates arranged in the supersonic combustion chamber section in a spaced mode and the two side walls of the supersonic combustion chamber section; the rear ends of the central supporting plates are provided with a plurality of rocket ejecting spraying pipe mounting holes communicating with cavities; the interiors of the central supporting plates are the hollow cavities used for communicating with a fuel storage tank; and a plurality of fuel nozzles communicating with the cavities are formed in the two side faces of the central supporting plates from front to back at intervals. The wide-range working rocket stamping combined full flow channel multimode flow channel capable of being shared is high in flow channel extensibility and simple in structure changing style.

Description

technical field [0001] The invention belongs to the technical field of rocket-based combined cycle engines, and in particular relates to a rocket stamping combined full runner with a wide range of work. Background technique [0002] Compared with the existing power system, which only needs to work in a narrow range, the characteristics of rocket ramming combination (RBCC) propulsion in large airspace and wide speed range bring great challenges to the full channel design of rocket ramming combined power. The key to the configuration design of the fixed-structure RBCC combustor is to adapt to the change of flow conditions with a wide Mach number, and to keep the flow channel area of ​​the combustor matching the combustion heat release, so as to complete stable and efficient work under different modes. The performance of the combustion chamber mainly depends on the heat obtained by the air flow in the combustion chamber. In the ejection mode, in order to ensure the suction effe...

AI Technical Summary

Problems solved by technology

[0002] Compared with the existing power system, which only needs to work in a narrow range, the characteristics of rocket ramming combination (RBCC) propulsion in large airspace and wide speed range bring great challenges to the full channel design of rocket ramming combination power

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