Pulse detonation and rotary detonation combined multi-channel combustion chamber

Abstract

The invention relates to a pulse detonation and rotary detonation combined multi-channel combustion chamber which comprises a pulse detonation combustion cavity, a first-stage rotary detonation combustion cavity, a second-stage rotary detonation combustion cavity, a third-stage rotary detonation combustion cavity, an air and fuel injector and a combustion chamber exhaust cavity. By combining the structural characteristics of a pulse detonation combustion chamber and a rotary detonation combustion chamber, a combined multi-channel detonation combustion chamber structure is formed, and when the rotary detonation combustion chamber and the pulse detonation combustion chamber work at the same time, the problem that the working stability of the combustion chamber is reduced due to intermittent exhaust of the pulse detonation combustion chamber can be effectively solved; meanwhile, the circulation area of the combustion chamber can be effectively increased, and the thrust-weight ratio of the combustion chamber is increased; and the output power of the combustion chamber can be effectively adjusted by controlling whether different combustion chambers are ignited or not. The working stability of the combustion chamber is guaranteed, the space utilization rate of the combustion chamber is increased, the output power of the combustion chamber is increased, and the adjusting range of the output power of the combustion chamber is widened.

Description

technical field [0001] The invention belongs to the technical field of detonation combustion chambers, and in particular relates to a combined multi-channel combustion chamber of pulse detonation and rotary detonation. Background technique [0002] Combustion can be divided into slow combustion and detonation combustion according to the intensity of the chemical reaction. Existing aerospace engines, including turbojet engines, conventional rocket engines, ramjet engines, etc., and industrial gas turbines and other power plants, the combustion chambers are all based on the slow-burning combustion method of the isobaric cycle, and its technology maturity is relatively high, which further improves the thermal cycle. Efficiency is very difficult. The characteristic of detonation combustion is that there is a shock wave structure before the chemical reaction zone, and the shock wave and the chemical reaction zone are coupled together to propagate. Due to the self-pressurization...

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Problems solved by technology

[0004] The purpose of the present invention is to provide a combined multi-channel combustor of pulse detonation and rotary detonation, which is intended to solve the problem of low working stability of the combustion chamber caused by the intermittent exhaust of the existing PDC and poor compatibility with compressor turbine components , and the problem of insufficient utilization of RDC space

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