A Scramjet Combustion Chamber Performance Prediction Method

Abstract

The invention provides a scramjet engine combustion chamber performance pre-evaluation method. By taking a thermal throat as a starting point, parameter distribution from the starting point to a combustion chamber inlet and from the starting point to a combustion chamber outlet is calculated, and the problem that a singular value is apt to occur in the thermal throat during solution due to a reason that the traditional one-dimension calculation is performed from the combustion chamber inlet is avoided. The scramjet engine combustion chamber performance pre-evaluation method fully considers the different working modes of the combustion chamber and provides a reference basis for the design of the combustion chamber within a wide flight Ma range.

Description

technical field [0001] The invention relates to a method for estimating the performance of a scramjet combustion chamber, and belongs to the technical field of scramjet engines. Background technique [0002] The dual-mode scramjet is an effective power device for hypersonic air-breathing aircraft. Its combustion chamber can work in scramjet or sub-combustion mode according to different flight conditions and fuel injection conditions so that the performance of the engine can reach best. [0003] In the development process of the dual-mode scramjet engine, the prediction of its combustion chamber performance has important guiding significance for the initial design and optimization of the engine. The more commonly used method is to use the three-dimensional full-scale numerical calculation method, which can obtain more comprehensive three-dimensional flow field parameters of the combustion chamber, including temperature, pressure, velocity, thrust, combustion efficiency, etc....

AI Technical Summary

Problems solved by technology

The direction of solution is generally from the entrance of the combustion chamber to the exit of the combustion chamber, and the problem of singular value is very easy to appear when solving the thermal throat

In addition, scramjet combustion chambers will have different combustion modes under different working conditions. There is no special calculation for different combustion modes in the existing one-dimensional analysis, and the analysis results are in a single state. Range of combustion chamber design cannot provide reference

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