基于试验设计的固体火箭冲压发动机燃烧效率规律研究

doi:10.7527/S1000-6893.2015.0116

Abstract

Abstract:

To study the combustion efficiency of air and primary fuel in the combustor of solid ducted rocket with twin-90°ventral 2D inlets, five factors including numbers of fuel inlets,dome height, rate of the length of combustion and diameter,air-flow angle and air-flow velocity are selected as the influence factors of secondary combustion efficiency. And, the five-factor and two-level table is established based on design of experiment (DOE) methodology. Flow fields of 32 combustors with different structures in above DOE table are studied by numerical simulation. Then, the simulation results are analyzed by using data processing procedure of DOE and the effect of five factors on combustion efficiency is obtained. To validate the results of simulation,performance of five different combustors in the DOE table are tested in the direct-connect experiment facility and the simulation result matches up well with the experiment result. In this paper, the DOE methodology has been successfully applied in the research of combustion performance of solid ducted rocket, and supplies a new feasible approach for the improvement of engine performance.It can be concluded that the research in this paper is valuable in the domain of engineering application.

Key words: design of experiment methodology, factor, combustion efficiency, numerical simulation, direct-connect experiment

CLC Number:

V430

SHAN Ruizi, CAO Junwei, MO Zhan, CHEN Zhiming. Research of solid ducted rocket combustion efficiency based on design of experiment methodology[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(9): 2859-2868.

References

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Research of solid ducted rocket combustion efficiency based on design of experiment methodology

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