|Table of Contents|

Analysis on unsteady exhaust process of pulse detonation engine and design method of nozzle(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2021年06期
Page:
93-100
Research Field:
专刊
Publishing date:

Info

Title:
Analysis on unsteady exhaust process of pulse detonation engine and design method of nozzle
Author(s):
WANG Yongjia1; YAN Yu1; JIAO Zhongtian1; 2; ZHANG Yang3; FAN Wei2
(1. Science and Technology on Liquid Rocket Engine Laboratory,Xian Aerospace Propulsion Institute,Xian 710100,China 2. School of Power and Energy,Northwestern Polytechnical University,Xian 710072,China 3. Xian Institute of Modern Control Technology, Xian 710054,China)
Keywords:
unsteady exhaust fixed nozzle pressure platform thrust coefficient
PACS:
V439
DOI:
-
Abstract:
In order to initially derive the nozzle design guidelines for pulse detonation engine,the unsteady exhaust process of pulse detonation combustion and the applicable nozzle design methods were analyzed based on numerical simulation and theoretical analysis methods. The unsteady exhaust process of pulse detonation combustion can be divided into four stages:detonation wave propagation stage,pressure downhill stage,pressure plateau stage and low pressure exhaust stage. Take the pulse detonation combustion of C2H4/O2 in straight tube as an example,the expansion ratio of suitable adjustable nozzle changes from 13 to 1 corresponding to the exhaust pressure range from 90.6 p∞ to 1.72 p∞. For the fixed nozzle scheme,the loss of shock wave triggered by over-expansion should be avoided. The design point of the fixed nozzle can be calculated by making use of the parameters of pressure platform,under which the thrust coefficient up to 0.95. The gas parameters of design point corresponding to the gas state when final Taylor expansion wave travels to the exit,which can be deduced from classical detonation theoretical equation,so as to realize the rapid design of fixed nozzle for the detonation.

References:

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