|Table of Contents|

Simulation on thrust/drag property in different modes of RBCC engine(PDF)

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

Issue:
2022年06期
Page:
52-58
Research Field:
目次
Publishing date:

Info

Title:
Simulation on thrust/drag property in different modes of RBCC engine
Author(s):
YANG Jianwen;  LIU Jiwu;  ZHANG Mengzheng;  NAN Xiangjun
(Key Laboratory of Science and Technology on Liquid Rocket Engine, Xian Aerospace Propulsion Institute, Xian 710100, China)
Keywords:
rocket-based combined-cycle work mode thrust drag simulation research
PACS:
V435
DOI:
-
Abstract:
Combustion flow of a RBCC test model was simulated through the three-dimensional numerical methods.Good agreements between computation and experimental results were obtained for wall static pressure distribution, validating that the numerical scheme employed is reliable.Results show that, to the same flow conditions, when the engine works properly, the air mass flux and the drag of the inlet are the same under different model.For the cold flow model, although the nozzle produced some thrust, but the inlet and combustor produced much more drag, so the engine will produce drag.For the rocket model, rocket will have ejector effect, and the ejector air will combustion again with the rocket gas, the engine thrust will be larger than the rocket thrust, and have 12.7 thrust gain.For the ramjet model, when the residual gas coefficient decreased, the engine thrust will increase.

References:

[1] MATTHEW K LEHMAN M K.Mixing and reaction processes in rocket based combined cycle and conventional rocket engines[D].State College:The Graduate School of the Pennsylvania State University,2000.
[2] 牛东圣,侯凌云,潘鹏飞,等.超燃冲压发动机内外流场三维燃烧数值模拟[J].航空动力学报,2014,29(4):763-769.
[3] 刘昊,王君.RBCC发动机火箭推力增益之探讨[J].火箭推进,2017,43(1):18-23.
LIU H,WANG J.Discussion of rocket thrust augmentation for RBCC engine[J].Journal of Rocket Propulsion,2017,43(1):18-23.
[4] 黄伟,罗世彬,王振国.火箭基组合循环(RBCC)发动机性能分析[J].火箭推进,2007,33(5):6-10.
HUANG W,LUO S B,WANG Z G.Performance analysis of RBCC engine[J].Journal of Rocket Propulsion,2007,33(5):6-10.
[5] 吕翔,刘佩进,何国强.RBCC发动机性能分析方法研究[J].固体火箭技术,2007,30(2):120-123.
[6] 何国强,秦飞,魏祥庚,等.火箭冲压组合发动机燃烧的若干基础问题研究[J].实验流体力学,2016,30(1):1-14.
[7] 秦飞,吕翔,刘佩进,等.火箭基组合推进研究现状与前景[J].推进技术,2010,31(6):660-665.
[8] 王亚军.基于热力调节具有宽适应性的RBCC亚燃模态研究[D].西安:西北工业大学,2017.
[9] 汤祥,何国强,秦飞.RBCC发动机超燃模态燃料喷射方案数值模拟研究[J].固体火箭技术,2013,36(6):736-741.
[10] 秦飞,何国强,刘佩进,等.圆形燃烧室支板火箭超燃冲压发动机数值模拟[J].固体火箭技术,2011,34(2):150-155.
[11] 徐朝启,何国强,刘佩进,等.RBCC发动机亚燃模态一次火箭引导燃烧的实验[J].航空动力学报,2013,28(3):567-572.
[12] 汤祥,何国强,秦飞.轴对称结构RBCC燃烧室超燃模态燃烧性能研究[J].西北工业大学学报,2014,32(1):29-34.
[13] 林彬彬,潘宏亮,叶进颖,等.多模态RBCC主火箭混合比对引射流动燃烧影响[J].固体火箭技术,2015,38(6):804-810.
[14] 刘晓伟,石磊,刘佩进,等.RBCC发动机引射模态进气道特性研究[J].固体火箭技术,2016,39(5):601-605.
[15] 万少文,何国强,刘佩进,等.RBCC混合燃烧模式下燃料喷注位置对燃烧性能影响研究[J].固体火箭技术,2010,33(6):636-640.
[16] 潘科玮,何国强,刘佩进,等.RBCC发动机燃料喷注位置变化对混合燃烧模式燃烧的影响[J].航空动力学报,2011,26(8):1900-1906.
[17] 赖林.带空腔超燃冲压发动机燃烧室喷雾流场特性研究[D].长沙:国防科技大学,2010.
[18] 潘余.超燃冲压发动机多凹腔燃烧室燃烧与流动过程研究[M].长沙:国防科技大学,2007.
[19] 刘世杰.超燃冲压发动机支板流场RANS_LES模拟及燃烧过程试验研究[M].长沙:国防科技大学,2007.
[20] 张留欢,南向军,张蒙正.RBCC发动机纯火箭模态流场数值仿真研究[J].火箭推进,2016,42(2):42-46.
ZHANG L H,NAN X J,ZHANG M Z.Numerical simulation for flow field in pure rocket modality of RBCC engine[J].Journal of Rocket Propulsion,2016,42(2):42-46.

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