|Table of Contents|

Influence of ignition relay process of gas generator onstarting performance of engines(PDF)

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

Issue:
2021年03期
Page:
74-82
Research Field:
研究与设计
Publishing date:

Info

Title:
Influence of ignition relay process of gas generator onstarting performance of engines
Author(s):
JIANG Lei1LIU Shang1LIU Zhirang2HAN Hongwei1
1.Science and Technology on Liquid Rocket Engine Laboratory,Xi'an 710100,China; 2.Academy of Aerospace Propulsion Technology,Xi'an 710100,China
Keywords:
liquid propellant rocket engine open-cycle forced start-up liquid oxygen/kerosene numerical simulation
PACS:
V434.1
DOI:
-
Abstract:
Using the open-cycle LOX/kerosene rocket engine as an example,the engine start-up characteristics were investigated.The simulation model of the engine start-up process was established,and the calculated performance parameter curves basically accorded with the test data,which preliminarily verified the feasibility of the simulation model.The influence of ignition relay process of gas generator on engine starting performance was further analyzed.The results demonstrate that when gas generator uses oxygen-enriched ignition,the fuel valve of gas generator opened early,the gas generator and the solid starter work together for a long time,and the acceleration time of engine is short,but the parameter overshoot is large; when the fuel valve of gas generator opened late,there is a lot of oxidant accumulated in the gas generator,the temperature peak and pressure peak are large during ignition; the gas generator needs to ignite before the pressure of the solid starter drops rapidly to prevent accumulated oxidant and fuel-rich gas from reacting at the equivalent mixing ratio,thereby releasing a lot of heat; when theoxygen valve opening time of gas generator is late,the opening time difference between oxygen valve and fuel valve of the gas generator can be reduced to reduce the ignition temperature peak and pressure peak.

References:

[1] BINDER M.A transient model of the RL10A-3-3A rocket engine[C]//31st Joint Propulsion Conference and Exhibit.San Diego,CA,USA.Reston,Virigina: AIAA,1995.
[2] KUROSU A,YAMANISHI N,TANI N,et al.Study of next booster engine LE-X in JAXA[C]//42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Sacramento,California.Reston,Virigina: AIAA,2006.
[3] KANMURI A, KANDA T, WAKAMATSU Y, et al. Transient analysis of LOX/LH2 rocket engine(LE-7)[C]//25th Joint Propulsion Conference. Monterey, CA, USA. Reston, Virigina: AIAA, 1989.
[4] 陈宏玉,刘红军,陈建华.补燃循环发动机强迫起动过程[J].航空动力学报,2015,30(12): 3010-3016.
[5] 徐浩海,刘站国.补燃循环发动机起动过程涡轮功率控制[J].火箭推进,2006,32(4): 10-14.XU H H,LIU Z G.Turbine power control of staged combustion cycle engine during start-up[J].Journal of Rocket Propulsion,2006,32(4): 10-14.
[6] 杨明磊,张黎辉.液氧/煤油补燃循环发动机起动过程研究[J].火箭推进,2009,35(1): 21-26.YANG M L,ZHANG L H.Study on start-up of the staged combustion LOX/kerosene rocket engine[J].Journal of Rocket Propulsion,2009,35(1): 21-26
[7] 李程,杨永强,徐浩海,等.500 t级液氧煤油补燃发动机起动过程仿真研究[J].火箭推进,2014,40(6): 1-7.LI C,YANG Y Q,XU H H,et al.Numerical simulation of start-up process for 500 t thrust LOX/kerosene staged combustion cycle rocket engine[J].Journal of Rocket Propulsion,2014,40(6): 1-7.
[8] 杨永强,刘红军,徐浩海,等.补燃循环发动机强迫起动研究[J].火箭推进,2011,37(2):14-18.YANG Y Q,LIU H J,XU H H,et al.Research on forced start-up of staged combustion engine[J].Journal of Rocket Propulsion,2011,37(2):14-18.
[9] 尘军,王桁.高压补燃氢氧发动机系统动态仿真[J].航天推进与动力,2008(2):15-21.
[10] 王弘亚,张卫红.基于AMESim平台的氢氧火箭发动机启动过程仿真研究[J].导弹与航天运载技术,2017(6): 28-31.
[11] 王弘亚,张箭,郑大勇. 补燃循环氢氧发动机起动过程仿真研究[J].航天推进与动力,2017(1):34-39.
[12] 黄仕启,刘登丰.上面级发动机瞬态工作过程的模块化建模仿真与工程应用[J].航天推进与动力,2012(3):39-35.
[13] 蒲光荣,单磊,赵晓慧,等.泵压式多次起动发动机起动过程仿真研究[J].火箭推进,2019,45(5): 17-24.PU G R,SHAN L,ZHAO X H,et al.Simulation study on start-up processes of a multi-startup turbopump-fed rocket engine[J].Journal of Rocket Propulsion,2019,45(5): 17-24.
[14] 张涛,唐虎,周江平,等.可贮存推进剂泵压式液体火箭发动机多次起动系统研究[J].火箭推进,2010,36(3):15-18.ZHANG T,TANG H,ZHOU J P,et al.Study on the multi-start system of turbopump-fed rocket engine with storable propellants[J].Journal of Rocket Propulsion,2010,36(3):15-18.
[15] 舍维亚科夫 A.A.火箭发动机自动控制理论[M].北京:机械工业出版社,1978.
[16] 尘军.液氢液氧高压补燃发动机系统和瞬变特性研究[D].西安:中国航天科技集团公司第十一研究所,2002.
[17] 吴有亮.基于Modelica的液体火箭发动机系统建模与仿真研究[D].北京: 北京航天动力研究所,2018.
[18] WYLIE E B,STREETER V L.瞬变流[M].清华大学流体传动与控制教研室,译.北京: 水利电力出版社,1983.
[19] 刘昆,张育林.低温推进剂火箭发动机泵出口密度、温度计算的一种新方法[J].低温工程,2002(4): 5-9.
[20] 吴新明,熊亚.混合理想气体绝热指数γmix的计算讨论[J].化学通报,1997,60(2): 32-36.
[21] 韦华.液氧煤油补燃循环发动机关机控制研究[D].西安:西安航天动力研究所,2012.
[22] 李程.重型液氧煤油补燃发动机起动过程仿真研究[D].西安:西安航天动力研究所,2014.
[23] 王飞.大推力液氧煤油发动机起动过程仿真研究[D].西安:西安航天动力研究所,2015.

Memo

Memo:
-
Last Update: 1900-01-01