|Table of Contents|

Analysis on outlet temperature uniformity of hydrogen/oxygen preburner with high-pressure and low-mixture-ratio(PDF)

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

Issue:
2023年01期
Page:
29-35
Research Field:
目次
Publishing date:

Info

Title:
Analysis on outlet temperature uniformity of hydrogen/oxygen preburner with high-pressure and low-mixture-ratio
Author(s):
PAN Gang1;  NIU Xudong1; PAN Liang1;  ZHENG Mengwei1;  SUN Jiguo1;  DING Zhaobo2
(1.Beijing Aerospace Propulsion Institute, Beijing 100076, China 2.Academy of Aerospace Propulsion Technology, Xian 710100, China)
Keywords:
hydrogen/oxygen preburner recess ratio turbulence structure variable operating condition outlet temperature uniformity
PACS:
V434
DOI:
-
Abstract:
In order to deeply understand the outlet temperature uniformity of high-pressure and low-mixture-ratio hydrogen/oxygen preburner, a subscale preburner was designed.The uniformity of outlet combustion gas temperature was carried out under different recess ratios, turbulence structures and operating conditions.In addition, the rationality of the design scheme was verified experimentally by the full-scale preburner.The experimental results show that the gas temperature uniformity increases gradually with the increase of recess ratio.With the increase of the combustor pressure and mixture ratio, the temperature homogenization effect of the turbulator is improved.The temperature uniformity in combustor can be improved 54.8-89 by the combination of turbulator and elbow structure.Under the design parameters of the injector in this paper, compared with the swirl coaxial injector, the temperature uniformity of subscale preburner is better with shear coaxial injector under 50-100 operating conditions.The temperature uniformity of full-scale preburner is less than ±50 K when the turbulator and the 90° elbow are used.At the same time, the gas temperature uniformity of the outlet near the oxygen turbine is better than that of the outlet near the hydrogen turbine.

References:

[1] 郑孟伟,岳文龙,孙纪国,等.我国大推力氢氧发动机发展思考[J].宇航总体技术,2019,3(2):12-17.
[2] 孙纪国,岳文龙.我国大推力补燃氢氧发动机研究进展[J].上海航天,2019,36(6):19-23.
[3] 郑大勇,陶瑞峰,张玺,等.大推力氢氧发动机关键技术及解决途径[J].火箭推进,2014,40(2):22-27.
ZHENG D Y,TAO R F,ZHANG X,et al.Study on key technology for large thrust LOX/LH2 rocket engine[J].Journal of Rocket Propulsion,2014,40(2):22-27.
[4] 丁兆波,刘倩,王天泰,等.220 t级补燃循环氢氧发动机推力室研制[J].火箭推进,2021,47(4):13-21.
DING Z B,LIU Q,WANG T T,et al.Development for thrust chamber of 220 t staged combustion cycle LOX/LH2 engine[J].Journal of Rocket Propulsion,2021,47(4):13-21.
[5] 丁兆波,潘刚,牛旭东,等.高压补燃大推力氢氧发动机预燃室关键技术[J].导弹与航天运载技术,2020(4):39-44.
[6] COLLIER M R,DOUGHERTY N S.Altitude testing of the J-2 rocket engine in propulsion engine test cell(J-4)(test J4-1554-20 THROUGH J4-1554-26)[R].AEDC-TR-67-145,1967.
[7] HUTT J J.SSME fuel preburner injector characterization[R].N94-23037,1994.
[8] GREENE W.SSME 0523 incident: Analysis of temperatures in the fuel preburner[C]//37th Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,2001.
[9] WOOD B.Propulsion for the 21st century:RS-68[C]//38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Reston,Virginia:AIAA,2002.
[10] KYNARD M.From paper to production:An update on NASAs upper stage engine for exploration[R].NASA M10-0617,2010.
[11] BYRD T.Testing to transition the J-2X from paper to hardware[R].NASA M10-0108,2010.
[12] BYRD T.The J-2X upper stage engine:From design to hardware[C]//46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Reston,Virginia:AIAA,2010.
[13] GREENE W.Development of the J-2X engine for the Ares I crew launch vehicle and the Ares V cargo launch vehicle building on the Apollo program for lunar return missions[R].NASA MSFC-100,2007.
[14] POULIQUEN M.VULCAIN cryogenic engine:Components test results[C]//22nd Joint Propulsion Conference.Reston,Virginia:AIAA,1986.
[15] THIARD B.Vulcain gas generator development status[C]//26th Joint Propulsion Conference.Reston,Virginia:AIAA,1990.
[16] DENIS L,GEORGES P.An experimental study of LOX/LH2 coaxial injection elements for the Vulcain gas generator[C]//23rd Joint Propulsion Conference.Reston,Virginia:AIAA,1987.
[17] EURY S,GASTAL J,BORROMEE J.Development status of the Vulcain engine[C]//26th Joint Propulsion Conference.Reston,Virginia:AIAA,1990.
[18] CAISSO P,BARTON J,ILLIG M,et al.Development status of the Vulcain 2 engine[C]//36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,2000.
[19] BROSSEL P,BARTON J,GOULPEAU C,et al.Development status of the Vulcain and Vulcain mark II engines Ariane V family[R].IAF95-S207,1995.
[20] BONNIOT C.The Vulcain MKII engine for Ariane 5 performance improvement[C]//28th Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,1992.
[21] TORII Y,SOGAME E.Development status of LE-7[R].IAF86-163,1986.
[22] KATSUTA K,MIYAJIMA H,SUZUKI K.Development status of LE-7 H-II rocket main engine[C]//22nd Joint Propulsion Conference.Reston,Virginia:AIAA,1986.
[23] FUKUSHIMA Y,NAKATSUZI H,NAGAO R,et al.Development status of LE-7A and LE-5B engines for H-IIA family[R].IAF97-S102,1997.
[24] RACHUK V,GONCHAROV N,MARTYNENKO Y,et al.Design,development,and history of the oxygen/hydrogen engine RD-0120[C]//31st Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,1995.
[25] TURTUSHOV V,ORLOV V,HULKA J,et al.Final model development and full-scale testing of a soot-free fuel-rich kerosene tripropellant preburner[C]//32nd Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,1996.
[26] 吴宝元,葛李虎,谭永华,等.富氧预燃室高压缩尺试验研究[J].推进技术,2003,24(2):104-108.
[27] 张锋,严宇,王延涛,等.气氧/煤油富燃燃气发生器燃烧试验研究[J].推进技术,2016,37(10):1916-1921.
[28] 潘刚,牛旭东,丁兆波,等.大流量低混合比氢氧喷嘴变工况燃烧特性研究[J].导弹与航天运载技术,2020(5):43-47.
[29] 白晓,李清廉,成鹏,等.液体中心式气液同轴离心式喷嘴火焰振荡特性[J].推进技术,2021,42(7):1593-1605.

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