|Table of Contents|

Design and experiment of hydrogen peroxide/kerosene thrust chamber with regenerative cooling based on 3D printing(PDF)

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

Issue:
2023年04期
Page:
74-81
Research Field:
目次
Publishing date:

Info

Title:
Design and experiment of hydrogen peroxide/kerosene thrust chamber with regenerative cooling based on 3D printing
Author(s):
BIAN Xianggang LI Longfei WANG Huayu LING Qiancheng SONG Daliang
(Xi'an Aerospace Propulsion Institute, Xi'an 710100, China)
Keywords:
rapid manufacturing 3D printing hydrogen peroxide regenerative cooling thrust chamber
PACS:
V434
DOI:
-
Abstract:
In order to achieve the rapid verification of key technologies of hydrogen peroxide/kerosene thrust chamber, the design and test of thrust chamber based on 3D printing rapid manufacturing was conducted. Firstly, according to the design index, the design of hydrogen peroxide/kerosene thrust chamber was completed by utilizing the advantages of 3D printing, such as fewer parts, high connection strength and light structural weight. Then, the commercial software Fluent was used to perform the rapid numerical simulation of combustion on the design scheme, and the pressure, temperature, streamline, and mass fraction of each component in the thrust chamber under the design conditionwere obtained. The combustion performance was analyzed and the optimization of the design scheme was completed. Finally, the performance of the thrust chamber was evaluated through the long-term hot test. The results show that the 3D printing thrust chamber has high structural reliability, good cooling performance, high combustion performance, and meets the design requirements. Compared to the traditional mechanical processing techniques, it shortens the development cycle by 50%, reduces manufacturing costs by 40%, reduces the number of parts by 50%, and reduces weight by 20%. At the same time, it fully shows the advantages of the 3D printing technology in the key technology verification stage of the thrust chamber, such as short cycle, low cost and high reliability.

References:

[1] VENTURA M,MULLENS P.The use of hydrogen peroxide for propulsion and power[C]//35th Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,1999.
[2] WHITEHEAD J C,DITTMAN M D,LEDEBUHR A G.Progress toward hydrogen peroxide micropulsion[EB/OL].https://www.researchgate.net/publication/255019195_Progress_toward_hydrogen_peroxide_micropulsion,1999.
[3] 武瑞刚,韩利萍,楚蓓蓓,等.3D打印技术在航天企业的应用[J].机械工程与自动化,2020(6):225-226.
[4] 黄卫东.材料3D打印技术的研究进展[J].新型工业化,2016,6(3):53-70.
[5] 左蔚,宋梦华,杨欢庆,等.增材制造技术在液体火箭发动机应用述评[J].火箭推进,2018,44(2):55-65.
ZUO W,SONG M H,YANG H Q,et al.Application of additive manufacturing technology in liquid rocket engine[J].Journal of Rocket Propulsion,2018,44(2):55-65.
[6] 杨开.NASA为大尺寸发动机组件开发新型3D打印技术[J].航天制造技术,2020(5):70.
[7] 王治军,常新龙,田干.液体火箭发动机推力室设计[M].北京:国防工业出版社,2014.
[8] 王镜淇,王成刚,陈雪娇,等.RBCC组合动力用液体推进剂研究进展[J].火箭推进,2022,48(6):101-112.
WANG J Q,WANG C G,CHEN X J,et al.Research progress of liquid propellant development for RBCC engine[J].Journal of Rocket Propulsion,2022,48(6):101-112.
[9] 凌前程,林革,刘志让.过氧化氢/煤油双组元发动机催化分解点火研究[C]//第五届海内外华人航天科技研讨会论文集.西安:中国宇航学会,2004.
[10] HAUTMAN D,ROSFJORD T.Transverse liquid injection studies[C]//26th Joint Propulsion Conference.Reston,Virginia:AIAA,1990.
[11] LIN K C,KENNEDY P,JACKSON T.Penetration heights of liquid jets in high-speed crossflows[C]//40th AIAA Aerospace Sciences Meeting and Exhibit.Reston,Virginia:AIAA,2002.
[12] CHEN T,SMITH C,SCHOMMER D,et al.Multi-zone behavior of transverse liquid jet in high-speed flow[C]//31st Aerospace Sciences Meeting.Reston,Virginia:AIAA,1993.
[13] MAZALLON J,DAI Z,FAETH G.Aerodynamic primary breakup at the surface of nonturbulent round liquid jets in crossflow[C]//36th AIAA Aerospace Sciences Meeting and Exhibit.Reston,Virginia:AIAA,1998.
[14] WU P K,KIRKENDALL K A,FULLER R P,et al.Breakup processes of liquid jets in subsonic crossflows[J].Journal of Propulsion and Power,1997,13(1):64-73.
[15] 王振国.液体火箭发动机燃烧过程建模与数值仿真[M].北京:国防工业出版社,2012.
[16] 庄逢辰.液体火箭发动机喷雾燃烧的理论、模型及应用[M].长沙:国防科技大学出版社,1995.
[17] MENTER F R.Two-equation eddy-viscosity turbulence models for engineering applications[J].AIAA Journal,1994,32(8):1598-1605.
[18] 郭康康,聂万胜,刘瑜,等.小型气氧/煤油火箭发动机试验及内流场数值模拟[J].导弹与航天运载技术,2018(6):43-48.

Memo

Memo:
-
Last Update: 1900-01-01