|Table of Contents|

Quasi-2D heat transfer calculation method of regenerative cooling thrust chamber (PDF)

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

Issue:
2023年02期
Page:
66-73
Research Field:
目次
Publishing date:

Info

Title:
Quasi-2D heat transfer calculation method of regenerative cooling thrust chamber
Author(s):
WU Youliang;  DING Yushuo;  LIU Xiao;  LIU Yangmin;  TIAN Yuan
(Beijing Aerospace Propulsion Institute, Beijing 100076, China)
Keywords:
regenerative cooling;  heat transfer;  quasi-2D;  temperature stratification;  boundary layer
PACS:
V434.14
DOI:
-
Abstract:
In order to improve the calculation accuracy of heat transfer, a general quasi-2D model was developed to study heat transfer of thrust chamber.This model takes account of the temperature stratification effect caused by heat conduction between coolant layers.The convective heat transfer on the gas side can be calculated by using Bartz equation or solving the governing equations of boundary layers.Then a quasi-2D heat transfer code was developed based on MATLAB language.Finally, validation of the model was carried out by comparison with the analysis of a rocket thrust chamber obtained by the code of one-dimensional model and CFD solver.The results show that the quasi-2D model can calculate the temperature stratification in the cooling channels.The calculated values of coolant temperature rise and pressure loss are in good agreement with the thermal test data, and the error is less than 10, which is better than the one-dimensional heat transfer results, which verifies the effectiveness of the calculation method.In addition, the heat flux obtained by directly solving the boundary layer governing equation is in good agreement with the CFD results.Finally, the calculation time of quasi-2D model is shortrt and the efficiency is higher.

References:

[1] 孙冰,张建伟.火箭发动机热防护技术[M].北京:北京航空航天大学出版社,2016.
[2] 刘国球. 液体火箭发动机原理[M].北京:中国宇航出版社,2005.
[3] CALVO J B,HANNEMANN K.Numerical simulation of liquid rocket engine cooling channels[C]//45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,2009.
[4] NEGISHI H,DAIMON Y,YAMANISHI N,et al.Numerical investigation of supercritical coolant flow in liquid rocket engine[C]//46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,2010.
[5] NEGISHI H,KUMAKAWA A,YAMANISHI N,et al.Heat transfer simulations in liquid rocket engine subscale thrust chambers[C]//44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Reston,Virginia:AIAA,2008.
[6] NEGISHI H,KUMAKAWA A,MORIYA S,et al.Numerical investigations of heat transfer enhancement in a thrust chamber with hot gas side wall ribs[C]//47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition.Reston,Virginia:AIAA,2009.
[7] 方磊,刘伟.姿控用再生冷却推力室传热特性研究[J].火箭推进,2008,34(6):6-13.
FANG L,LIU W.Research on heat transfer characteristic of regeneratively cooled attitude control engine thrust chamber[J].Journal of Rocket Propulsion,2008,34(6):6-13.
[8] 吴峰,王秋旺,罗来勤,等.液体推进剂火箭发动机推力室再生冷却通道三维流动与传热数值计算[J].航空动力学报,2005,20(4):707-712.
[9] 康玉东,孙冰,高翔宇.液体火箭发动机推力室冷却通道温度分层数值研究[J].航空动力学报,2009,24(8):1904-1910.
[10] PIZZARELLI M,NASUTI F,ONOFRI M.Coupled numerical simulation of wall heat conduction and coolant flow in liquid rocket engines[C]//47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,2011.
[11] DIVALENTIN J,NARAGHI M.Effects cooling channel curvature on coolant secondary flow and heat transfer[C]//46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,2010.
[12] 吴有亮,张成印,潘浩,等.再生冷却燃气对流换热系数计算方法优化研究[J].火箭推进,2018,44(1):22-26.
WU Y L,ZHANG C Y,PAN H,et al.Optimization for calculation method of gas convective heat transfer coefficient inside regeneratively-cooled chamber[J].Journal of Rocket Propulsion,2018,44(1):22-26.
[13] 李军伟,刘宇.一种计算再生冷却推力室温度场的方法[J].航空动力学报,2004,19(4):550-556.
[14] 孙鑫,杨成虎.5 kN再生冷却发动机推力室传热研究[J].火箭推进,2012,38(2):32-37.
SUN X,YANG C H.Heat transfer investigation for 5 kN regeneratively-cooled engine thrust chamber[J].Journal of Rocket Propulsion,2012,38(2):32-37.
[15] PIZZARELLI M,CARAPELLESE S,NASUTI F.A quasi-2D model for the prediction of the wall temperature of rocket engine cooling channels[J].Numerical Heat Transfer,Part A:Applications,2011,60(1):1-24.
[16] BARTZ D R. A simple equation for rapid estimation of rocket nozzle convective heat transfer coefficient[J].Jet Propulsion,1957,27(1):49-51.
[17] 刘阳旻.液体火箭发动机喷管附面层求解器开发与应用[D].北京:中国运载火箭技术研究院,2021.
[18] 刘阳旻,田原.氢氧液体火箭发动机喷管边界层传热分析[J].低温工程,2020(S1):167-172.
[19] KACYNSKI K.Thermal stratification potential in rocket engine coolant channels[R].NASA-TM-4378.
[20] HESS H L,KUNZ H R.A study of forced convection heat transfer to supercritical hydrogen[J].Journal of Heat Transfer,1965,87(1):41-46.
[21] NARAGHI M,DUNN S,COATS D.A model for design and analysis of regeneratively cooled rocket engines[C]//40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,2004.

Memo

Memo:
-
Last Update: 1900-01-01