| Autor: |
Chul-Sung Ryu, Yong-Hyun Chung, Won-Kook Cho, Soo-Yong Lee, Kwang-Jin Lee, Seung-Han Kim |
| Rok vydání: |
2005 |
| Předmět: |
|
| Zdroj: |
Journal of the Korean Society for Aeronautical & Space Sciences. 33:107-113 |
| ISSN: |
1225-1348 |
| DOI: |
10.5139/jksas.2005.33.3.107 |
| Popis: |
A calorimeter of 2-ton thrust level rocket engine chamber has been developed to measure the wall heat flux. The liner of the chamber is made of copper-chromium alloy to maximize the heat transfer performance and structural strength. 1-D design code based on empirical correlations has been used for the prediction of the global thermal characteristics while 3-D CFD has been applied for the verification of local cooling performance. The predicted average wall heat flux at the throat is 43 for the combustion chamber pressure of 53 bar. The chamber structure is confirmed to be safe at the pressure of 150 bar through 2-D stress analysis and measurement of the strain of the test species. Finally, the test of pressurizing the calorimeter chamber has been performed with water at the pressure of 150 bar in room temperature environment. No thermal damage has been detected after the hot-fire test in the test nozzle of same cooling performance with the developed calorimeter though the measured throat heat flux is higher than the design value by 10%. |
| Databáze: |
OpenAIRE |
| Externí odkaz: |
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