Numerical Analyses of the Conjugate Heat Transfer in a Bipropellant Liquid Rocket Combustor

• Main Authors: Tsu-YangHuang, 黃祖洋
• Other Authors: Tsung-Leo Jiang
• Format: Others
• Language: zh-TW
• Published: 2010
• Online Access: http://ndltd.ncl.edu.tw/handle/29899202791597923319

碩士 === 國立成功大學 === 航空太空工程學系碩博士班 === 98 === 　The high-temperature gas of a bipropellant liquid rocket combustor may burn and erode the chamber wall, damaging the whole structure. Therefore, in a general practice, part of the fuel of a bipropellant liquid rocket is injected toward the chamber wall to form a film, cooling down the chamber wall. In the present study, a bipropellant liquid rocket combustion simulation model is developed for the conjugate heat transfer analysis the combustion flow and the chamber wall. The simulation results indicate that considering the effect of gravity leads to better extension of the cooling film and higher temperature on nozzle. For the investigation of the arrangement of impinging jets, the case of NTO(inner)/MMH(outer) results in the center flame structure and slower evaporating velocity of the cooling film than that of the case using MMH(inner)/NTO(outer). The NTO/MMH arrangement also leads to more drastic combustion and higher wall temperature. Reducing the distance between cooling jets and the wall of the combustion chamber leads to earlier protection on the wall of the combustion chamber, while it does not alleviate the high temperature flow near impinging jets.