Characterization of cryogenic injection at supercritical pressure
Characterization of cryogenic injection at supercritical pressure
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DOI：
10.2514/6.2001-3275
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发表时间：
2001-07
期刊：
影响因子：
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通讯作者：
W. Mayer;J. Telaar;R. Branam;G. Schneider;J. Hussong
中科院分区：
文献类型：
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作者：
W. Mayer;J. Telaar;R. Branam;G. Schneider;J. Hussong
了解火箭腔室的复杂环境需要对喷射现象有很好的了解。了解喷射现象使火箭设计师能够使用节省时间和成本的建模工具来设计更高性能的火箭发动机。火箭发动机的性能高度依赖于燃烧室内的喷射过程。这个项目着眼于注入流体低温氮的超临界状态下的注入过程，以便更好地了解当今火箭发动机的实际情况。该研究考虑了在两种不同注入速度和温度下的4.0至6.0 MPa的测试条件。在不同的测试条件下，将拉曼成像和阴影成像的实验数据与计算模型进行了比较。测试数据可以比较密度、长度尺度和射流扩散角。计算结果较好地验证了计算模型，与经典理论相吻合。该协议允许进一步使用模型来预测这些操作条件下的注入行为。此外，利用计算模型对不同测试用例进行了进一步的比较，以考虑压力、速度和温度变化对低温射流的影响。
Understanding the Complex environment of the rocket chamber involves good knowledge of the injection phenomena. Understanding the injection phenomena allows the rocket designer to employ time and cost saving modeling tools to design a higher performance rocket engine. The rocket engine performance is highly dependent on the injection processes within the chamber. This project looked at injection processes in the supercritical regime of the injected fluid, cryogenic nitrogen, in order to better understand realistic conditions in the rocket engines of today. The investigation considered test conditions from 4.0 to 6.0 MPa at two different injection velocities and temperatures. Experimental data taken by Raman imaging and Shadowgraphy were compared to computational models for these various test conditions. The test data allows comparisons of density, length scales and jet spreading angles. The results validate the computational models fairly well and agree with classical theory.This agreement allows further use of the models to predict injection behavior under these operating conditions. Also, further comparisons were made between the various test cases using the computational models to consider the effects of pressure, velocity and temperature variations on the cryogenic jet.