Analysis of Acoustic Cavitation Surge in a Rocket Engine Turbopump
Analysis of Acoustic Cavitation Surge in a Rocket Engine Turbopump
复制标题
火箭发动机涡轮泵声空化喘振分析
DOI：
10.1155/2010/717013
复制
发表时间：
2010
影响因子：
0.9
通讯作者：
Y. Yoshida
中科院分区：
文献类型：
--
作者：
Hideaki Nanri;Hiroki Kannan;N. Tani;Y. Yoshida
在液体火箭发动机中，涡轮泵导轮在低进气压力下工作时，导轮中的空化现象有时会导致不稳定现象。空化喘振(自振)是一种不稳定现象，主要基于假定不可压缩流动的惯性模型来讨论。当采用该模型时，空化喘振频率随着涡轮泵进口压力的降低而不断减小。然而，我们得到了一个有趣的实验结果，其中空化浪涌的频率不连续地变化。因此，我们采用了基于声学模型的一维分析，在该模型中，流体是可压缩的。分析结果与实验结果定性吻合。
In a liquid rocket engine, cavitation in an inducer of a turbopump sometimes causes instability phenomena when the inducer is operated at low inlet pressure. Cavitation surge (auto-oscillation), one such instability phenomenon, has been discussed mainly based on an inertia model assuming incompressible flow. When this model is used, the frequency of the cavitation surge decreases continuously as the inlet pressure of the turbopump decreases. However, we obtained an interesting experimental result in which the frequency of cavitation surge varied discontinuously. Therefore, we employed one-dimensional analysis based on an acoustic model in which the fluid is assumed to be compressible. The analytical result qualitatively corresponded with the experimental result.