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. By using this model, the frequency of the cavitation surge decreases as the inlet pressure decreases. However, we obtained interesting experimental results in which the cavitation surge frequency varied disconnectedly. Therefore, we considered the factor of fluid compression employed one-dimensional analysis applying an acoustic model, combining the inlet pipe with the sonic velocity of liquid oxygen. Consequently, the analytical results qualitatively corresponded with the experimental results. In addition, an actual liquid rocket propulsion system is usually equipped with a Pogo suppression device (PSD), which is a kind of accumulator with a hydraulic compliance, upstream of a liquid oxidizer turbopump. We modified the analytical model to include the effect of this PSD and compared the analytical results with the experimental results. It was found that the frequency of cavitation surge basically became the Helmholtz frequency, defined by the cavitation compliance and the length of pipe between the PSD and the turbopump. And when the frequency of cavitation surge coincided with one of the acoustic resonance frequencies of the inlet pipe, the cavitation surge was strongly excited.
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ASME 2010 3rd Joint US-European Fluids Engineering Summer Meeting collocated with 8th International Conference on Nanochannels, Microchannels, and Minichannels
August 1–5, 2010
Montreal, Quebec, Canada
Conference Sponsors:
- Fluids Engineering Division
ISBN:
978-0-7918-4948-4
PROCEEDINGS PAPER
Analysis of Cavitation Surge Considering the Acoustic Effect of the Inlet Line in a Rocket Engine Turbopump Available to Purchase
Hideaki Nanri,
Hideaki Nanri
Japan Aerospace Exploration Agency, Kakuda, Miyagi, Japan
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Naoki Tani,
Naoki Tani
Japan Aerospace Exploration Agency, Tsukuba, Ibaraki, Japan
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Hiroki Kannan,
Hiroki Kannan
Japan Aerospace Exploration Agency, Kakuda, Miyagi, Japan
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Yoshiki Yoshida
Yoshiki Yoshida
Japan Aerospace Exploration Agency, Kakuda, Miyagi, Japan
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Hideaki Nanri
Japan Aerospace Exploration Agency, Kakuda, Miyagi, Japan
Naoki Tani
Japan Aerospace Exploration Agency, Tsukuba, Ibaraki, Japan
Hiroki Kannan
Japan Aerospace Exploration Agency, Kakuda, Miyagi, Japan
Yoshiki Yoshida
Japan Aerospace Exploration Agency, Kakuda, Miyagi, Japan
Paper No:
FEDSM-ICNMM2010-30434, pp. 957-964; 8 pages
Published Online:
March 1, 2011
Citation
Nanri, H, Tani, N, Kannan, H, & Yoshida, Y. "Analysis of Cavitation Surge Considering the Acoustic Effect of the Inlet Line in a Rocket Engine Turbopump." Proceedings of the ASME 2010 3rd Joint US-European Fluids Engineering Summer Meeting collocated with 8th International Conference on Nanochannels, Microchannels, and Minichannels. ASME 2010 3rd Joint US-European Fluids Engineering Summer Meeting: Volume 1, Symposia – Parts A, B, and C. Montreal, Quebec, Canada. August 1–5, 2010. pp. 957-964. ASME. https://doi.org/10.1115/FEDSM-ICNMM2010-30434
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