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research-article

Rotordynamic Forces Acting on a Two-Stage Inducer

[+] Author and Article Information
Naoki Nagao

Research and Development Directorate, Japan Aerospace Exploration Agency, 2-1-1 Sengen, Tsukuba, Ibaraki 305-8505, Japan
nagao.naoki@jaxa.jp

Katsuji Nagaura

Operations department, Foundation for Promotion of Japanese Aero-Space Technology, 1 Kimigaya Aza Koganezawa, Kakuda, Miyagi 981-1525, Japan
nagaura.katsuji@jaxa.jp

Tsutomu Tamura

Operations department, Foundation for Promotion of Japanese Aero-Space Technology, 1 Kimigaya Aza Koganezawa, Kakuda, Miyagi 981-1525, Japan
tamura.tsutomu@jaxa.jp

Satoshi Hasegawa

Research and Development Directorate, Japan Aerospace Exploration Agency, 1 Kimigaya Aza Koganezawa, Kakuda, Miyagi 981-1525, Japan
hasegawa.satoshi@jaxa.jp

Masaharu Uchiumi

Research and Development Directorate, Japan Aerospace Exploration Agency, 1 Kimigaya Aza Koganezawa, Kakuda, Miyagi 981-1525, Japan
uchiumi.masaharu@jaxa.jp

1Corresponding author.

ASME doi:10.1115/1.4037986 History: Received September 09, 2016; Revised May 15, 2017

Abstract

Rocket turbopumps sometimes experience self-excited shaft vibration due to rotordynamic forces. To prevent this vibration, a key step is to establish a method to measure and evaluate the rotordynamic forces that act on turbopump components. In this study, we measured rotordynamic forces acting on a two-stage inducer using a rotordynamic test stand developed in 2012 at Kakuda Space Center. In noncavitating conditions, we didn't observe strong non-linearities in rotordynamic forces in the inducer at low flow-rate conditions. The results of the pressure fluctuation on the inducer showed that rotordynamic forces were mainly excited in the second stage of the inducer. In cavitating conditions, we found that there is no strong nonlinearity between cavitating rotordynamic forces and the whirling frequency ratio in the inducer. These results show the robustness of the rotordynamic forces acting on the inducer against the flow rate and cavitation.

Copyright (c) 2017 by ASME
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