JAXA Special Publication JAXA-SP-19-003E

Numerical Simulation of Rocket Turbopumps
Report Number: R18EG3214
Subject Category: Research and Development
URL: https://www.jss.jaxa.jp/en/ar/e2018/9145/
Responsible Representative
Eiji Shima, Research and Development Directorate, Research Unit III
Contact Information
Hideyo Negishi (negishi.hideyo@jaxa.jp)
Members
Takayuki Ito, Hideyo Negishi, Yoichi Ohnishi, Miki Nishimoto, Yu Daimon, Ashvin Hosangadi, Masaaki Ino,
Osamu Fukasawa, Shinji Ohno, Andrea Zambon, Takenori Nakajima, Takashi Amemiya, Yutaka Umemura,
Hironori Fujiwara, Hiroumi Tani, Keiichiro Fujimoto, Tetsufumi Ohmaru, Akiko Kotani, Taroh Fukuda, MayuMatsumoto, Masashi Toyama, Daiki Muto, Susumu Teramoto, Takahiko Toki
Abstract
Turbopumps are still one of key components in liquid rocket engine development in terms of cost, time, andrisks. Furthermore, a turbopump itself is a complex system consisting of sub-components such as pump, turbine,bearing, balance piston, sealing and so on. From numerical simulation technology point of view, there is notechnology able to evaluate performance of an entire turbopump system in the world. And also, accuracy andfidelity of numerical simulation technology for sub-components are still poor and cannot be used to reduce thenumber of experiments. Therefore, experiments are indispensable to evalute feasibility of considered design inengine development.
In this study, numerical simulation technology of an entire turbopump system applicable in engine design phasehas been developed enhancing accuracy and fedelity. We are aiming at reducing cost and time for future engine
development by making full use of our numerical simulation to reduce the number of experiments. And also,innovative design methodology for higher performance rocket turbopumps has been investigated by using ournumerical simulations.
Ref. URL: http://stage.tksc.jaxa.jp/jedi/simul/index.html
Reasons for using JSS2
In this study, JSS2 has been used because of the following reasons:(1) To make it possible to perform large-scale numerical simulations with high accuracy and fidelity(2) To produce a lot of computed results on time within limited short period of time under JAXA’s rocketdevelopment(3) To ensure information security about rocket-related technical information in JAXA’s network only－260－

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JAXA Supercomputer System Annual Report (April 2018-March 2019)

Achievements of the YearIn fiscal year 2018, we succeded in performing three-dimensional compressible URANS simulation of liquidrocket hydrogen pump considering cryogenic physical properties based on NIST database (See Fig. 1). It was
confirmed that computed pressures in the pump agreed well with experimental results within 4% error. The
developed numerical simulation approach has been employed in the booster engine LE-9 development of H3
launch vehicle.

Fig. 1: Computed result of liquid rocket hydrogen pump (pressure distribution)

Publications- Peer-reviewed papers(1) Negishi, H., et al., “Investigation on Flow Field Characteristics of a Liquid Rocket Open Impeller Based on
Compressible URANS Simulation”, Vol. 46, No. 12, Dec. 2018, pp. 705-714.
- Non peer-reviewed papers(1) Negishi, H., et al., “Computational analysis of flow field characteristics of a liquid rocket unshrouded
impeller,” 29th IAHR Symposium on Hydraulic Machinery and Systems, IAHR2018-422, Kyoto, Sep. 16-21,2018.
(2) Negishi, H., et al., “Thermal-flow Field Characteristics of a Liquid Hydrogen Open Impeller (Influence ofFlow Coefficient),” 80th Turbomachinery Society of Japan, Academic conference, Oct. 2018.

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JAXA Special Publication JAXA-SP-19-003E

Usage of JSS2


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Computational Information
Process Parallelization Methods

MPI

Thread Parallelization Methods

FLAT

Number of Processes

128 - 6400

Elapsed Time per Case

300 Hour (s)Resources Used
Fraction of Usage in Total Resources*1 (%): 0.42Details
Computational Resources
System Name

Amount of Core Time(core x hours)

Fraction of Usage*2 (%)

SORA-MA

3,576,887.13

0.44

SORA-PP

7,545.15

0.06

SORA-LM

1,114.21

0.52

SORA-TPP

19.56

0.00

File System Resources
File System Name

Storage Assigned (GiB)

Fraction of Usage*2 (%)/home

495.16

0.51

/data

31,784.03

0.56

/ltmp

16,295.88

1.40

Archiver Resources
Archiver Name

Storage Used (TiB)

J-SPACE

Fraction of Usage*2 (%)
2.61

0.09

*1: Fraction of Usage in Total Resources: Weighted average of three resource types (Computing, File System,and Archiver).
*2: Fraction of Usage: Percentage of usage relative to each resource used in one year.

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