JAXA Special Publication JAXA-SP-19-003E

Combustion analysis technology
Report Number: R18EG3212
Subject Category: Research and Development
URL: https://www.jss.jaxa.jp/en/ar/e2018/9143/
Responsible Representative
Eiji Shima, Director, Research and Development Directorate, Research Unit III
Contact Information
Takanori Haga, Research and Development Directorate, Research Unit III (haga.takanori@jaxa.jp)
Members
Takayuki Ito, Ryoji Takaki, Seiji Tsutsumi, Hiroyuki Ito, Taro Shimizu, Junya Aono, Takanori Haga, Yuhi Morii,Masaharu Abe, Masayuki Kakehi, Mikiroh Motoe, Manabu Hisida, Hideyo Negishi, Yoichi Ohnishi, MikiNishimoto, 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, Mayu Matsumoto, Masashi Toyama, Kei Nishimura, Daiki
Muto, Nozomu Kanno, Takeshi Watanabe
Abstract
To capture the unsteady phenomena in the liquid rocket engine, combustion large eddy simulations (LES) are
carried out, and this evaluation tool is validated by comparing with a sub-scale test.
Ref. URL: http://www.kenkai.jaxa.jp/eng/research/software/software.html
Reasons for using JSS2
Since the flow and combustion in rocket chambers are in a turbulent state and have nonstationary characteristics,
LES analysis is essential. Even in this verification target, analysis calculation of about several million steps isrequired for grid of tens of millions of cells, so it is impossible to achieve the target without using supercomputer.
Achievements of the Year
1. Towards the improvement of reacting flow simulations, Large eddy simulation of a methane/oxygen multielement subscale combustion chamber is performed. JAXA/JEDI in-house CFD solver LS-FLOW is used in thepresent simulation. For combustion modeling, the laminar flamelet approach is applied. The number of grid point
is approximately 0.24 billion. Figure 1 shows the instantaneous temperature contour. The present simulation
captures the complex turbulent combustion field including mixing and combustion, and subsequent flame
interaction structures.
2. A fully conjugated combustion and heat transfer simulation was performed and validated for GCH4/GO2
combustion with a water-cooled calorimeter chamber. The employed numerical methodology was based on the－242－

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three-dimensional Reynolds-averaged Navier-Stokes simulation in which the injection and combustion processesof propellants on the hot-gas side, heat conduction in the chamber wall, and cooling channel flows were considered.
Figure 2 shows the temperature distributions of the (a) non-coupled and (b) coupled simulation results. In thecombustion chamber, the high temperature region, which corresponds to the diffusion flame, extends gradually.
The low temperature region, which corresponds to the GOX core, narrows gradually. The heat of combustion gas
is transferred to the wall, then conducted through the chamber wall and then into the cooling water in therectangular and circular tubes.

Fig. 1: Instantaneous temperature contours.

Fig. 2: Comparison of temperature contours between (a) non-coupled and (b) coupled simulation.

Publications- Non peer-reviewed papers
1) Daiki Muto, Yu Daimon, Taro Shimizu, and Hideyo Negishi, A wall model including chemical effects forpredicting wall heat transfer in combustion chambers, 56th Symposium (Japanese) on Combustion, B331, 2018
(in Japanese).
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JAXA Special Publication JAXA-SP-19-003E

2) Daiki Muto, Yu Daimon, Taro Shimizu, and Hideyo Negishi, Wall modeling of reacting turbulent flow andheat transfer in liquid rocket engines, 2018 Joint Propulsion Conference, AIAA Propulsion and Energy Forum,AIAA 2018-4870, 2018.
3) Daiki Muto, Yu Daimon, Taro Shimizu, and Hideyo Negishi, Wall-modeled large eddy simulations ofturbulent heat transfer at supercritical pressures, 55th National Heat Transfer Symposium of Japan, J322, 2018 (inJapanese).
4) Yu Daimon, Hideyo Negishi, Simona Silvestri, Oskar J. Haidn, “Conjugated Combustion and Heat Transfer
Simulation for a 7 element GOX/GCH4 Rocket Combustor,” AIAA 2018-4553, Joint Propulsion Conference,
2018

Usage of JSS2
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Computational Information
Process Parallelization Methods

MPI

Thread Parallelization Methods

N/A

Number of Processes

3200 - 6400

Elapsed Time per Case

1500 Hour (s)Resources UsedFraction of Usage in Total Resources*1 (%): 5.46
Details
Computational Resources
System Name

Amount of Core Time(core x hours)

Fraction of Usage*2 (%)

SORA-MA

49,699,070.75

6.08

SORA-PP

71,716.79

0.57

SORA-LM

5,147.93

2.40

SORA-TPP

16,237.54

1.19

File System Resources
File System Name

Storage Assigned (GiB)

Fraction of Usage*2 (%)/home

5,896.12

6.10

/data

114,509.95

2.02/ltmp

19,865.96

1.70

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Archiver Resources
Archiver Name

Storage Used (TiB)

J-SPACE

Fraction of Usage*2 (%)
119.91

4.20*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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