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Study on future space transportation system – combined cycle engine (JAXA-Tohoku Univ. collaborative course)

JAXA Supercomputer System Annual Report February 2023-January 2024

Report Number: R23ECWU07

Subject Category: Cooperative Graduate School System

PDF available here

  • Responsible Representative: Sadatake Tomioka, Associate Principal Researcher, Research and Development Directorate, 4th Unit.
  • Contact Information: Sadatake Tomioka (RInsertHereD directorate, 4th Research Unit)(tomioka.sadatake@jaxa.jp)
  • Members: Sadatake Tomioka, Hironobu Nishiguchi, Ryota Ito

Abstract

Fully reusable launch vehicle will reduce the transportation cost and increase the space launch demands. Introduction of airbreathing engine will afford system weigth penalty necessary to realise reuablity by reducing on-board oxygen consumption. Enabling prediction of scramjet engine and scramjet-rocket combined cycle engine performance is prime target of the present study, especially on reacting flow within combustor with presence of separation to evaluate combustion control methods.

Reference URL

N/A

Reasons and benefits of using JAXA Supercomputer System

In combustors, supersonic / subsonic flows are mixed and chemical reaction takes place, and LES or LES/RANS Hybrid methods are found to be promissing. Huge calculation resource is required for such calculations, and JSS matchs the requirement for prompt output .

Achievements of the Year

Effects of fuel injection angle combustion phenomena were investigated. Either upstream oriented injector or perpendicular injector was installed at upstream of a flame-holding cavity. LES/RANS hybrid calculation was applied for unsteady calculation, and so-called cavity flame, i.e, flame propegated from the anchor flame within the flame-holding cavity, was observed for the perpendicular injection, while so-called jet-wake flame, i.e., flame attached to teh fuel jet, was observed for the upstream injection (Fig. 1). THis difference in flame structure as well as the mixing enhancement due to aerodynamic effect resulted in higher mixing efficiency and higher combustion efficiency (Fig. 2).

Annual Reoprt Figures for 2023

Fig.1: Instantaneous (left) and averaged (right) static temperature contour with perpendicular injection (upper) and upstream injection (lower).

 

Annual Reoprt Figures for 2023

Fig.2: Mixing and combustion efficiencies distributions

 

Publications

– Peer-reviewed papers

H. Nishiguchi, et al., ‘Unsteady Numerical Analysis of a Dual-Mode Scramjet Combustor with a Cavity,’ Trans. JSASS, 66 (2023), pp. 103-117.

Usage of JSS

Computational Information

  • Process Parallelization Methods: MPI
  • Thread Parallelization Methods: N/A
  • Number of Processes: 32 – 9600
  • Elapsed Time per Case: 60 Hour(s)

JSS3 Resources Used

 

Fraction of Usage in Total Resources*1(%): 0.65

 

Details

Please refer to System Configuration of JSS3 for the system configuration and major specifications of JSS3.

Computational Resources
System Name CPU Resources Used
(Core x Hours)
Fraction of Usage*2(%)
TOKI-SORA 17121085.13 0.77
TOKI-ST 76257.42 0.08
TOKI-GP 0.00 0.00
TOKI-XM 0.00 0.00
TOKI-LM 1801.89 0.14
TOKI-TST 525.51 0.01
TOKI-TGP 0.00 0.00
TOKI-TLM 0.00 0.00

 

File System Resources
File System Name Storage Assigned
(GiB)
Fraction of Usage*2(%)
/home 1350.00 1.12
/data and /data2 58851.00 0.36
/ssd 6748.00 0.64

 

Archiver Resources
Archiver Name Storage Used
(TiB)
Fraction of Usage*2(%)
J-SPACE 0.00 0.00

*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.

 

ISV Software Licenses Used

ISV Software Licenses Resources
ISV Software Licenses Used
(Hours)
Fraction of Usage*2(%)
ISV Software Licenses
(Total)
1383.02 0.62

*2: Fraction of Usage:Percentage of usage relative to each resource used in one year.

JAXA Supercomputer System Annual Report February 2023-January 2024