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Research on combustor simulation

JAXA Supercomputer System Annual Report April 2019-March 2020

Report Number: R19ETET05

Subject Category: Skills Acquisition System

PDF available here

  • Responsible Representative: AOYAMA Takashi, Director, Aeronautical Technology Directorate, Numerical Simulation Research Unit
  • Contact Information: Himeko Yamamoto(himeko@toki.waseda.jp)
  • Members: Himeko Yamamoto

Abstract

For the development of a aircraft engine combustor with high environmental compatibility, we develop the combustion calculation methods that can reproduce the pressure propagation and chemical reaction with practical calculation cost. In addition, numerical simulations of the DLR scramjet test-engine combustor are conducted to evaluate these proposed methods.

Reference URL

N/A

Reasons and benefits of using JAXA Supercomputer System

It is necessary to use supercomputer to conduct development and verification of the combustion calculation methods.

Achievements of the Year

The laminar flamelet model, which is a tabulated chemistry method, is effective for reducing the inflexibility of numerical simulation of combustion. However, the recently proposed compressible flamelet model, which is applicable to compressible flow, has some problems of computational performance related to increased complication of the flamelet table and the pressure-calculation process. To address these problems of the conventional method (form0-lerp) of the compressible flamelet model which uses conventional formulation (form0) and flamelet table with linear interpolation (Lerp), we propose two formulations, namely form1 and form2. Form1 has the advantage of making the spatial gradient calculation of each chemical species mass fraction more efficient. Form2 has the advantage of eliminating the calculation procedure that depends on the number of chemical species. We also propose methods of utilizing artificial neural network (ANN) that produce synergistic effects with these formulations. In addition, to evaluate two particularly effective methods, form2-lerp and form2-ann, numerical simulations (Fig.2, Fig.3) based on the DLR scramjet test-engine combustor (Fig.1) are conducted.

Annual Reoprt Figures for 2019

Fig.1: DLR scramjet test-engine combustor

 

Annual Reoprt Figures for 2019

Fig.2: Axial velocity distribution (experiment, form0-lerp, form2-lerp, form2-ann)

 

Annual Reoprt Figures for 2019

Fig.3: Temperature distribution (experiment, form0-lerp, form2-lerp, form2-ann)

 

Publications

– Peer-reviewed papers

Himeko Yamamoto, Rui Toyonaga, Yusuke Komatsu, Koki Kabayama, Yasuhiro Mizobuchi, Tetsuya Sato, “Improved Methods of Laminar Flamelet Model for Compressible Flow”, AIAA Journal, American Institute of Aeronautics and Astronautics (2020.3, accepted)

Usage of JSS2

Computational Information

  • Process Parallelization Methods: MPI
  • Thread Parallelization Methods: N/A
  • Number of Processes: 2 – 1024
  • Elapsed Time per Case: 120 Hour(s)

Resources Used

 

Fraction of Usage in Total Resources*1(%): 0.11

 

Details

Please refer to System Configuration of JSS2 for the system configuration and major specifications of JSS2.

Computational Resources
System Name Amount of Core Time
(core x hours)
Fraction of Usage*2(%)
SORA-MA 877,071.08 0.11
SORA-PP 7,887.09 0.05
SORA-LM 0.00 0.00
SORA-TPP 0.00 0.00

 

File System Resources
File System Name Storage Assigned
(GiB)
Fraction of Usage*2(%)
/home 476.84 0.40
/data 39,062.52 0.67
/ltmp 1,953.13 0.17

 

Archiver Resources
Archiver Name Storage Used
(TiB)
Fraction of Usage*2(%)
J-SPACE 0.48 0.01

*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.

JAXA Supercomputer System Annual Report April 2019-March 2020