Research on combustor simulation
JAXA Supercomputer System Annual Report April 2018-March 2019
Report Number: R18ETET05
Subject Category: Skills Acquisition System
- Responsible Representative: Takashi Aoyama, 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 method that can reproduce the pressure propagation and chemical reaction with practical calculation cost. In addition, a verification calculation of this calculation method is conducted on the scramjet test engine of DLR.
Reference URL
N/A
Reasons for using JSS2
It is necessary to use supercomputer to conduct development and verification of the combustion calculation method.
Achievements of the Year
The laminar flamelet model, which is a tabulated-chemistry calculation 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 related to increased complication of the flamelet table and the pressure-calculation process. To address these problems of the conventional formulation of the compressible flamelet model (method A), we propose two formulations (methods B and C). Method B improves the calculation speed by choosing thermochemical properties of a multicomponent gas and a part of the subgrid-scale term as outputs of the flamelet tables. Method C reduces the memory usage of the flamelet tables drastically by applying the artificial neural networks to the formulation of method B. To evaluate these methods in an actual combustion field, we conducted numerical simulations (Fig.2, Fig.3) based on the German Aerospace Center scramjet test-engine combustor(Fig.1).
Publications
– Peer-reviewed papers
Himeko Yamamoto, Rui Toyonaga, Yusuke Komatsu, Koki Kabayama, Yasuhiro Mizobuchi, Tetsuya Sato, “Improvement of Laminar Flamelet Moedl for Compressible Flows Using Artificial Neural Network”, Aerospace Technology Japan (Online Journal, In Japanese), Japan Society for Aeronautical and Space Sciences (2018.11, accepted)
– Poster Presentations
Himeko Yamamoto, Rui Toyonaga, Yusuke Komatsu, Koki Kabayama, Yasuhiro Mizobuchi, Tetsuya Sato, “Generation of Thermochemical Database Using Artificial Neural Network For Compressible Flamelet Approach”, International Symposium on Combustion, WiPP session, Ireland, 2018.8
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(%): 0.46
Details
Please refer to System Configuration of JSS2 for the system configuration and major specifications of JSS2.
System Name | Amount of Core Time(core x hours) | Fraction of Usage*2(%) |
---|---|---|
SORA-MA | 3,869,594.74 | 0.47 |
SORA-PP | 31,509.90 | 0.25 |
SORA-LM | 0.00 | 0.00 |
SORA-TPP | 0.00 | 0.00 |
File System Name | Storage Assigned(GiB) | Fraction of Usage*2(%) |
---|---|---|
/home | 476.84 | 0.49 |
/data | 39,062.52 | 0.69 |
/ltmp | 1,953.13 | 0.17 |
Archiver Name | Storage Used(TiB) | Fraction of Usage*2(%) |
---|---|---|
J-SPACE | 0.48 | 0.02 |
*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 2018-March 2019