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Investigation of internal flow of aircraft combustor for En-Core Project.

JAXA Supercomputer System Annual Report April 2019-March 2020

Report Number: R19EA0714

Subject Category: Aeronautical Technology

PDF available here

  • Responsible Representative: Mitsumasa Makida(JAXA, Aeronautical Technology Directorate)
  • Contact Information: Mitsumasa Makida(Aeronautical Technology Directorate)(makida.mitsumasa@jaxa.jp)
  • Members: Mitsumasa Makida, Naoki Nakamura, Takashi Ishiyama

Abstract

In the development process of aircraft combustors, air mass flow distribution between fuel nozzles, dilution and cooling air holes on the liner effects performances of combustors. So it is important to understand the internal flow and estimate the mass flow distribution. In this research, we conduct cold-flow simulations of internal flow inside the combustor which faithfully simulates the configuration of practical combustor. Then we aim to develop methods to analyze aerodynamic performance of combustors such as air mass flow distribution with high accuracy.

Reference URL

N/A

Reasons and benefits of using JAXA Supercomputer System

It is important to do parametric case study with slightly different geometry, and each case needs large scale simulation. To conduct such simulation effectively, we need the super computer with high parallelization efficiency.

Achievements of the Year

In this fiscal year, we conducted cold-flow simulations for a single-sector combustor. These simulations aimed to estimate the effect of the angle of pilot swirlers on the internal flow of the combustor. Fig.1 shows the total view of the combustor, Fig.2 shows the geometry of the fuel nozzle and pilot swirlers (angles of pilot1 and pilot2 are 55- and 45-degree respectively), and Fig.3 shows calculation grids of the combustion chamber and the fuel nozzle. And also, as examples of calculation result, Fig.4 shows contour of y-momentum on y=0 cross section. Calculations were also conducted for angles of pilot1 and pilot2 of 50- and 40-degree cases. To do parametric studies by changing minimum parts of combustor configuration, the overset boundary method, in which corresponding parts can be changed, is effective.

Annual Reoprt Figures for 2019

Fig.1: Total view of combustor

 

Annual Reoprt Figures for 2019

Fig.2: Geometry of fuel nozzle and pilot swirlers

 

Annual Reoprt Figures for 2019

Fig.3: Calculation grids of combustion chamber and fuel nozzle

 

Annual Reoprt Figures for 2019

Fig.4: Contour of y-momentum on y=0 cross section

 

Publications

N/A

Usage of JSS2

Computational Information

  • Process Parallelization Methods: MPI
  • Thread Parallelization Methods: Automatic Parallelization
  • Number of Processes: 64
  • Elapsed Time per Case: 250 Hour(s)

Resources Used

 

Fraction of Usage in Total Resources*1(%): 0.09

 

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 655,339.74 0.08
SORA-PP 26,183.96 0.17
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 82.81 0.07
/data 7,402.33 0.13
/ltmp 1,450.89 0.12

 

Archiver Resources
Archiver Name Storage Used
(TiB)
Fraction of Usage*2(%)
J-SPACE 1.85 0.05

*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