JAXA Supercomputer System Annual Report April 2016-March 2017

Report Number: R16E0004

• Responsible Representative: Toshiya Nakamura(Aeronautical Technology Directorate, Next Generation Aeronautical Innovation Hub Center)
• Contact Information: Mitsumasa Makida(makida@chofu.jaxa.jp)
• Members: Mitsumasa Makida, Naoki Nakamura
• Subject Category: Aviation(Aircraft engine)

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.

Goal

This research aims to develop a cold-flow simulation code which can estimate internal flow of aircraft combustor with high accuracy.

Objective

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.

References and Links

Please refer ‘Green engine technology | ECAT – Environment-Conscious Aircraft Technology Program | Aeronautical Technology Directorate‘.

Use of the Supercomputer

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

Necessity of the Supercomputer

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 multi-sector combustor which consisted of three single-sector two-stage premixed combustors. These simulations aimed to estimate the effect of side walls on the internal flow of the combustor. After this, we will conduct parametric case study with different combustor configurations aiming to select good configuration, and utilize the information for the development of combustors.

Fig.1:Configuration and calculation grids of combustor(Total configuration viewed from inlet(left), Calculation grids on downstream wall of fuel nozzles(right))

Fig.2:Stream lines from fuel nozzles

Publications

N/A

Computational Information

• Parallelization Methods: Hybrid Parallelization
• Process Parallelization Methods: MPI
• Thread Parallelization Methods: Automatic Parallelization
• Number of Processes: 128
• Number of Threads per Process: 4
• Number of Nodes Used: 16
• Elapsed Time per Case (Hours): 250
• Number of Cases: 1

Resources Used

Total Amount of Virtual Cost(Yen): 2,699,328

Breakdown List by Resources

Note: Virtual Cost=amount of cost, using the unit price list of JAXA Facility Utilization program(2016)

JAXA Supercomputer System Annual Report April 2016-March 2017