JAXA Supercomputer System Annual Report April 2016-March 2017

Report Number: R16E0023

• Responsible Representative: Toshio Nishizawa(Aeronautical Technology Directorate, aFJR project team)
• Contact Information: Shunji Enomoto(eno@chofu.jaxa.jp)
• Members: Junichi Kazawa, Shunji Enomoto, Toshio Nishizawa, Susumu Kato, Kenshi Yamashita
• Subject Category: Aviation(Aircraft engine)

Abstract

The purpose of aFJR project is to advance research on jet engine component technologies so that Japanese manufacturers can join more effectively in international joint-development projects on next-generation jet engines. To compensate for increasing fan diameter, we are developing lightweight fan blades that have higher aerodynamic efficiency by applying advanced simulation technology and composite materials evaluation technology.

Goal

Please refer 'aFJR (Advanced Fan Jet Research) project | ECAT - Environment-Conscious Aircraft Technology Program | Aeronautical Technology Directorate'.

Objective

Please refer 'aFJR (Advanced Fan Jet Research) project | ECAT - Environment-Conscious Aircraft Technology Program | Aeronautical Technology Directorate'.

References and Links

Please refer 'aFJR (Advanced Fan Jet Research) project | ECAT - Environment-Conscious Aircraft Technology Program | Aeronautical Technology Directorate'.

Use of the Supercomputer

For the development of high efficiency laminar flow fan blade technology in aFJR project, we develop laminar-turbulent transition simulation technology, and evaluate the blade designed for the verification test.

Necessity of the Supercomputer

Laminar-turbulent transition simulation is useful for increasing the certainty of aFJR project and super-computers are required for this type of transition simulation.

Achievements of the Year

A Large-Eddy Simulation code, UPACS-LES, is used to simulate laminar-turbulent transition process around a fan blade. Fine computational grids are set for the boundary layer region from the leading edge to 0.2 chord length position. Random disturbance was added near the leading edge. Fig. 1 shows Mach number distribution. Boundary layer transition can be seen around 0.13 chord length position. Fig.2 shows instantaneous velocity fluctuation component. Small eddies are generated near the leading edge, and grow gradually until transition occurs. These result shows the possibility to simulate laminar-turbulent transition using the LES code.

Fig.1:Mach number

Fig.2:Velocity fluctuation component

Publications

N/A

Computational Information

• Parallelization Methods: Hybrid Parallelization
• Process Parallelization Methods: MPI
• Thread Parallelization Methods: OpenMP
• Number of Processes: 72
• Number of Threads per Process: 2
• Number of Nodes Used: 12
• Elapsed Time per Case (Hours): 270
• Number of Cases: 12

Resources Used

Total Amount of Virtual Cost(Yen): 8,539,897

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