Axial compressor stall
Ultra-fast direct simulation of stall inception in NASA Stage 37
- 32 NVIDIA P100 GPUs
- 12 hours per simulation (2 hours per rotor revolution)
- 60 million grid nodes
Turbostream enables stall inception simulations to take place within realistic design timescales. This full-annulus URANS simulation of NASA Stage 37 was completed in 12 hours. It reveals that stall inception occurs due to the blockage caused by large rotor tip corner separations - information that could be used to improve the design.
Multiple award-winning publications have shown that Turbostream can accurately predict this process in a variety of machines:
Origins and Structure of Spike-Type Rotating Stall (2015)
Pullan, G., Young, A. M., Day, I. J, Greitzer, E. M. and Spakovszky, Z. S.
Journal of Turbomachinery, Vol. 137 (051007)
2012 ASME Gas Turbine Award
The Role of Tip Leakage Flow in Spike-Type Rotating Stall Inception (2017)
Hewkin-Smith, M., Pullan, G., Grimshawm S. D., Day, I. J, Greitzer, E. M. and Spakovszky, Z. S.
Proceedings of ASME Turbo Expo 2017, GT2017-63655
2017 ASME Turbomachinery Committee Best Paper Award
Stall Inception in Low Pressure Ratio Fans (2018)
Kim, S., Pullan, G., Hall, C. A., Grewe, R. P., Wilson, M. J., Gunn, E. J.
Proceedings of ASME Turbo Expo 2018, GT2018-75153
Stall inception has previously been studied using experimental rig tests or one-off, research-intensive CFD. Using Turbostream, it can now be carried out as a routine part of the 3D design process.