NASA SBIR 2020-I Solicitation

Proposal Summary

 20-1- A1.07-6328
 Propulsion Efficiency - Turbomachinery Technology for High Power Density Turbine-Engines
 A GPU-Accelerated Full-Wheel Multi-Stage Turbomachinery Flow Solver
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
CASCADE Technologies, Inc.
2445 Faber Place, Suite 100
Palo Alto, CA 94303
(650) 521-0243

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Kan Wang
2445 Faber Place, Suite 100 Palo Alto, CA 94303 - 3346
(574) 309-5898

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Guillaume Bres
2445 Faber Place, Suite 100 Palo Alto, CA 94303 - 3346
(650) 521-0243
Estimated Technology Readiness Level (TRL) :
Begin: 4
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

Cascade will validate the CPU-based moving mesh solver using NASA stage 37, high-pressure-ratio stage of an axial core compressor developed by NASA in late 1970’s. Cascade will port its moving version of the large-eddy simulation (LES) flow solver charLES to GPU-accelerated architectures. The moving mesh solver uses the same Voronoi diagram-based meshing strategy as the static mesh solver, however the meshing is now integrated with the solver to allow local regeneration of the Voronoi diagram when points are in relative motion. The current implementation for traditional architectures uses a conservative space-time formulation that allows for complex motions including collisions and full contact. Since complex motions and thus complex solver treatments are not required for the relatively simple solid-body rotational motion of turbomachinery, the development will be staged by first porting the Voronoi point search and cutting algorithms to the GPU, and simply re-cutting the interface cells in each time step, and updating the communication pattern. The entire algorithm can remain fully explicit, utilizing essentially the same solver as the static charLES for accelerated architectures. In regards to specific architectures, the static accelerated charLES is written in both CUDA and HIP, allowing us to leverage both NVIDIA and AMD accelerated architectures. Verification will be performed by comparing the GPU and CPU implementations in two stages. First, a comparison of the geometric data and operators (e.g. geometric conservation, volumetric fluxes and gradient operators) will be conducted on a mesh containing a moving disk part. Second, a comparison of the flow variables will be made on canonical flows (e.g. Euler vortex, 1D acoustic wave and solid body rotation) with and without a moving disk part. The moving solver calculations will be validated by comparing results against a direct numerical simulation of a rotating sphere.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The GPU-accelerated mesh generator could eventually evolve into stand-alone meshing tool. Leveraging the duality between the Voronoi diagram and the Delaunay triangulation, the tool can quickly produce tetrahedral meshes for NASA codes (e.g., FUN3D). The GPU-accelerated moving mesh solver and its capability of performing efficient full-annulus multi-stage simulations of compressors and turbines will benefit NASA’s turbomachinery research by providing a high-fidelity simulation approach to complement NASA’s RANS codes (e.g. APNASA and TURBO).

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Turbomachinery is at the core of the aeronautical propulsion. The successful completion of Phase I & II will produce an efficient and affordable solution for high-fidelity numerical predictions of complex flows in compressors and turbines, which is highly aligned with the request and demand of Cascade’s commercial licensees in the aerospace industry (e.g. Bosch, Boeing and General Electric).

Duration: 6

Form Generated on 06/29/2020 20:58:42