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PCSTAGE
Overview
PCSTAGE is a CFD code for the analysis of quasi-3-D
blade-to-blade flows in turbomachinery developed by Dr. Eric R.
McFarland (ret.) at NASA Glenn Research Center. The code uses an
integral equation solution method to solve the two-dimensional,
inviscid flow equations for multiple bodies. Compressibility
effects are approximated in the solution. The method is most
accurate for low-speed flows, but can be applied to flows where
the Mach number repains less than one. PCSTAGE can also be used
to model unsteady blade row interaction by calculating steady
solutions with blades at different positions.
PCSTAGE is available to companies and universities within the
United States from the NASA GRC software repository:
https://technology.grc.nasa.gov/software/
Applications
- Blade-to-blade flows for all subsonic turbomachinery
- Multiple bodies
- Quasi-unsteady multistage simulations
Formulation
- 2-D inviscid. incompressible, irrotational equations on a
surface of revolution
- Compressibility correction
- Stream surface radius and height model 3-D effects
- Integral equation solution technique (panel method)
- Very fast solutions on a PC
Examples
Click on a thumbnail image below to open an animation in
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Unsteady
Calculations - click for animation
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Quasi-unsteady pressure field in an underflowing pump
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Quasi-unsteady pressure field in a pump at the design
point.
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Quasi-unsteady pressure field in an overflowing pump
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Quasi-unsteady pressure field in a radial inflow turbine
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Simulation of the W5b oscillating cascade rig. Colors
represent Mach number.
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