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Grid for a turbine stage CFD Codes for Turbomachinery, Dr. Rodrick V. Chima, NASA Glenn Research Center, Cleveland, Ohio, USA Pressure contours on a turbine stage
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SWIFT v. 400

Overview
SWIFT is a multiblock CFD code for the analysis of 3-D flows in turbomachinery. The code solves the thin-layer Navier-Stokes equations using explicit finite-difference techniques. It can be used to analyze linear cascades or annular blade rows with or without rotation. Limited multiblock capability can be used to model tip-clearances and multistage machines.

Applications
  • Linear cascades
  • Axial compressors and turbines
  • Isolated blade rows or multistage machines
  • Centrifugal impellers and mixed flow machines without splitters
  • Radial diffusers
  • Pumps
  • Rectangular ducts
Multi-block capability
  • C-grids around blades with H-grids upstream
  • H-grids around blades
  • O-grids for hub and tip clearances (a non-gridded clearance model is also available)
  • Mixing planes for multistage calculations
  • Version 400 now allows discontinuous spanwise grids at mixing planes
Formulation and differencing schemes

SWIFT solves the Navier-Stokes equations formulated in a Cartesian coordinate system with rotation about the x-axis. The equations are mapped to a general body-fitted coordinate system. Streamwise viscous terms are neglected using the thin-layer assumption, but all cross-channel viscous terms are retained.

  • Central difference + artificial viscosity
  • Central difference + H-CUSP upwind
  • AUSM+ upwind scheme
Turbulence models
  • Baldwin-Lomax (algebraic)
  • Cebeci-Smith (algebraic)
  • Wilcox's 2006 k-omega (two-equation) with stress limiter and cross-diffusion
  • All turbulence models include transition and roughness effects.
Numerical method
  • Explicit multi-stage Runge-Kutta scheme
  • Variable time-step and implicit residual smoothing for convergence acceleration
  • Preconditioning for low-speed (incompressible) flows
Input and output
  • Namelist input
  • Grids are usually generated using TCGRID and are stored in PLOT3D format
  • Solution files are in PLOT3D format
  • Printed output of convergence history, spanwise output of average flow properties, and streamwise output of blade surface properties

Computer and graphics requirements

SWIFT requires a Fortran 90 compiler and CFD visualization software for use. Click the button below for more information.


Test cases included with SWIFT 400

An Excel file with flow conditions, experimental data, and comparisons between computations and experiment is included with SWIFT 400 for each case.

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Pressure contours on a compressor rotor

NASA rotor 37

Pressure contours on a turbine vane

Goldman annular turbine cascade

Pressure contours on a compressor stage

NASA stage 35

Pressure contours on a 2-stage turbine

SSME 2-stage fuel turbine

Pressure contours on a fan rotor

NASA rotor 67

Pressure contours on an impeller

Large low-speed centrifugal impeller

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Curator: John Slater
NASA Official: Mary Jo Long-Davis
Last Updated: 05/04/2012