This page requires JavaScript for proper operation of the menus.
NASA Glenn Research Center
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
 CFD CODES HOME BUTTON
GRAPE: 2-D GRIDS BUTTON
RVCQ3D: Q-3-D ANALYSIS BUTTON
TCGRID: 3-D GRIDS BUTTON
 SWIFT: 3-D ANALYSIS BUTTON
REFERENCES BUTTON
AUTHOR BUTTON
TURBOMACHINERY BRANCH BUTTON
INLETS & NOZZLES BRANCH BUTTON

RVCQ3D v. 406

Overview
RVCQ3D (Rotor Viscous Code Quasi-3-D) is a computer code for analyzing inviscid and viscous blade-to-blade flows in turbomachinery. It includes the quasi-3-D effects of rotation, radius change, and variable stream surface thickness. Simple flat plate and duct geometries can also be analyzed.

Applications

  • Axial compressors and turbines
  • Centrifugal impellers and radial diffusers (no splitters)
  • Pumps
  • Linear cascades
  • Flat plates and rectangular ducts
  • Fast parametric studies of blade shape, incidence angle, etc.
  • CFD and turbomachinery education
Formulation and differencing schemes
RVCQ3D solves the Euler or Navier-Stokes equations written on a surface of revolution. The equations are written in an (m,theta)coordinate system, where m is the arc length along the surface and theta is the circumferential direction. The stream surface radius and thickness are assumed to be known functions of m, and are usually obtained from an axisymmetric throughflow analysis.
  • 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 cross diffusion term and stress limiter

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
  • Grids are usually generated using GRAPE
  • Grid and solution files are in PLOT3D format
  • Namelist input
  • Printed output of convergence history, blade surface properties, and average flow properties at the inlet and exit

Computer and graphics requirements
RVCQ3D requires a Fortran 90 compiler and CFD visualization software for use. Click the button below for more information.



Test cases included with RVCQ3D 406

Click on a preview image below to open a larger image in your browser.
Use your < Back > button to return to this screen.

Colored mach contours around fan blades

Mach contours, NASA rotor 37,
70 percent span

Colored mach contours around impeller blades

Mach contours, NASA 6:1
centrifugal impeller

Colored mach contours around turbine vanes

Mach contours, Goldman annular
turbine vane

Plot of skin friction coefficient vs. Rex

Flat plate skin friction
for testing turbulence models

 


Other cases modeled with RVCQ3D

Mach contours through an array of rectangular slots

Mach contours, supersonic flow through a slotted plate

Gray scale contours around several fan blades

Density gradient contours showing shocks
on a cascade of fan blades

NASA logo + NASA - Home + NASA Privacy and Security Notices

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