Overview
APNASA
is a three-dimensional, steady-state, time-averaged Navier-Stokes
code for multistage compressor analysis, which has been in
development since 1985 at the NASA Glenn Research Center.
The code is based on the Average-Passage model, authored by John
Adamczyk at Glenn. The Average Passage model is based on a
sequence of mathematical averaging of the Navier-Stokes
equations, the continuity equation, the energy equation and the
equation of state, resulting in a system of equations which
govern turbomachinery flow behavior.
For more information about APNASA contact Dr.
Kenneth L. Suder , 216-433-5899, Kenneth.L.Suder@nasa.gov
Glenn-HT2000
Overview
Glenn-HT2000
is a CFD code used to predict heat transfer and fluid flow for a
variety of steady gas turbine engine problems. Efforts
have focused on turbine heat transfer, where computations have
modeled tip clearance, internal coolant, and film cooling
flows. Excellent agreement has been achieved for a variety
of experimental test cases, and results have been published in
over 40 technical publications.
Glenn-HT2000 is available to companies and universities within the
United States. For more information about Glenn-HT2000
contact Dr. James D. Heidmann, 216-433-3604, James.D.Heidmann@nasa.gov
H3D
Overview
H3D is a CFD code for the analysis of 3-D
flows in turbomachinery developed by Dr. Chunill Hah at NASA
Glenn Research Center. The code solves the full Navier-Stokes
equations using a pressure based solver with a standard
two-equation turbulence model and a large eddy simulation (LES).
For more information about H3D, contact
Dr. Chunill Hah,
Chunill.Hah@nasa.gov
MSU TURBO
Overview
MSU TURBO is a graphical user interface for a
set of codes called GUMBO and TURBO used for
analysis of unsteady flows in turbomachinery. MSU
TURBO is used to define input parameters, and
includes online documentation. The codes are being
developed at the Computational Simulation and
Design Center at the Engineering Research Center
at Mississippi State University (MSU). Development
of the codes has been supported by NASA Glenn
Research Center, the US Army Research Office, GE
Aircraft Engines, and Honeywell Engines Systems
and Service.
MSU TURBO home page: http://www.erc.msstate.edu/simcenter/docs/msu_turbo/
For more information about MSU TURBO, contact
Dr. Michael D. Hathaway,
Michael.D.Hathaway@grc.nasa.gov
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: 
