APNASA

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. 

The capability of this code includes the prediction of the interaction between stationary and rotating components of multistage turbomachinery (i.e., fan, compressor, turbine, etc.)  The CFD (Computational Fluid Dynamics) code is a steady state, viscous solver for the Navier-Stokes equations, and uses a two equation turbulence model (K-ε).  As the code is written in FORTRAN 90, it can run on any modest Linux-based computer which is available today.  Support for APNASA includes environment software for pre-processing, run-time control, and post-processing.  Pre-processing tools include MMESH, a program for single-block mesh generation, and utilities for generating the initial startup flow field required for running a simulation.  Post-processing tools include those needed for the 1-D analysis, 2-D analysis, and 3-D flow visualization of generated solutions. 

The uniqueness of APNASA lies in its ability to model the aerodynamic effect of neighboring blade rows on a given blade row.  It has been successfully used to simulate a number of geometries from commercial aero-engine companies, as well as NASA's own research compressors.  The code also allows for the modeling of flow injection or bleeding on blade surfaces and end walls via surface boundary conditions.  These bleed ports sometimes can significantly impact the aerodynamic performance of turbomachinery.  

For more information about APNASA contact  Dr. Kenneth L. Suder, 216-433-5899, Kenneth.L.Suder@nasa.gov