Computations are based on mean-diameter flow properties. For any given turbine, all stages, except the first, are specified to have same shape velocity diagram. First stage inlet flow is axial

Glassman, A. J.

English

NASA Technical Reports Server

February 1973
	 B73-10066 
NASA TECH BRIEF 
Lewis Research Center 
NASA Tech Briefs announce new technology derived from the U.S. space program. They are issued to encourage 
commercial application. Tech Briefs are available on a subscription basis from the National Technical Information 
Service, Springfield, Virginia 22151. Requests for individual copies or questions relating to the Tech Brief program may 
be directed to the Technology Utilization Office, NASA, Code KT, Washington, D.C. 20546. 
Computer Program for Preliminary

Design Analysis of Axial-Flow Turbines 
I.
A computer program has been developed for the 
preliminary design analysis of axial-flow turbines. The 
computations are based on mean-diameter flow proper-
ties and do not consider any radial gradients. Specific 
heat ratio is assumed constant throughout the turbine. 
For any given turbine, all stages, except the first, are 
specified to have the same shape velocity diagram. The 
first stage differs only in that the inlet flow is axial. 
The velocity diagram shape depends upon the speed-
work parameter value and the specified type of velocity 
diagram. Any of three types of velocity diagrams can be 
specified: symmetrical, zero exit swirl, or impulse. Exit 
turning vanes can be included in the design.	 - 
Input design requirements include power or pressure 
ratio, mass flow rate, inlet temperature and pressure, 
and rotative speed. The design variables include inlet and 
exit diameters, stator angle or exit radius ratio, and 
number of stages. Gas properties are input as gas con-
stant, specific heat ratio, and viscosity.
The program output includes inlet and exit annulus 
dimensions, exit temperature and pressure, total and 
static efficiencies, blading angles, and last-stage critical 
velocity ratios. 
Notes: 
1. All computations are performed in one main program 
written in IBM 7090/7094 FORTRAN IV language. 
2. The computations can be done either in SI units or 
in US customary units. 
3. Inquiries concerning this program should be directed 
to:
COSMIC 
112 Barrow Hall 
University of Georgia 
Athens, Georgia 30601 
Reference: LEW-1 1815 
Source: Arthur J. Glassman

Lewis Research Center

(LEW-1 1815) 
Category 09,06 
This document was prepared under the sponsorship of the National 	 Government assumes any liability resulting from the use of the 
Aeronautics and Space Administration. Neither the United States 	 information contained in this document, or warrants that such use 
Government nor any person acting on behalf of the United States 	 will be free from privately owned rights.
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Computer program for preliminary design analysis of axial-flow turbines

The program method is based on a mean-diameter flow analysis. Input design requirements include power or pressure ratio, flow, temperature, pressure, and speed. Turbine designs are generated for any specified number of stages and for any of three types of velocity diagrams (symmetrical, zero exit swirl, or impulse). Exit turning vanes can be included in the design. Program output includes inlet and exit annulus dimensions, exit temperature and pressure, total and static efficiencies, blading angles, and last-stage critical velocity ratios. The report presents the analysis method, a description of input and output with sample cases, and the program listing

Computer program for preliminary design analysis of axial-flow turbines

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