Computer program, MAGNFY, calculates the velocity distribution through the passage between and over blade surfaces of blade rows for turbines and compressors. Using the input of other programs, MAGNFY obtains velocities on smaller than normal finite difference mesh in any part of the blade-to-blade passage

Katsanis, T.

Mc Nally, W.

English

NASA Technical Reports Server

NASA TECH BRIEF 
May 1969
	
Brief 69-10132 
NASA Tech Briefs are issued to summarize specific innovations derived from the U.S. space program, 
to encourage their commercial application. Copies are available to the public at 15 cents each 
from the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151. 
(MAGNIFY) Program for Calculating Velocities in 
Magnified Region of Turbomachines 
The problem: 
To obtain the velocity distribution through the pass-
age between and particularly over the blade surfaces 
of blade rows for turbines and compressors, especially 
the velocities around leading or trailing edge radii and 
within slot regions. 
The solution: 
MAGNFY was developed to obtain velocities on 
smaller-than-normal finite difference mesh in any part 
of the blade-to-blade passage. 
How it's done: 
Programs have been published to obtain velocity 
distribution through the passages and over blade sur-
faces' of single and tandem blade rows. Using these 
programs, however, it is not always possible to ob-
tain sufficient detail on some critical parts of the 
blade surfaces such as around the small leading or 
trailing edge radii or within slot regions. It is within 
these regions that geometry, and thus velocities, 
change most rapidly. 
This program, therefore, uses input of the other pro-
grams (2DCP, TURBLE, TANDEM) to obtain a 
solution on a fine mesh in a small part of the blade-
to-blade region. The output is similar to that of the 
other three programs and includes detailed surface 
velocities, velocity magnitude and direction, and 
stream function values throughout the magnified 
region. In essence, the program yields a local detailed
solution around the leading or trailing edge or in a 
slot region for compressible, subsonic, non-viscous 
flow on a blade-to-blade surface between two turbo-
machine blades. 
A course mesh solution for an entire blade-to-blade 
region can be magnified by a chosen magnification 
factor in a small rectangular region. The method is 
based on the stream function with the solution of the 
simultaneous, nonlinear, finite-difference equations 
being obtained by two major levels of iteration. The 
inner iteration consists of the solution of simultaneous 
linear equations by successive overrelaxation, using an 
estimated optimum overrelaxation factor. The outer 
iteration then changes the coefficient of the simul-
taneous equations to compensate for compressibility. 
Notes: 
1. This program is written in FORTRAN IV 
language for use on the IBM 7094 computer. 
2. Inquiries concerning this innovation may be 
directed to:
COSMIC 
Computer Center 
University of Georgia 
Athens, Georgia 30601 
Reference: B69-10132 
Patent status: 
No patent action is contemplated by NASA. 
Source: Theodore Katsanis and William McNally 
(LEW- 10789) 
Category 06 
This document was prepared under the sponsorship of the National 
Aeronautics and Space Administration. Neither the United States 
Government nor any person acting on behalf of the United States
Government assumes any libiIity reslting from the use of the 
information contained in this document, or warrants that such use 
will be free from privately owned rights.
https://ntrs.nasa.gov/search.jsp?R=19690000132 2020-03-16T17:58:45+00:00Z


MAGNTY - Program for calculating velocities in magnified region of turbomachines

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