Computer program, capable of analyzing single and multispool units, computes absolute and relative flow fields within the turbine at the first stator inlet, at each interblade row plane, and at the final rotor exit. No simplifying assumptions are made which would result in restrictive design

Carter, A. F.

Lenherr, F. K.

English

NASA Technical Reports Server

December 1970	 Brief 70-10669 
NASA TECH 
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 progam may be directed to the Tech-
riology Utilization Division, NASA, Code UT, Washington, D.C. 20546. 
Computer Program for the Design of Axial-Flow Turbines 
-4
The problem: 
To develop a nonrestrictive method for determining 
the alternative geometries and associated design point 
performance of axial-flow turbines capable of satis-
fying specified design requirements. 
The solution: 
Program TD 2 (Turbine Design) is a computer pro-
gram that solves the flow field within the turbine 
without making the simplifying assumptions that re-
sult in restrictive designs. 
How it's done: 
The program is capable of analyzing both single 
and multispool units. A;maximum of three spools, each 
with up to eight stages, is allowed. The absolute and 
relative flow fields are computed at the first stator 
inlet, at each interbiade row plane, and at the final 
rotor exit. Radial variation effects of the following 
quantities are taken into account: inlet conditions, 
streamline angle of inclination and curvature, loss 
coefficient or efficiency, and meridional velocity or 
angle. Further, the effects of coolant flows, inter-
filament mixing, and station-to-station variation of 
specific heat can be included. The program internally 
calculates losses, based on a pre-developed correlation 
for pressure-loss coefficient; and either subsonic or 
supersonic solutions can be used to determine the 
absolute velocity. 
Standard turbine design parameters can be deter-
mined at a preselected number of streamlines. These
parameters will be consistent with radial equilibrium 
requirements, specified or calculated blade element 
performance, and input specifications defining design 
requirements. When used for the analysis of a single 
spool, the program can consecutively produce designs 
for any number of sets of analysis variables. 
Notes: 
I. This program is written in FORTRAN IV lan-
guage for use on the IBM 7094/7044 Direct Couple 
System. 
2. This program is an updated version of the com-
puter program described in NASA Tech Brief 
69-10111, "Geometry and Design Point Perform-
ance of Axial Flow Turbines." 
3. Inquiries may be directed to: 
COSMIC 
Barrow Hall
	 - 
University of Georgia 
Athens, Georgia 30601 
Reference: B70-10669 
Patent status: 
No patent action is contemplated by NASA. 
Source: F. K. Lenherr and A. F. Carter of 
Northern Research and Engineering Corp. 
under contract to 
Lewis Research Center 
(LEW-1 1029) 
Category 09 
As 
MW
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.
https://ntrs.nasa.gov/search.jsp?R=19700000649 2020-03-17T01:05:01+00:00Z


Computer program for the design of axial-flow turbines

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