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Computer code for predicting coolant flow and heat transfer in turbomachineryA computer code was developed to analyze any turbomachinery coolant flow path geometry that consist of a single flow passage with a unique inlet and exit. Flow can be bled off for tip-cap impingement cooling, and a flow bypass can be specified in which coolant flow is taken off at one point in the flow channel and reintroduced at a point farther downstream in the same channel. The user may either choose the coolant flow rate or let the program determine the flow rate from specified inlet and exit conditions. The computer code integrates the 1-D momentum and energy equations along a defined flow path and calculates the coolant's flow rate, temperature, pressure, and velocity and the heat transfer coefficients along the passage. The equations account for area change, mass addition or subtraction, pumping, friction, and heat transfer.
Document ID
19900018406
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Meitner, Peter L.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1990
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.60:2985
E-5186
NASA-TP-2985
AVSCOM-TR-89-C-008
Accession Number
90N27722
Funding Number(s)
PROJECT: DA PROJ. 1L1-61102-AH-45
PROJECT: RTOP 505-62-0K
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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