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Record 30 of 3122
A generalized one dimensional computer code for turbomachinery cooling passage flow calculations
Author and Affiliation:
Kumar, Ganesh N.(NASA Lewis Research Center, Sverdrup Technology, Inc.)
Roelke, Richard J.(NASA Lewis Research Center, Cleveland, OH, United States)
Meitner, Peter L.(NASA Lewis Research Center, U.S. Army, Propulsion Directorate, Cleveland)
Abstract: A generalized one-dimensional computer code for analyzing the flow and heat transfer in the turbomachinery cooling passages was developed. This code is capable of handling rotating cooling passages with turbulators, 180 degree turns, pin fins, finned passages, by-pass flows, tip cap impingement flows, and flow branching. The code is an extension of a one-dimensional code developed by P. Meitner. In the subject code, correlations for both heat transfer coefficient and pressure loss computations were developed to model each of the above mentioned type of coolant passages. The code has the capability of independently computing the friction factor and heat transfer coefficient on each side of a rectangular passage. Either the mass flow at the inlet to the channel or the exit plane pressure can be specified. For a specified inlet total temperature, inlet total pressure, and exit static pressure, the code computers the flow rates through the main branch and the subbranches, flow through tip cap for impingement cooling, in addition to computing the coolant pressure, temperature, and heat transfer coefficient distribution in each coolant flow branch. Predictions from the subject code for both nonrotating and rotating passages agree well with experimental data. The code was used to analyze the cooling passage of a research cooled radial rotor.
Publication Date: Jul 01, 1989
Document ID:
19890059563
(Acquired Nov 28, 1995)
Accession Number: 89A46934
Subject Category: FLUID MECHANICS AND HEAT TRANSFER
Report/Patent Number: AIAA PAPER 89-2574
Document Type: Preprint
Publisher Information: United States
Financial Sponsor: NASA; United States
Organization Source: NASA Lewis Research Center; Cleveland, OH, United States
Army Aviation Systems Command; Cleveland, OH, United States
Sverdrup Technology, Inc.; Cleveland, OH, United States
Description: 13p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: COMPUTER PROGRAMMING; COMPUTER PROGRAMS; FLOW DISTRIBUTION; HEAT TRANSFER; TURBOMACHINERY; CARTESIAN COORDINATES; COOLING; INLET TEMPERATURE; ITERATION; MASS FLOW
Imprint And Other Notes: AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. 13 p. Previously announced in STAR as N89-22862.
Availability Source: Other Sources
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