Application of finite element code Q3DFL0-81 to turbomachinery flow fields
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Authors
Schulz, H. D.
Neuhoff, F.
Hirsch, Ch.
Shreeve, R. P.
Subjects
Finite Element Code
Turbomachinery Flow Fields
Through-Flow Calculations
Turbomachinery Flow Fields
Through-Flow Calculations
Advisors
Date of Issue
1984-09
Date
1 October 1983-September 1984
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
Through-flow and blade-to-blade calculations were made in association with a
number of experimental research activities at the Turbopropulsion Laboratory,
Naval Postgraduate School. The Q3DFL0-81 code was operated on an IBM 370-3033
mainframe computer. The flow through a single stage axial research compressor
was computed and compared with both probe survey and stage performance map
measurments. Swirling flow produced by a vaned out-flow generator for a
radial diffuser test facility was calculated for both large low-speed and
small-scale high-speed versions of the device. Flow through a two-dimensional
compressor cascade of "controlled-dif fusion" blade shapes was calculated and
the results compared with experimental data, and with predictions obtained
using the NASA code QSONIC.
Type
Technical Report
Description
Series/Report No
Department
Identifiers
NPS Report Number
NPS67-84-005
Sponsors
Prepared for: Naval Air Systems Command, Washington DC
Funder
N0001984WR 41099, N0001984WR 41134
Format
NA
Citation
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.