Transonic axial compressor design case study and preparations for testing
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Authors
Reid, William D.
Subjects
Advisors
Shreeve, Raymond P.
Date of Issue
1995-09
Date
September 1995
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
Test runs of the transonic axial compressor test rig at the Naval Postgraduate School, Turbopropulsion Laboratory, were conducted in preparation for the installation of a new stage design. Modifications in the cooling air supply to the high speed bearings, and to the design of the torque measuring system were completed during subsequent overhaul. A case study of the design of the new transonic stage was initiated. This consisted of a review of the procedure used in the design, as well as a design comparison. The comparison examined the differences between the blades designed for the new stage, which was primarily accomplished using a full, three- dimensional, Computational Fluid Dynamics code, and blades designed using two-dimensional streamline curvature methods. The axi-symmetric through-flow code, used in the design case study was modified to run on workstations at the Naval Postgraduate School, Department of Aeronautics and Astronautics, providing students and faculty with a design tool for single or multiple stage axial flow compressors.
Type
Thesis
Description
Series/Report No
Department
Aeronautical Engineering
Organization
Identifiers
NPS Report Number
Sponsors
Funding
NA
Format
102 p.
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.