Report on the testing of a hybrid (radial-to-axial) compressor
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Authors
Shreeve, Raymond P.
Subjects
Advisors
Date of Issue
1973-11
Date
1973-11
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
A full account is given of a test program to evaluate a prototype "Hybrid" compressor, wherin the flow is turned through 180[degrees] (from axial to radial to axial) within the rotor. The initial stator, or diffuser, consisted of two cascades of unswept and untwisted blades arranged and designed as in an axial compressor. The performance was measured with two diffusers of different solidities and with changes in the blade stagger angles. The maximum efficiency approached 80%, however, the flow was separated in the second blade row for all diffuser designs tested. Surveys from hub to tip at the rotor exit revealed an unusually larger variation in flow angle. Approximations were obtained from normalized distributions of velocity and angle from all tests which will allow the design of a diffuser with swept or twisted blades. It is recommended that such a design be tested to provide a more definitive assessment of the "Hybrid" concept. The reported tests were the first conducted in a new turbine-driven compressor test rig at the Turboprobulsion Laboratories. An account is included of the verification of flow, torque and temperature measurements and of a method devised to overcome the difficulty of establishing the performance with highly non-uniform total pressure distributions from multiple passages within a thin annulus. The method, which was analytically correct and required the input of a particular number of sample measurements, gave results almost identical to the conventional mass-averaging technique. (Author)
Type
Technical Report
Description
Series/Report No
Department
Identifiers
NPS Report Number
NPS-57Sr73112A
Sponsors
This research program was carried out for the Department of the Navy,
Naval Air Systems Command, in accordance with Airtask No. 3303300/186B/3F41432301 under the congnizace of Mr. K. H. Guttmann, Code AIR-330C, NAVAIR Project Engineer.
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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.