Publication:
The effects of low-profile vortex generators on flow in a transonic fan-blade cascade

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Authors
Gamerdinger, Peter M.
Subjects
Advisors
Shreeve, Raymond P.
Date of Issue
1995-03
Date
March 1995
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
Two dimensional fully-mixed-out flow conditions were measured downstream of a two-passage transonic fan-blade cascade which had low-profile vortex generators (VGs) attached to the suction surfaces of the blades. The simulation was conducted using a blowdown wind tunnel at a Mach number of 1.4. The objective was to assess the effects of vortex generating devices on the suction surface shock-boundary layer interaction and the resulting losses. Measurements are reported from tests made with older aluminum blading, with and without VGs, and with a nominally similar new set of steel blading, with and without VGs. Differences between the old and new blading were found to be most significant. While shock structures appeared to be similar with VGs attached, dye injection showed that the shock-induced boundary layer separation was greatly suppressed and the downstream flow was much steadier. With VGs, the flow turning was improved by 0.94 degrees, but the flow loss coefficient increased by about 8%. An extension of the study is needed to fully assess the potential of using low-profile VGs in military fan engines.
Type
Thesis
Description
Series/Report No
Department
Aeronautical Engineering
Organization
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Format
97 p.
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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.
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