EXPERIMENTAL AND COMPUTATIONAL ANALYSIS OF ADVANCED CASING TREATMENTS IN A TRANSONIC COMPRESSOR
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Authors
Jones, Matthew B.
Subjects
compressor
casing
stall margin
CFD
CFX
casing
stall margin
CFD
CFX
Advisors
Gannon, Anthony J.
Smith, Walter C.
Date of Issue
2022-06
Date
Publisher
Monterey, CA; Naval Postgraduate School
Language
Abstract
Turbo-fan engines seek to achieve the highest compression ratios possible with the minimum number of parts by driving compressor stages to the extremes of their operating limits, which can risk compressor stall. This study expands on previous work by combining experimental and computational methods to evaluate the effectiveness of advanced transonic compressor casing treatments at increasing stall margin while minimizing losses. The NPS Turbopropulsion Lab Transonic Compressor Rig was used to characterize the performance of an advanced transonic compressor in the stage and stage-and-a-half configurations; additionally, inlet guide vanes were installed and evaluated. After characterization of the base performance, s-shaped axial endwall grooves were added to improve stall margin of the compressor stage. Experimental results proved the casing treatments were successful only in the subsonic regime. Stall margin increases of at least 286% were seen in low speed tests with 117% observed in high speed operation. Computational analysis simulated advanced casing treatments and effects of inlet whirl and was correlated to experimental data to shed light on the recirculation mechanisms active in casing treatments. The simulations provided insight for further development of novel self-recirculating endwall treatments and associated technologies.
Type
Thesis
Description
Series/Report No
Department
Mechanical and Aerospace Engineering (MAE)
Organization
Identifiers
NPS Report Number
Sponsors
Office of Naval Research, Arlington, VA, 22217
Funding
Format
Citation
Distribution Statement
Approved for public release. Distribution is unlimited.
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.