Effects of Free Stream Turbulence on Compressor Cascade Performance

The effects of grid generated free-stream turbulence on compressor cascade performance was measured experimentally in the Virginia Tech blow-down wind tunnel. The parameter of key interest was the behavior of the measured total pressure loss coefficient with and without generated free-stream turbul...

Full description

Bibliographic Details
Main Author: Douglas, Justin W.
Other Authors: Mechanical Engineering
Format: Others
Published: Virginia Tech 2014
Subjects:
Online Access:http://hdl.handle.net/10919/31449
http://scholar.lib.vt.edu/theses/available/etd-03122001-155007/
id ndltd-VTETD-oai-vtechworks.lib.vt.edu-10919-31449
record_format oai_dc
spelling ndltd-VTETD-oai-vtechworks.lib.vt.edu-10919-314492020-09-26T05:38:15Z Effects of Free Stream Turbulence on Compressor Cascade Performance Douglas, Justin W. Mechanical Engineering Ng, Wing Fai Li, Shi Ming Diller, Thomas E. Dancey, Clinton L. Compressor Cascade Anemometer Hotwire Aerodynamic Loss Turbulence Grid Boundary Layer Transition The effects of grid generated free-stream turbulence on compressor cascade performance was measured experimentally in the Virginia Tech blow-down wind tunnel. The parameter of key interest was the behavior of the measured total pressure loss coefficient with and without generated free-stream turbulence. A staggered cascade of nine airfoils was tested at a range of Mach numbers between 0.59 and 0.88. The airfoils were tested at both the lowest loss level cascade angle and extreme positive and negative cascade angles about this condition. The cascade was tested in a Reynolds number range based on the chord length of approximately 1.2-2x106. A passive turbulent grid was used as the turbulence-generating device, it produced a turbulent intensity of approximately 1.6%. The total pressure loss coefficient was reduced by 11-56% at both the "lowest loss level" and more positive cascade angles for both high and low Mach numbers. Oil Visualization and blade static pressure measurements were performed in order to gain a qualitative understanding of the loss reduction mechanism. The results indicate that the effectiveness of an increasing turbulent free-stream on loss reduction, at transonic Mach numbers, depends on whether the shock wave on the suction surface is strong enough to completely separate the boundary layer. At negative cascade angles, increasing free-stream turbulence proved to have a negligible influence on the pressure loss coefficient. At cascade angles where transition exists within a laminar separation bubble, increasing free-stream turbulence suppressed the extent of the laminar separation bubble and led to an earlier turbulent reattachment. Master of Science 2014-03-14T20:32:30Z 2014-03-14T20:32:30Z 2001-03-01 2001-03-12 2002-03-13 2001-03-13 Thesis etd-03122001-155007 http://hdl.handle.net/10919/31449 http://scholar.lib.vt.edu/theses/available/etd-03122001-155007/ jwdpdf.pdf In Copyright http://rightsstatements.org/vocab/InC/1.0/ application/pdf Virginia Tech
collection NDLTD
format Others
sources NDLTD
topic Compressor Cascade
Anemometer
Hotwire
Aerodynamic Loss
Turbulence Grid
Boundary Layer Transition
spellingShingle Compressor Cascade
Anemometer
Hotwire
Aerodynamic Loss
Turbulence Grid
Boundary Layer Transition
Douglas, Justin W.
Effects of Free Stream Turbulence on Compressor Cascade Performance
description The effects of grid generated free-stream turbulence on compressor cascade performance was measured experimentally in the Virginia Tech blow-down wind tunnel. The parameter of key interest was the behavior of the measured total pressure loss coefficient with and without generated free-stream turbulence. A staggered cascade of nine airfoils was tested at a range of Mach numbers between 0.59 and 0.88. The airfoils were tested at both the lowest loss level cascade angle and extreme positive and negative cascade angles about this condition. The cascade was tested in a Reynolds number range based on the chord length of approximately 1.2-2x106. A passive turbulent grid was used as the turbulence-generating device, it produced a turbulent intensity of approximately 1.6%. The total pressure loss coefficient was reduced by 11-56% at both the "lowest loss level" and more positive cascade angles for both high and low Mach numbers. Oil Visualization and blade static pressure measurements were performed in order to gain a qualitative understanding of the loss reduction mechanism. The results indicate that the effectiveness of an increasing turbulent free-stream on loss reduction, at transonic Mach numbers, depends on whether the shock wave on the suction surface is strong enough to completely separate the boundary layer. At negative cascade angles, increasing free-stream turbulence proved to have a negligible influence on the pressure loss coefficient. At cascade angles where transition exists within a laminar separation bubble, increasing free-stream turbulence suppressed the extent of the laminar separation bubble and led to an earlier turbulent reattachment. === Master of Science
author2 Mechanical Engineering
author_facet Mechanical Engineering
Douglas, Justin W.
author Douglas, Justin W.
author_sort Douglas, Justin W.
title Effects of Free Stream Turbulence on Compressor Cascade Performance
title_short Effects of Free Stream Turbulence on Compressor Cascade Performance
title_full Effects of Free Stream Turbulence on Compressor Cascade Performance
title_fullStr Effects of Free Stream Turbulence on Compressor Cascade Performance
title_full_unstemmed Effects of Free Stream Turbulence on Compressor Cascade Performance
title_sort effects of free stream turbulence on compressor cascade performance
publisher Virginia Tech
publishDate 2014
url http://hdl.handle.net/10919/31449
http://scholar.lib.vt.edu/theses/available/etd-03122001-155007/
work_keys_str_mv AT douglasjustinw effectsoffreestreamturbulenceoncompressorcascadeperformance
_version_ 1719342578205196288