Using Gurney Flaps to Control Laminar Separation on Linear Cascade Blades
This paper describes an experimental investigation of the use of Gurney flaps to control laminar separation on turbine blades in a linear cascade. Measurements were made at Reynolds numbers (based upon inlet velocity and axial chord) of 28×103,65×103 and 167×103. The freestream turbulence intensity...
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Veröffentlicht in: | Journal of turbomachinery 2003-01, Vol.125 (1), p.114-120 |
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description | This paper describes an experimental investigation of the use of Gurney flaps to control laminar separation on turbine blades in a linear cascade. Measurements were made at Reynolds numbers (based upon inlet velocity and axial chord) of 28×103,65×103 and 167×103. The freestream turbulence intensity for all three cases was 0.8%. Laminar separation was present on the suction surface of the Langston blade shape for the two lower Reynolds numbers. In an effort to control the laminar separation, Gurney flaps were added to the pressure surface close to the trailing edge. The measurements indicate that the flaps turn and accelerate the flow in the blade passage toward the suction surface of the neighboring blade thereby eliminating the separation bubble. Five different sizes of Gurney flaps, ranging from 0.6 to 2.7% of axial chord, were tested. The laser thermal tuft technique was used to determine the influence of the Gurney flaps on the location and size of the separation bubble. Additionally, measurements of wall static pressure, profile loss, and blade-exit flow angle were made. The blade pressure distribution indicates that the lift generated by the blade is increased. As was expected, the Gurney flap also produced a larger wake. In practice, Gurney flaps might possibly be implemented in a semi-passive manner. They could be deployed for low Reynolds number operation and then retracted at high Reynolds numbers when separation is not present. This work is important because it describes a successful means for eliminating the separation bubble while characterizing both the potential performance improvement and the penalties associated with this semi-passive flow control technique. |
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Measurements were made at Reynolds numbers (based upon inlet velocity and axial chord) of 28×103,65×103 and 167×103. The freestream turbulence intensity for all three cases was 0.8%. Laminar separation was present on the suction surface of the Langston blade shape for the two lower Reynolds numbers. In an effort to control the laminar separation, Gurney flaps were added to the pressure surface close to the trailing edge. The measurements indicate that the flaps turn and accelerate the flow in the blade passage toward the suction surface of the neighboring blade thereby eliminating the separation bubble. Five different sizes of Gurney flaps, ranging from 0.6 to 2.7% of axial chord, were tested. The laser thermal tuft technique was used to determine the influence of the Gurney flaps on the location and size of the separation bubble. Additionally, measurements of wall static pressure, profile loss, and blade-exit flow angle were made. The blade pressure distribution indicates that the lift generated by the blade is increased. As was expected, the Gurney flap also produced a larger wake. In practice, Gurney flaps might possibly be implemented in a semi-passive manner. They could be deployed for low Reynolds number operation and then retracted at high Reynolds numbers when separation is not present. This work is important because it describes a successful means for eliminating the separation bubble while characterizing both the potential performance improvement and the penalties associated with this semi-passive flow control technique.</description><identifier>ISSN: 0889-504X</identifier><identifier>EISSN: 1528-8900</identifier><identifier>DOI: 10.1115/1.1518701</identifier><identifier>CODEN: JOTUEI</identifier><language>eng</language><publisher>New York, NY: ASME</publisher><subject>Applied sciences ; Continuous cycle engines: steam and gas turbines, jet engines ; Engines and turbines ; Exact sciences and technology ; Mechanical engineering. Machine design</subject><ispartof>Journal of turbomachinery, 2003-01, Vol.125 (1), p.114-120</ispartof><rights>2003 INIST-CNRS</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-a374t-733a85fa02ca6d16040a765f5ee50fa40cfbc10531c8ffe5f6ac3be2acc91ecf3</citedby><cites>FETCH-LOGICAL-a374t-733a85fa02ca6d16040a765f5ee50fa40cfbc10531c8ffe5f6ac3be2acc91ecf3</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,776,780,27903,27904,38499</link.rule.ids><backlink>$$Uhttp://pascal-francis.inist.fr/vibad/index.php?action=getRecordDetail&idt=14546442$$DView record in Pascal Francis$$Hfree_for_read</backlink></links><search><creatorcontrib>Byerley, Aaron R</creatorcontrib><creatorcontrib>Sto¨rmer, Oliver</creatorcontrib><creatorcontrib>Baughn, James W</creatorcontrib><creatorcontrib>Simon, Terrence W</creatorcontrib><creatorcontrib>Van Treuren, Kenneth W</creatorcontrib><creatorcontrib>List, Jo¨rg</creatorcontrib><title>Using Gurney Flaps to Control Laminar Separation on Linear Cascade Blades</title><title>Journal of turbomachinery</title><addtitle>J. Turbomach</addtitle><description>This paper describes an experimental investigation of the use of Gurney flaps to control laminar separation on turbine blades in a linear cascade. Measurements were made at Reynolds numbers (based upon inlet velocity and axial chord) of 28×103,65×103 and 167×103. The freestream turbulence intensity for all three cases was 0.8%. Laminar separation was present on the suction surface of the Langston blade shape for the two lower Reynolds numbers. In an effort to control the laminar separation, Gurney flaps were added to the pressure surface close to the trailing edge. The measurements indicate that the flaps turn and accelerate the flow in the blade passage toward the suction surface of the neighboring blade thereby eliminating the separation bubble. Five different sizes of Gurney flaps, ranging from 0.6 to 2.7% of axial chord, were tested. The laser thermal tuft technique was used to determine the influence of the Gurney flaps on the location and size of the separation bubble. Additionally, measurements of wall static pressure, profile loss, and blade-exit flow angle were made. The blade pressure distribution indicates that the lift generated by the blade is increased. As was expected, the Gurney flap also produced a larger wake. In practice, Gurney flaps might possibly be implemented in a semi-passive manner. They could be deployed for low Reynolds number operation and then retracted at high Reynolds numbers when separation is not present. This work is important because it describes a successful means for eliminating the separation bubble while characterizing both the potential performance improvement and the penalties associated with this semi-passive flow control technique.</description><subject>Applied sciences</subject><subject>Continuous cycle engines: steam and gas turbines, jet engines</subject><subject>Engines and turbines</subject><subject>Exact sciences and technology</subject><subject>Mechanical engineering. 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Machine design</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Byerley, Aaron R</creatorcontrib><creatorcontrib>Sto¨rmer, Oliver</creatorcontrib><creatorcontrib>Baughn, James W</creatorcontrib><creatorcontrib>Simon, Terrence W</creatorcontrib><creatorcontrib>Van Treuren, Kenneth W</creatorcontrib><creatorcontrib>List, Jo¨rg</creatorcontrib><collection>Pascal-Francis</collection><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><jtitle>Journal of turbomachinery</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Byerley, Aaron R</au><au>Sto¨rmer, Oliver</au><au>Baughn, James W</au><au>Simon, Terrence W</au><au>Van Treuren, Kenneth W</au><au>List, Jo¨rg</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Using Gurney Flaps to Control Laminar Separation on Linear Cascade Blades</atitle><jtitle>Journal of turbomachinery</jtitle><stitle>J. Turbomach</stitle><date>2003-01-01</date><risdate>2003</risdate><volume>125</volume><issue>1</issue><spage>114</spage><epage>120</epage><pages>114-120</pages><issn>0889-504X</issn><eissn>1528-8900</eissn><coden>JOTUEI</coden><abstract>This paper describes an experimental investigation of the use of Gurney flaps to control laminar separation on turbine blades in a linear cascade. Measurements were made at Reynolds numbers (based upon inlet velocity and axial chord) of 28×103,65×103 and 167×103. The freestream turbulence intensity for all three cases was 0.8%. Laminar separation was present on the suction surface of the Langston blade shape for the two lower Reynolds numbers. In an effort to control the laminar separation, Gurney flaps were added to the pressure surface close to the trailing edge. The measurements indicate that the flaps turn and accelerate the flow in the blade passage toward the suction surface of the neighboring blade thereby eliminating the separation bubble. Five different sizes of Gurney flaps, ranging from 0.6 to 2.7% of axial chord, were tested. The laser thermal tuft technique was used to determine the influence of the Gurney flaps on the location and size of the separation bubble. Additionally, measurements of wall static pressure, profile loss, and blade-exit flow angle were made. The blade pressure distribution indicates that the lift generated by the blade is increased. As was expected, the Gurney flap also produced a larger wake. In practice, Gurney flaps might possibly be implemented in a semi-passive manner. They could be deployed for low Reynolds number operation and then retracted at high Reynolds numbers when separation is not present. This work is important because it describes a successful means for eliminating the separation bubble while characterizing both the potential performance improvement and the penalties associated with this semi-passive flow control technique.</abstract><cop>New York, NY</cop><pub>ASME</pub><doi>10.1115/1.1518701</doi><tpages>7</tpages></addata></record> |
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subjects | Applied sciences Continuous cycle engines: steam and gas turbines, jet engines Engines and turbines Exact sciences and technology Mechanical engineering. Machine design |
title | Using Gurney Flaps to Control Laminar Separation on Linear Cascade Blades |
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