Separated Flow Transition on an LP Turbine Blade With Pulsed Flow Control
Flow measurements were made on a highly loaded low pressure turbine blade in a low-speed linear cascade facility. The blade has a design Zweifel coefficient of 1.34 with a peak pressure coefficient near 47% axial chord (midloaded). Flow and surface pressure data were taken for Rec=20,000 with 3% inl...
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| Veröffentlicht in: | Journal of turbomachinery 2008-04, Vol.130 (2), p.021014 (8)-021014 (8) |
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| creator | Bons, Jeffrey P Reimann, Daniel Bloxham, Matthew |
| description | Flow measurements were made on a highly loaded low pressure turbine blade in a low-speed linear cascade facility. The blade has a design Zweifel coefficient of 1.34 with a peak pressure coefficient near 47% axial chord (midloaded). Flow and surface pressure data were taken for Rec=20,000 with 3% inlet freestream turbulence. For these operating conditions, a large separation bubble forms over the downstream portion of the blade suction surface, extending from 59% to 86% axial chord. Single-element hot-film measurements were acquired to clearly identify the role of boundary layer transition in this separated region. Higher-order turbulence statistics were used to identify transition and separation zones. Similar measurements were also made in the presence of unsteady forcing using pulsed vortex generator jets just upstream of the separation bubble (50% cx). Measurements provide a comprehensive picture of the interaction of boundary layer transition and separation in this unsteady environment. Similarities between pulsed flow control and unsteady wake motion are highlighted. |
| doi_str_mv | 10.1115/1.2751149 |
| format | Article |
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The blade has a design Zweifel coefficient of 1.34 with a peak pressure coefficient near 47% axial chord (midloaded). Flow and surface pressure data were taken for Rec=20,000 with 3% inlet freestream turbulence. For these operating conditions, a large separation bubble forms over the downstream portion of the blade suction surface, extending from 59% to 86% axial chord. Single-element hot-film measurements were acquired to clearly identify the role of boundary layer transition in this separated region. Higher-order turbulence statistics were used to identify transition and separation zones. Similar measurements were also made in the presence of unsteady forcing using pulsed vortex generator jets just upstream of the separation bubble (50% cx). Measurements provide a comprehensive picture of the interaction of boundary layer transition and separation in this unsteady environment. Similarities between pulsed flow control and unsteady wake motion are highlighted.</description><identifier>ISSN: 0889-504X</identifier><identifier>EISSN: 1528-8900</identifier><identifier>DOI: 10.1115/1.2751149</identifier><identifier>CODEN: JOTUEI</identifier><language>eng</language><publisher>New York, NY: ASME</publisher><subject>Applied sciences ; Boundary layer and shear turbulence ; Continuous cycle engines: steam and gas turbines, jet engines ; Engines and turbines ; Exact sciences and technology ; Fluid dynamics ; Fundamental areas of phenomenology (including applications) ; Mechanical engineering. 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Turbomach</addtitle><description>Flow measurements were made on a highly loaded low pressure turbine blade in a low-speed linear cascade facility. The blade has a design Zweifel coefficient of 1.34 with a peak pressure coefficient near 47% axial chord (midloaded). Flow and surface pressure data were taken for Rec=20,000 with 3% inlet freestream turbulence. For these operating conditions, a large separation bubble forms over the downstream portion of the blade suction surface, extending from 59% to 86% axial chord. Single-element hot-film measurements were acquired to clearly identify the role of boundary layer transition in this separated region. Higher-order turbulence statistics were used to identify transition and separation zones. Similar measurements were also made in the presence of unsteady forcing using pulsed vortex generator jets just upstream of the separation bubble (50% cx). Measurements provide a comprehensive picture of the interaction of boundary layer transition and separation in this unsteady environment. Similarities between pulsed flow control and unsteady wake motion are highlighted.</description><subject>Applied sciences</subject><subject>Boundary layer and shear turbulence</subject><subject>Continuous cycle engines: steam and gas turbines, jet engines</subject><subject>Engines and turbines</subject><subject>Exact sciences and technology</subject><subject>Fluid dynamics</subject><subject>Fundamental areas of phenomenology (including applications)</subject><subject>Mechanical engineering. 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Machine design</topic><topic>Physics</topic><topic>Transition to turbulence</topic><topic>Turbulent flows, convection, and heat transfer</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Bons, Jeffrey P</creatorcontrib><creatorcontrib>Reimann, Daniel</creatorcontrib><creatorcontrib>Bloxham, Matthew</creatorcontrib><collection>Pascal-Francis</collection><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>ANTE: Abstracts in New Technology & Engineering</collection><collection>Engineering Research Database</collection><jtitle>Journal of turbomachinery</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Bons, Jeffrey P</au><au>Reimann, Daniel</au><au>Bloxham, Matthew</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Separated Flow Transition on an LP Turbine Blade With Pulsed Flow Control</atitle><jtitle>Journal of turbomachinery</jtitle><stitle>J. Turbomach</stitle><date>2008-04-01</date><risdate>2008</risdate><volume>130</volume><issue>2</issue><spage>021014 (8)</spage><epage>021014 (8)</epage><pages>021014 (8)-021014 (8)</pages><issn>0889-504X</issn><eissn>1528-8900</eissn><coden>JOTUEI</coden><abstract>Flow measurements were made on a highly loaded low pressure turbine blade in a low-speed linear cascade facility. The blade has a design Zweifel coefficient of 1.34 with a peak pressure coefficient near 47% axial chord (midloaded). Flow and surface pressure data were taken for Rec=20,000 with 3% inlet freestream turbulence. For these operating conditions, a large separation bubble forms over the downstream portion of the blade suction surface, extending from 59% to 86% axial chord. Single-element hot-film measurements were acquired to clearly identify the role of boundary layer transition in this separated region. Higher-order turbulence statistics were used to identify transition and separation zones. Similar measurements were also made in the presence of unsteady forcing using pulsed vortex generator jets just upstream of the separation bubble (50% cx). Measurements provide a comprehensive picture of the interaction of boundary layer transition and separation in this unsteady environment. Similarities between pulsed flow control and unsteady wake motion are highlighted.</abstract><cop>New York, NY</cop><pub>ASME</pub><doi>10.1115/1.2751149</doi></addata></record> |
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| ispartof | Journal of turbomachinery, 2008-04, Vol.130 (2), p.021014 (8)-021014 (8) |
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| source | ASME Transactions Journals (Current) |
| subjects | Applied sciences Boundary layer and shear turbulence Continuous cycle engines: steam and gas turbines, jet engines Engines and turbines Exact sciences and technology Fluid dynamics Fundamental areas of phenomenology (including applications) Mechanical engineering. Machine design Physics Transition to turbulence Turbulent flows, convection, and heat transfer |
| title | Separated Flow Transition on an LP Turbine Blade With Pulsed Flow Control |
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