Overall and Adiabatic Effectiveness Values on a Scaled Up, Simulated Gas Turbine Vane
Recent advances in computational power have made conjugate heat transfer simulations of fully conducting, film cooled turbine components feasible. However, experimental data available with which to validate conjugate heat transfer simulations is limited. This paper presents experimental measurements...
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| Veröffentlicht in: | Journal of turbomachinery 2013-09, Vol.135 (5), p.1-10 |
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| container_title | Journal of turbomachinery |
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| creator | Dees, Jason E. Bogard, David G. Ledezma, Gustavo A. Laskowski, Gregory M. |
| description | Recent advances in computational power have made conjugate heat transfer simulations of fully conducting, film cooled turbine components feasible. However, experimental data available with which to validate conjugate heat transfer simulations is limited. This paper presents experimental measurements of external surface temperature on the suction side of a scaled up, fully conducting, cooled gas turbine vane. The experimental model utilizes the matched Bi method, which produces nondimensional surface temperature measurements that are representative of engine conditions. Adiabatic effectiveness values were measured on an identical near adiabatic vane with an identical geometry and cooling configuration. In addition to providing a valuable data set for computational code validation, the data shows the effect of film cooling on the surface temperature of a film cooled part. As expected, in nearly all instances, the addition of film cooling was seen to decrease the overall surface temperature. However, due to the effect of film injection causing early boundary layer transition, film cooling at a high momentum flux ratio was shown to actually increase surface temperature over 0.35 |
| doi_str_mv | 10.1115/1.4023105 |
| format | Article |
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However, experimental data available with which to validate conjugate heat transfer simulations is limited. This paper presents experimental measurements of external surface temperature on the suction side of a scaled up, fully conducting, cooled gas turbine vane. The experimental model utilizes the matched Bi method, which produces nondimensional surface temperature measurements that are representative of engine conditions. Adiabatic effectiveness values were measured on an identical near adiabatic vane with an identical geometry and cooling configuration. In addition to providing a valuable data set for computational code validation, the data shows the effect of film cooling on the surface temperature of a film cooled part. As expected, in nearly all instances, the addition of film cooling was seen to decrease the overall surface temperature. However, due to the effect of film injection causing early boundary layer transition, film cooling at a high momentum flux ratio was shown to actually increase surface temperature over 0.35 < s/C < 0.45.</description><identifier>ISSN: 0889-504X</identifier><identifier>EISSN: 1528-8900</identifier><identifier>DOI: 10.1115/1.4023105</identifier><identifier>CODEN: JOTUEI</identifier><language>eng</language><publisher>New York, NY: ASME</publisher><subject>Adiabatic flow ; Analytical and numerical techniques ; Applied sciences ; Computer simulation ; Conduction ; Continuous cycle engines: steam and gas turbines, jet engines ; Engines and turbines ; Exact sciences and technology ; Film cooling ; Fluid dynamics ; Fundamental areas of phenomenology (including applications) ; Gas turbines ; Heat transfer ; Mechanical engineering. Machine design ; Physics ; Surface temperature ; Transition to turbulence ; Turbulent flows, convection, and heat transfer ; Vanes</subject><ispartof>Journal of turbomachinery, 2013-09, Vol.135 (5), p.1-10</ispartof><rights>2014 INIST-CNRS</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-a312t-a6f3ffcf91224d3232a0a73b90841f6b5842c5b8d72540b444c47c8e7e28d1c23</citedby><cites>FETCH-LOGICAL-a312t-a6f3ffcf91224d3232a0a73b90841f6b5842c5b8d72540b444c47c8e7e28d1c23</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,780,784,27924,27925,38520</link.rule.ids><backlink>$$Uhttp://pascal-francis.inist.fr/vibad/index.php?action=getRecordDetail&idt=27770875$$DView record in Pascal Francis$$Hfree_for_read</backlink></links><search><creatorcontrib>Dees, Jason E.</creatorcontrib><creatorcontrib>Bogard, David G.</creatorcontrib><creatorcontrib>Ledezma, Gustavo A.</creatorcontrib><creatorcontrib>Laskowski, Gregory M.</creatorcontrib><title>Overall and Adiabatic Effectiveness Values on a Scaled Up, Simulated Gas Turbine Vane</title><title>Journal of turbomachinery</title><addtitle>J. Turbomach</addtitle><description>Recent advances in computational power have made conjugate heat transfer simulations of fully conducting, film cooled turbine components feasible. However, experimental data available with which to validate conjugate heat transfer simulations is limited. This paper presents experimental measurements of external surface temperature on the suction side of a scaled up, fully conducting, cooled gas turbine vane. The experimental model utilizes the matched Bi method, which produces nondimensional surface temperature measurements that are representative of engine conditions. Adiabatic effectiveness values were measured on an identical near adiabatic vane with an identical geometry and cooling configuration. In addition to providing a valuable data set for computational code validation, the data shows the effect of film cooling on the surface temperature of a film cooled part. As expected, in nearly all instances, the addition of film cooling was seen to decrease the overall surface temperature. However, due to the effect of film injection causing early boundary layer transition, film cooling at a high momentum flux ratio was shown to actually increase surface temperature over 0.35 < s/C < 0.45.</description><subject>Adiabatic flow</subject><subject>Analytical and numerical techniques</subject><subject>Applied sciences</subject><subject>Computer simulation</subject><subject>Conduction</subject><subject>Continuous cycle engines: steam and gas turbines, jet engines</subject><subject>Engines and turbines</subject><subject>Exact sciences and technology</subject><subject>Film cooling</subject><subject>Fluid dynamics</subject><subject>Fundamental areas of phenomenology (including applications)</subject><subject>Gas turbines</subject><subject>Heat transfer</subject><subject>Mechanical engineering. Machine design</subject><subject>Physics</subject><subject>Surface temperature</subject><subject>Transition to turbulence</subject><subject>Turbulent flows, convection, and heat transfer</subject><subject>Vanes</subject><issn>0889-504X</issn><issn>1528-8900</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2013</creationdate><recordtype>article</recordtype><recordid>eNo9kM1LAzEUxIMoWKsHz15yERTcms9N9iilVqHQQ1vxFt5mE9iy3a3JbsH_3pQWT48HvxlmBqF7SiaUUvlKJ4IwTom8QCMqmc50QcglGhGti0wS8X2NbmLcEkI5l2KENsuDC9A0GNoKv1U1lNDXFs-8d7avD651MeIvaAYXcddiwCsLjavwZv-CV_VuaKBP3xwiXg-hrFuX4NbdoisPTXR35ztGm_fZevqRLZbzz-nbIgNOWZ9B7rn31heUMVFxxhkQULwsiBbU56XUgllZ6koxKUgphLBCWe2UY7qilvExejr57kP3kyL2ZldH65omZeiGaNICpBAyFzShzyfUhi7G4LzZh3oH4ddQYo7TGWrO0yX28WwLMdX1AVpbx38BU0oRrY7cw4mDuHNm2w2hTW2NECxXOf8DgN90XQ</recordid><startdate>20130901</startdate><enddate>20130901</enddate><creator>Dees, Jason E.</creator><creator>Bogard, David G.</creator><creator>Ledezma, Gustavo A.</creator><creator>Laskowski, Gregory M.</creator><general>ASME</general><general>American Society of Mechanical Engineers</general><scope>IQODW</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>F28</scope><scope>FR3</scope><scope>H8D</scope><scope>L7M</scope></search><sort><creationdate>20130901</creationdate><title>Overall and Adiabatic Effectiveness Values on a Scaled Up, Simulated Gas Turbine Vane</title><author>Dees, Jason E. ; Bogard, David G. ; Ledezma, Gustavo A. ; Laskowski, Gregory M.</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a312t-a6f3ffcf91224d3232a0a73b90841f6b5842c5b8d72540b444c47c8e7e28d1c23</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2013</creationdate><topic>Adiabatic flow</topic><topic>Analytical and numerical techniques</topic><topic>Applied sciences</topic><topic>Computer simulation</topic><topic>Conduction</topic><topic>Continuous cycle engines: steam and gas turbines, jet engines</topic><topic>Engines and turbines</topic><topic>Exact sciences and technology</topic><topic>Film cooling</topic><topic>Fluid dynamics</topic><topic>Fundamental areas of phenomenology (including applications)</topic><topic>Gas turbines</topic><topic>Heat transfer</topic><topic>Mechanical engineering. Machine design</topic><topic>Physics</topic><topic>Surface temperature</topic><topic>Transition to turbulence</topic><topic>Turbulent flows, convection, and heat transfer</topic><topic>Vanes</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Dees, Jason E.</creatorcontrib><creatorcontrib>Bogard, David G.</creatorcontrib><creatorcontrib>Ledezma, Gustavo A.</creatorcontrib><creatorcontrib>Laskowski, Gregory M.</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><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>Journal of turbomachinery</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Dees, Jason E.</au><au>Bogard, David G.</au><au>Ledezma, Gustavo A.</au><au>Laskowski, Gregory M.</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Overall and Adiabatic Effectiveness Values on a Scaled Up, Simulated Gas Turbine Vane</atitle><jtitle>Journal of turbomachinery</jtitle><stitle>J. Turbomach</stitle><date>2013-09-01</date><risdate>2013</risdate><volume>135</volume><issue>5</issue><spage>1</spage><epage>10</epage><pages>1-10</pages><issn>0889-504X</issn><eissn>1528-8900</eissn><coden>JOTUEI</coden><abstract>Recent advances in computational power have made conjugate heat transfer simulations of fully conducting, film cooled turbine components feasible. However, experimental data available with which to validate conjugate heat transfer simulations is limited. This paper presents experimental measurements of external surface temperature on the suction side of a scaled up, fully conducting, cooled gas turbine vane. The experimental model utilizes the matched Bi method, which produces nondimensional surface temperature measurements that are representative of engine conditions. Adiabatic effectiveness values were measured on an identical near adiabatic vane with an identical geometry and cooling configuration. In addition to providing a valuable data set for computational code validation, the data shows the effect of film cooling on the surface temperature of a film cooled part. As expected, in nearly all instances, the addition of film cooling was seen to decrease the overall surface temperature. However, due to the effect of film injection causing early boundary layer transition, film cooling at a high momentum flux ratio was shown to actually increase surface temperature over 0.35 < s/C < 0.45.</abstract><cop>New York, NY</cop><pub>ASME</pub><doi>10.1115/1.4023105</doi><tpages>10</tpages></addata></record> |
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| ispartof | Journal of turbomachinery, 2013-09, Vol.135 (5), p.1-10 |
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| source | ASME Transactions Journals (Current); Alma/SFX Local Collection |
| subjects | Adiabatic flow Analytical and numerical techniques Applied sciences Computer simulation Conduction Continuous cycle engines: steam and gas turbines, jet engines Engines and turbines Exact sciences and technology Film cooling Fluid dynamics Fundamental areas of phenomenology (including applications) Gas turbines Heat transfer Mechanical engineering. Machine design Physics Surface temperature Transition to turbulence Turbulent flows, convection, and heat transfer Vanes |
| title | Overall and Adiabatic Effectiveness Values on a Scaled Up, Simulated Gas Turbine Vane |
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