Quantification of Cooled Film Thermal Protection Using Net Heat Flux Reduction within Transonic Environments

Considered are NHFR or net heat flux reduction data in order to illustrate and quantify turbulent thermal convection phenomena within a unique and intricate cooled film environment along the extremity end of a transonic turbine airfoil with a rim in the form of a squealer. Of particular focus are th...

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Veröffentlicht in:	Thermal engineering Jg. 72; H. 10; S. 802 - 816
Hauptverfasser:	Ligrani, P., Knox, N.
Format:	Journal Article
Sprache:	Englisch
Veröffentlicht:	Moscow Pleiades Publishing 01.10.2025 Springer Nature B.V
Schlagworte:	Airfoils Blade tips Boundary layers Combined-Cycle Power Plants and Their Auxiliary Equipment Convection cooling Cooling Engineering Engineering Thermodynamics Free convection Gas-Turbine Heat and Mass Transfer Heat flux Heat transfer Investigations Ratios Reynolds number Static pressure Steam-Turbine Temperature Thermal protection Turbines Velocity blowing ratio tip gap net heat flux reduction transonic flow cooled film squealer turbine airfoil
ISSN:	0040-6015, 1555-6301
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Abstract	Considered are NHFR or net heat flux reduction data in order to illustrate and quantify turbulent thermal convection phenomena within a unique and intricate cooled film environment along the extremity end of a transonic turbine airfoil with a rim in the form of a squealer. Of particular focus are the consequences of modifying the magnitude of GAP (tip gap magnitude) which is adjacent to the outer end of the airfoil. Data are given for a variety of cooled film ratio of blowing conditions, as the coolant film is provided by two separate plenums that are connected to a row of holes which are located along the top segment of the concave surface of the blade, as well as to two dusting cooled film holes located on the end extremity of the blade. Line-averaged NHFR data show different dependence upon RoB u and RoB d ratios of blowing, depending upon the magnitude of GAP. Especially for the trailing edge portion of the squealer tip surface of the airfoil, NHFR data vary significantly with aft ratio of blowing RoB d for the 1.2 mm or smaller GAP arrangement, whereas very little variation with RoB d is present for the 2.0 mm or larger GAP environment. Here, GAP is the thickness of the flow gap at the blade tip. In addition, line-averaged NHFR data associated with the smaller GAP are often higher than values associated with the larger GAP, when compared for the same squealer surface airfoil tip locations, and at the same approximate RoB u and RoB d ratios of blowing. The flow and local static pressure variations within tip gap regions, which vary as the magnitude of GAP is changed, are less influential in regard to the data associated with the top portion of the concave surface of the two-dimensional airfoil. The impact of the present arrangements and configuration is new and unique NHFR results for different GAP values for complex boundary layer and separation flow environments, which are different from all other data which are available within the archival literature.
AbstractList	Considered are NHFR or net heat flux reduction data in order to illustrate and quantify turbulent thermal convection phenomena within a unique and intricate cooled film environment along the extremity end of a transonic turbine airfoil with a rim in the form of a squealer. Of particular focus are the consequences of modifying the magnitude of GAP (tip gap magnitude) which is adjacent to the outer end of the airfoil. Data are given for a variety of cooled film ratio of blowing conditions, as the coolant film is provided by two separate plenums that are connected to a row of holes which are located along the top segment of the concave surface of the blade, as well as to two dusting cooled film holes located on the end extremity of the blade. Line-averaged NHFR data show different dependence upon RoB u and RoB d ratios of blowing, depending upon the magnitude of GAP. Especially for the trailing edge portion of the squealer tip surface of the airfoil, NHFR data vary significantly with aft ratio of blowing RoB d for the 1.2 mm or smaller GAP arrangement, whereas very little variation with RoB d is present for the 2.0 mm or larger GAP environment. Here, GAP is the thickness of the flow gap at the blade tip. In addition, line-averaged NHFR data associated with the smaller GAP are often higher than values associated with the larger GAP, when compared for the same squealer surface airfoil tip locations, and at the same approximate RoB u and RoB d ratios of blowing. The flow and local static pressure variations within tip gap regions, which vary as the magnitude of GAP is changed, are less influential in regard to the data associated with the top portion of the concave surface of the two-dimensional airfoil. The impact of the present arrangements and configuration is new and unique NHFR results for different GAP values for complex boundary layer and separation flow environments, which are different from all other data which are available within the archival literature. Considered are NHFR or net heat flux reduction data in order to illustrate and quantify turbulent thermal convection phenomena within a unique and intricate cooled film environment along the extremity end of a transonic turbine airfoil with a rim in the form of a squealer. Of particular focus are the consequences of modifying the magnitude of GAP (tip gap magnitude) which is adjacent to the outer end of the airfoil. Data are given for a variety of cooled film ratio of blowing conditions, as the coolant film is provided by two separate plenums that are connected to a row of holes which are located along the top segment of the concave surface of the blade, as well as to two dusting cooled film holes located on the end extremity of the blade. Line-averaged NHFR data show different dependence upon RoBu and RoBd ratios of blowing, depending upon the magnitude of GAP. Especially for the trailing edge portion of the squealer tip surface of the airfoil, NHFR data vary significantly with aft ratio of blowing RoBd for the 1.2 mm or smaller GAP arrangement, whereas very little variation with RoBd is present for the 2.0 mm or larger GAP environment. Here, GAP is the thickness of the flow gap at the blade tip. In addition, line-averaged NHFR data associated with the smaller GAP are often higher than values associated with the larger GAP, when compared for the same squealer surface airfoil tip locations, and at the same approximate RoBu and RoBd ratios of blowing. The flow and local static pressure variations within tip gap regions, which vary as the magnitude of GAP is changed, are less influential in regard to the data associated with the top portion of the concave surface of the two-dimensional airfoil. The impact of the present arrangements and configuration is new and unique NHFR results for different GAP values for complex boundary layer and separation flow environments, which are different from all other data which are available within the archival literature.
Author	Ligrani, P. Knox, N.
Author_xml	– sequence: 1 givenname: P. surname: Ligrani fullname: Ligrani, P. email: pml0006@uah.edu organization: University of Alabama in Huntsville – sequence: 2 givenname: N. surname: Knox fullname: Knox, N. organization: University of Alabama in Huntsville
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Cites_doi	10.1115/1.4005978 10.2514/1.B34299 10.1115/1.4001810 10.1016/0894-1777(88)90043-X 10.1115/1.4045466 10.1016/j.ijheatmasstransfer.2023.125043
ContentType	Journal Article
Copyright	Pleiades Publishing, Ltd. 2025 ISSN 0040-6015, Thermal Engineering, 2025, Vol. 72, No. 10, pp. 802–816. © Pleiades Publishing, Ltd., 2025.Russian Text © The Author(s), 2025, published in Teploenergetika. Pleiades Publishing, Ltd. 2025.
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References	G. Fulmer (1721_CR5) 2024; 221 R. J. Moffat (1721_CR7) 1988; 1 S. Sakaoglu (1721_CR4) 2020; 142 J. L. Rutledge (1721_CR2) 2012; 134 C. Zhou (1721_CR3) 2012; 28 S. J. Kline (1721_CR6) 1953; 75 J. L. Rutledge (1721_CR1) 2010; 132
References_xml	– volume: 134 start-page: 7 year: 2012 ident: 1721_CR2 publication-title: J. Eng. Gas Turbines Power doi: 10.1115/1.4005978 – volume: 28 start-page: 900 year: 2012 ident: 1721_CR3 publication-title: J. Propul. Power doi: 10.2514/1.B34299 – volume: 132 start-page: 12 year: 2010 ident: 1721_CR1 publication-title: J. Eng. Gas Turbines Power doi: 10.1115/1.4001810 – volume: 1 start-page: 3 year: 1988 ident: 1721_CR7 publication-title: Exp. Therm. Fluid Sci. doi: 10.1016/0894-1777(88)90043-X – volume: 142 start-page: 2 year: 2020 ident: 1721_CR4 publication-title: J. Turbomach. doi: 10.1115/1.4045466 – volume: 221 start-page: 125043 year: 2024 ident: 1721_CR5 publication-title: Int. J. Heat Mass Transfer doi: 10.1016/j.ijheatmasstransfer.2023.125043 – volume: 75 start-page: 3 year: 1953 ident: 1721_CR6 publication-title: Mech. Eng.
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SubjectTerms	Airfoils Blade tips Boundary layers Combined-Cycle Power Plants and Their Auxiliary Equipment Convection cooling Cooling Engineering Engineering Thermodynamics Free convection Gas-Turbine Heat and Mass Transfer Heat flux Heat transfer Investigations Ratios Reynolds number Static pressure Steam-Turbine Temperature Thermal protection Turbines Velocity
Title	Quantification of Cooled Film Thermal Protection Using Net Heat Flux Reduction within Transonic Environments
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