Volume 20, Issue 3 No AccessFilm-Cooling Prediction on Turbine Blade Tip with Various Film Hole ConfigurationsHuitao Yang, Hamn-Ching Chen and Je-Chin HanHuitao Yang Texas A&M University, College Station, Texas 77843-3123Search for more papers by this author, Hamn-Ching Chen Texas A&M University, College Station, Texas 77843-3123Search for more papers by this author and Je-Chin Han Texas A&M University, College Station, Texas 77843-3123Search for more papers by this authorPublished Online:23 May 2012https://doi.org/10.2514/1.18422SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About Previous article Next article FiguresReferencesRelatedDetailsSee PDF for referencesCited byAerothermal performance analysis and knowledge discovery of film holes on the squealer tip of a gas turbine bladeInternational Journal of Thermal Sciences, Vol. 186Film cooling performance of multi-row casing injection in a turbine-rotor cascade under blade passingThermal Science and Engineering Progress, Vol. 38Digital modeling and simulation verification of five-axis laser processing of curved surfacesDusting Hole Film Cooling Heat Transfer on a Transonic Turbine Blade TipInternational Journal of Rotating Machinery, Vol. 2022Investigation of the film-cooling and flow characteristics of trapezoidal slot scheme on the blade tip with partial pressure side squealer in transonic flowInternational Journal of Thermal Sciences, Vol. 179Effect of Film Position on the Flow and Heat Transfer Characteristics of Full-Ribbed Rotor Tip22 February 2022 | Frontiers in Energy Research, Vol. 10Experimental study on film cooling performance of a turbine blade tip with a trapezoidal slot cooling scheme in transonic flow using PSP techniqueExperimental Thermal and Fluid Science, Vol. 130Optimization of Turbine Cascade Squealer Tip Cooling Design by Combining Shaping and Flow Injection15 June 2021 | Journal of Turbomachinery, Vol. 143, No. 11Investigation on film cooling and aerodynamic performance of blade tip with tangential jet cooling scheme at transonic flowAerospace Science and Technology, Vol. 934An aerothermal analysis of the effects of tip gap height and cavity depth of a gas turbine bladeInternational Journal of Thermal Sciences, Vol. 158On the Heat Transfer and Flow Structures’ Characteristics of the Turbine Blade Tip Underside With Dirt Purge Holes at Different Locations by Using Topological Analysis21 February 2019 | Journal of Turbomachinery, Vol. 141, No. 7Turbine Blade Tip External Cooling Technologies26 August 2018 | Aerospace, Vol. 5, No. 3Effect of film-hole configuration on film-cooling effectiveness of squealer tipsJournal of Thermal Science and Technology, Vol. 12, No. 1Effects of casing motion on tip leakage flow and film-cooling effectiveness of squealer tipsJournal of Thermal Science and Technology, Vol. 12, No. 2Effects of stress on phase separation in InxGa1−xN/GaN multiple quantum-wellsActa Materialia, Vol. 59, No. 10Gas Turbine Blade Tip Heat Transfer and Cooling: A Literature SurveyHeat Transfer Engineering, Vol. 31, No. 7Numerical study of film cooled rotor leading edge with tip clearance in 1-1/2 turbine stageInternational Journal of Heat and Mass Transfer, Vol. 51, No. 11-12 What's Popular Volume 20, Number 3July 2006 Crossmark TopicsAerodynamicsCoolantCooling TechnologyFinite Volume MethodFluid DynamicsHeat ConductionHeat TransferHeating, Ventilating, and Air ConditioningMass TransferNumerical Heat TransferThermodynamic PropertiesThermodynamicsThermophysics and Heat TransferTurbulence KeywordsHigh Pressure TurbineFilm CoolingCalculated Heat Transfer CoefficientsCamberReynolds Stress Turbulence ModelsCoolantReynolds Averaged Navier StokesFlow ConditionsVorticesMach NumberPDF Published online23 May 2012