Numerical Investigation of Film Cooling over a Flat Plate with Varying Injection Angle

2017 ◽  
Vol 17 (17th International Conference) ◽  
pp. 1-16
Author(s):  
Abdelaziz Elareibi ◽  
Tarek Elnady ◽  
Ali Elmaihy ◽  
Salman Elshmarka
Keyword(s):  
Flat Plate ◽  
Numerical Investigation ◽  
Film Cooling ◽  
Injection Angle

scholarly journals Numerical Investigation of Film Cooling over a Flat Plate with Varying Injection Angle

2017 ◽  
Vol 17 (AEROSPACE SCIENCES) ◽  
pp. 1-16
Author(s):  
Abdelaziz Elareibi ◽  
Tarek Elnady ◽  
Ali Elmaihy ◽  
Salman Elshmarka
Keyword(s):  
Flat Plate ◽  
Numerical Investigation ◽  
Film Cooling ◽  
Injection Angle

The Influence of Density Difference Between Hot and Coolant Gas on Film Cooling by a Row of Holes: Predictions and Experiments

1992 ◽  
Vol 114 (4) ◽  
pp. 747-755 ◽  
Author(s):  
W. Haas ◽  
W. Rodi ◽  
B. Scho¨nung
Keyword(s):  
Boundary Layer ◽  
Flat Plate ◽  
Turbine Blade ◽  
Film Cooling ◽  
Density Ratio ◽  
Density Difference ◽  
Extended Model ◽  
Cooling Effectiveness ◽  
Film Cooling Effectiveness ◽  
Injection Angle

The two-dimensional boundary-layer procedure of Scho¨nung and Rodi [1] for calculating film cooling by a row of holes was extended to account for density differences between hot gas and injected coolant gas. The extensions concern the injection model for leaping over the immediate blowing region in the boundary-layer calculation and also the dispersion model for taking into account three-dimensional effects. The extended model is tested for a density ratio of ρj/ρe ≈ 2 for both flat-plate situations and film cooling on a model turbine blade. The predicted laterally averaged film cooling effectiveness is compared with measurements for these cases. Results for the flat-plate experiments were taken from the literature, while experiments for a model turbine blade are also described in this paper. For a fixed injection angle of 32 deg, the film cooling effectiveness was measured for various spacings and velocity ratios Uj/Ue. The density ratio ρj/ρe ≈ 2 was achieved by adding Freon to the injection gas. The results are compared with those reported in [2] for negligible density difference. At the same blowing rate M = Uj/Ue, the film cooling effectiveness was found to increase with the density ratio ρj/ρe. In general, the influence of the density difference is well predicted by the model.

scholarly journals Numerical Investigation of Adiabatic Film Cooling Effectiveness over Flat Plate with ESCR Shape Ramp Configuration

2021 ◽  
Vol 1 (2) ◽  
pp. 31-38
Author(s):  
Grine Mustapha ◽  
Ben Ali Kouchih Fatima ◽  
Boualem Khadidja ◽  
Azzi Abbès
Keyword(s):  
Flat Plate ◽  
Numerical Investigation ◽  
Film Cooling ◽  
Cooling Effectiveness ◽  
Film Cooling Effectiveness

scholarly journals Comparison of RANS and U-RANS for Flat Plate Film Cooling

2015 ◽  
Vol 773-774 ◽  
pp. 353-357
Author(s):  
Kamil Abdullah ◽  
Osama H. Abdulguad ◽  
Akmal Nizam Mohammed ◽  
Zaid Suleiman
Keyword(s):  
Flat Plate ◽  
Numerical Investigation ◽  
Thermal Performance ◽  
Film Cooling ◽  
Thermal Protection ◽  
Navier Stokes ◽  
Reynolds Average Navier Stokes ◽  
Cooling Hole ◽  
Turbulent Models ◽  
Reynolds Average

Film cooling has been extensively used to provide thermal protection for the external surfaces of gas turbine components. For the past 40 years, numerous number of film cooling hole designs and arrangements have been introduced. Due to broad designs and arrangements of film cooling, numerical investigation has been utilized to provide initial insight on the aerodynamics and thermal performance of the new film cooling designs or arrangements. The present work focuses on the numerical investigation of RANS and URANS analyses on a flat plate film cooling. The investigation aims to provide comparison between various turbulent models available for the Reynolds Average Navier Stokes (RANS) analyses and extended to unsteady Reynolds Average Navier Stokes (URANS). The numerical investigations make used of ANSYS CFX ver. 14 and were carried out at Reynolds Number, Re = 7,000 based on the hole diameter at blowing ratio, BR = 0.5. The results of the RANS analyses show significant influence of the turbulent models on the predicted aerodynamics and thermal performance of the film cooling. The result of URANS indicates limitation of RANS analyses to provide details on the eddied and vortices formation in film cooling flow structure.

The Influence of Density Difference Between Hot and Coolant Gas on Film Cooling by a Row of Holes: Predictions and Experiments

1991 ◽  
Author(s):  
W. Haas ◽  
W. Rodi ◽  
B. Schönung
Keyword(s):  
Boundary Layer ◽  
Flat Plate ◽  
Turbine Blade ◽  
Film Cooling ◽  
Density Ratio ◽  
Density Difference ◽  
Extended Model ◽  
Cooling Effectiveness ◽  
Film Cooling Effectiveness ◽  
Injection Angle

The two-dimensional boundary-layer procedure of Schönung and Rodi [1] for calculating film cooling by a row of holes was extended to account for density differences between hot gas and injected coolant gas. The extensions concern the injection model for leaping over the immediate blowing region in the boundary-layer calculation and also the dispersion model for taking into account three-dimensional effects. The extended model is tested for a density ratio of ρj/ρe ≈ 2 both for flat-plate situations and film cooling on a model turbine blade. The predicted laterally averaged film cooling effectiveness is compared with measurements for these cases. Results for the flat-plate experiments were taken from the literature, while experiments for a model turbine blade are also described in this paper. For a fixed injection angle of 32°, the film cooling effectiveness was measured for various spacings and velocity ratios Uj/Ue. The density ratio ρj/ρe ≈ 2 was achieved by adding Freon to the injection gas. The results are compared with those reported in [2] for negligible density difference. At the same blowing rate M = Uj/Ue, the film cooling effectiveness was found to increase with the density ratio ρj/ρe. In general, the influence of the density difference is well predicted by the model.

scholarly journals An Infrared Technique for Evaluating Turbine Airfoil Cooling Designs

1999 ◽  
Author(s):  
Patrick C. Sweeney ◽  
Jeffrey F. Rhodes
Keyword(s):  
Surface Temperature ◽  
Flat Plate ◽  
Film Cooling ◽  
Large Scale ◽  
Imaging System ◽  
Cost Effective ◽  
Hole Injection ◽  
Internal Cooling ◽  
Turbine Engine ◽  
Injection Angle

An experimental approach is used to evaluate turbine airfoil cooling designs for advanced gas turbine engine applications by incorporating double-wall film-cooled design features into large scale flat plate specimens. An infrared (IR) imaging system is used to make detailed, two-dimensional steady state measurements of flat plate surface temperature with spatial resolution on the order of 0.4 mm. The technique employs a cooled zinc selenide window transparent to infrared radiation and calibrates the IR temperature readings to reference thermocouples embedded in each specimen, yielding a surface temperature measurement accuracy of ±4 °C. With minimal thermocouple installation required, the flat plate/IR approach is cost effective, essentially non-intrusive, and produces abundant results quickly. Design concepts can proceed from art to part to data in a manner consistent with aggressive development schedules. The infrared technique is demonstrated here by considering the effect of film hole injection angle for a staggered array of film cooling holes integrated with a highly effective internal cooling pattern. Heated freestream air and room temperature cooling air are used to produce a nominal temperature ratio of 2 over a range of blowing ratios from 0.7 to 1.5. Results were obtained at hole angles of 90° and 30° for two different hole spacings and are presented in terms of overall cooling effectiveness.

An Infrared Technique for Evaluating Turbine Airfoil Cooling Designs

1999 ◽  
Vol 122 (1) ◽  
pp. 170-177 ◽  
Author(s):  
P. C. Sweeney ◽  
J. F. Rhodes
Keyword(s):  
Surface Temperature ◽  
Flat Plate ◽  
Film Cooling ◽  
Large Scale ◽  
Imaging System ◽  
Cost Effective ◽  
Hole Injection ◽  
Internal Cooling ◽  
Turbine Engine ◽  
Injection Angle

An experimental approach is used to evaluate turbine airfoil cooling designs for advanced gas turbine engine applications by incorporating double-wall film-cooled design features into large-scale flat plate specimens. An infrared (IR) imaging system is used to make detailed, two-dimensional steady-state measurements of flat plate surface temperature with spatial resolution on the order of 0.4 mm. The technique employs a cooled zinc selenide window transparent to infrared radiation and calibrates the IR temperature readings to reference thermocouples embedded in each specimen, yielding a surface temperature measurement accuracy of ±4°C. With minimal thermocouple installation required, the flat plate/IR approach is cost effective, essentially nonintrusive, and produces abundant results quickly. Design concepts can proceed from art to part to data in a manner consistent with aggressive development schedules. The infrared technique is demonstrated here by considering the effect of film hole injection angle for a staggered array of film cooling holes integrated with a highly effective internal cooling pattern. Heated free stream air and room temperature cooling air are used to produce a nominal temperature ratio of 2 over a range of blowing ratios from 0.7 to 1.5. Results were obtained at hole angles of 90 and 30 deg for two different hole spacings and are presented in terms of overall cooling effectiveness. [S0889-504X(00)01901-2]

Film Cooling Effectiveness Measurement of Fan-Shaped Holes Manufactured Using EDM Technique

2021 ◽  
Author(s):  
S. Rouina ◽  
H. Abdeh ◽  
G. Barigozzi ◽  
V. Odemondo ◽  
L. Abba ◽  
...  
Keyword(s):  
Flat Plate ◽  
Film Cooling ◽  
Cooling Effectiveness ◽  
Film Cooling Effectiveness ◽  
Injection Angle ◽  
Blowing Ratio ◽  
Pressure Sensitive ◽  
Geometric Factors ◽  
Expansion Angle ◽  
Effectiveness Measurement

Abstract In this study, the influence of geometric factors such as hole diameter (D), length-to-diameter ratio (L/D), injection angle (α), and lateral expansion angle (β) on film cooling effectiveness of holes made using EDM is experimentally investigated. Nine different cooling configurations were tested on a flat plate wind tunnel at various coolant Reynolds number (Rec) and coolant to mainstream blowing ratio (M). The considered flat plate model incorporates engine sized V-shaped holes. EDM reliability is assessed through a hole qualification process, while effectiveness was measured by the Pressure Sensitive Paint (PSP) technique. Results confirm the suitability of EDM for V-shaped hole manufacturing as long as a correct tolerance on β is prescribed. An accurate qualification of hole morphology is also recommended.

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