Transonic Film Cooling Effectiveness from Shaped Holes on a Simulated Turbine Airfoil

Furukawa, Tetsuji; Ligrani, Phillip M.

doi:10.2514/2.6672

Cited by 37 publications

(6 citation statements)

References 22 publications

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“…The thermocouples located in high temperature gradients are excluded from calibration curve by some researchers. For example, Schulz 2000; Gritsch et al 1998;Fukukawa and Ligrani 2002;Won et al 2004 have employed the readings of only those thermocouples for calibration which are located approximately in uniform temperature areas. However, we have employed data of all the thermocouples for calibration in this thermographic analysis.…”

Section: Procedures For In-situ Calibrationmentioning

confidence: 99%

Application of infrared thermography for temperature distributions in fluid-saturated porous media

2016

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Section: Procedures For In-situ Calibrationmentioning

confidence: 99%

Application of infrared thermography for temperature distributions in fluid-saturated porous media

2016

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“…The magnitudes of longitudinal turbulence intensity used at the inlet of the test section are 0.9 percent, 5.5 percent, and 16.2 percent, where the latter values are produced using a mesh grid and cross-bars, respectively. Additional details on experimental apparatus and procedure details, including the Transonic Wind Tunnel, are provided by Zhang et al [5][6][7], Furukawa and Ligrani [67], and Zhang and Ligrani [8], including discussion of techniques to determine rough-surface skin friction coefficients from wake profile measurements [7]. Figure 1.…”

Section: Symmetric Airfoils With No Film Coolingmentioning

confidence: 99%

Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number

Ligrani

2012

International Journal of Rotating Machinery

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The influences of a variety of different physical phenomena are described as they affect the aerodynamic performance of turbine airfoils in compressible, high-speed flows with either subsonic or transonic Mach number distributions. The presented experimental and numerically predicted results are from a series of investigations which have taken place over the past 32 years. Considered are (i) symmetric airfoils with no film cooling, (ii) symmetric airfoils with film cooling, (iii) cambered vanes with no film cooling, and (iv) cambered vanes with film cooling. When no film cooling is employed on the symmetric airfoils and cambered vanes, experimentally measured and numerically predicted variations of freestream turbulence intensity, surface roughness, exit Mach number, and airfoil camber are considered as they influence local and integrated total pressure losses, deficits of local kinetic energy, Mach number deficits, area-averaged loss coefficients, mass-averaged total pressure loss coefficients, omega loss coefficients, second law loss parameters, and distributions of integrated aerodynamic loss. Similar quantities are measured, and similar parameters are considered when film-cooling is employed on airfoil suction surfaces, along with film cooling density ratio, blowing ratio, Mach number ratio, hole orientation, hole shape, and number of rows of holes.

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“…The University of Utah Transonic Wind Tunnel (TWT) is used for the study. Detailed descriptions of this blow-downtype facility are provided by Jackson et al [16] and Furukawa and Ligrani [17].…”

Section: Test Section and Flow Characteristicsmentioning

confidence: 99%

Wake Turbulence Structure Downstream of a Cambered Airfoil in Transonic Flow: Effects of Surface Roughness and Freestream Turbulence Intensity

Zhang

Ligrani

2006

International Journal of Rotating Machinery

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The wake turbulence structure of a cambered airfoil is studied experimentally, including the effects of surface roughness, at different freestream turbulence levels in a transonic flow. As the level of surface roughness increases, all wake profile quantities broaden significantly and nondimensional vortex shedding frequencies decrease. Freestream turbulence has little effect on the wake velocity profiles, turbulence structure, and vortex shedding frequency, especially downstream of airfoils with rough surfaces. Compared with data from a symmetric airfoil, wake profiles produced by the cambered airfoils also have significant dependence on surface roughness, but are less sensitive to variations of freestream turbulence intensity. The cambered airfoil also produces larger streamwise velocity deficits, and broader wakes compared to the symmetric airfoil.

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Transonic Film Cooling Effectiveness from Shaped Holes on a Simulated Turbine Airfoil

Cited by 37 publications

References 22 publications

Application of infrared thermography for temperature distributions in fluid-saturated porous media

Application of infrared thermography for temperature distributions in fluid-saturated porous media

Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number

Wake Turbulence Structure Downstream of a Cambered Airfoil in Transonic Flow: Effects of Surface Roughness and Freestream Turbulence Intensity

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