Experimental and Numerical Investigation of Flow Field and Downstream Surface Temperatures of Cylindrical and Diffuser Shaped Film Cooling Holes1

Kampe, Tilman auf dem; Völker, Stefan; Sämel, Torsten; Heneka, Christian; Ladisch, Helge; Schulz, Achmed; Bauer, Hans‐Jörg

doi:10.1115/1.4006336

Cited by 15 publications

(9 citation statements)

References 26 publications

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“…Only one study was found to report measured flowfields for shaped holes with high-density ratio jet injection at elevated freestream turbulence intensity [12]. The present study builds upon those results by contrasting shaped hole performance at low and high freestream turbulence intensities at conditions not previously reported in literature.…”

Section: Previous Studiessupporting

confidence: 68%

Effect of High Freestream Turbulence on Flowfields of Shaped Film Cooling Holes

Schroeder

Thole

2016

Journal of Turbomachinery

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Shaped film cooling holes have become a standard geometry for protecting gas turbine components. Few studies, however, have reported flowfield measurements for moderately expanded shaped holes and even fewer have reported on the effects of high freestream turbulence intensity relevant to gas turbine airfoils. This study presents detailed flowfield and adiabatic effectiveness measurements for a shaped hole at freestream turbulence intensities of 0.5% and 13%. Test conditions included blowing ratios of 1.5 and 3 at a density ratio of 1.5. Measured flowfields revealed a counter-rotating vortex pair (CRVP) and high jet penetration into the mainstream at the blowing ratio of 3. Elevated freestream turbulence had a minimal effect on mean velocities and rather acted by increasing turbulence intensity around the coolant jet, resulting in increased lateral spreading of coolant.

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Section: Previous Studiessupporting

confidence: 68%

Effect of High Freestream Turbulence on Flowfields of Shaped Film Cooling Holes

Schroeder

Thole

2016

Journal of Turbomachinery

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“…Even if it is not reported in the results, this overlapping phenomena of the jets was found on all the measured row for both geometries (up to the fourth) with a progressive weakening of the phenomenon moving away from the swirler. Finally, looking to the lateral spots of the jets from the previous row (s = ±2.5), it is clear how the cores of the jets assume a stretched and elongated shape, far from the classical behaviour in the presence of an axial flow [20][21][22]. It is possible to speculate that such a strong deviation underline that any correlative approach to estimate cooling effectiveness based on formulations developed on fundamental test cases could be completely ineffective especially in the near dome region.…”

Section: Swirling Flow Characterizationmentioning

confidence: 95%

Unsteady Flow Field Characterization of Effusion Cooling Systems with Swirling Main Flow: Comparison Between Cylindrical and Shaped Holes

et al. 2020

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The presence of injectors with strongly swirled flows, used to promote flame stability in the combustion chambers of gas turbines, influences the behaviour of the effusion cooling jets and consequently of the liner’s cooling capabilities. For this reason, unsteady behaviour of the jets in the presence of swirling flow requires a characterization by means of experimental flow field analyses. The experimental setup of this work consists of a non-reactive single-sector linear combustor test rig, scaled up with respect to the real engine geometry to increase spatial resolution and to reduce the frequencies of the unsteadiness. It is equipped with a radial swirler and multi-perforated effusion plates to simulate the liner cooling system. Two effusion plates were tested and compared: with cylindrical and with laid-back fan-shaped 7-7-7 holes in staggered arrangement. Time resolved Particle Image Velocimetry has been carried out: the unsteady characteristics of the jets, promoted by the intermittent interactions with the turbulent mainstream, have been investigated as their vortex structures and turbulent decay. The results demonstrate how an unsteady analysis is necessary to provide a complete characterization of the coolant behaviour and of its turbulent mixing with mainflow, which affect, in turn, the film cooling capability and liner’s lifetime.

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“…This paper, likewise in the efforts by Kampe et al [23], aims at the clarification of detailed velocity field associated with cooling holes using 3D-LDV and their characteristics in film effectiveness on the wall measured by IR camera. This paper especially deals with multiple cooling holes with two types of in-line configurations.…”

Section: Introductionmentioning

confidence: 97%

“…It was concluded that the main reason behind poorer film cooling performance at higher turbulent level is due to the enhancement of the mixing between the coolant and the mainstream air which lead to coolant temperature drop thus reducing its cooling capacity. Kampe et al [23] presented a complete study of diffuser shape film cooling holes covering both the thermal and the aerodynamics aspects. The thermal measurements have been made by IR camera while both PIV and LDV have been used in the aerodynamics measurements.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigations on Aero-Thermal Interaction of Film Cooling Airs Ejected From Multiple Holes: Shallow Hole Angle

Abdullah

Funazaki

Onodera

et al. 2012

Volume 4: Heat Transfer, Parts a and B

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This paper presents thermal and aerodynamics investigations of multiple cooling holes with shallow hole angle. Three test models have been considered namely TMA, TMB and TMG. TMB is acting as the baseline test model having 35° hole angle cooling holes. The other two test models; TMA and TMG, have a shallow hole angle of 20° with different lateral pitch distance of 6D and 3D respectively. Total of twenty conventional cylindrical cooling holes have been arranged to form a five times four matrix. All three test models have been considered in the thermal investigations with only the shallow hole angle test models have been considered for the aerodynamics investigation. The film cooling effectiveness has been measured by means of infrared thermography while 3D-LDV has been utilized for the flowfield measurements. The measurements were carried out at single Reynolds number base on the hole diameter of 6200 at three different blowing ratios of 0.5, 1.0 and 2.0. All three blowing ratios have been considered in the thermal investigations with only the latter two blowing ratios were considered in the aerodynamics investigation. The results are presented in the form of contour plot of various variables including film cooling effectiveness, normalized u, v, and w velocities, normalized root mean square of u velocity and Reynolds stress tensors. Distribution of laterally average film cooling effectiveness along the x-axis are also presented, showing that the 20° hole angle cooling holes provide a very promising results particularly at high blowing ratio. The velocities contours clearly capture the flow structure of the film cooling jets, along with the effects of blowing ratios and lateral pitch on the flowfield.

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Experimental and Numerical Investigation of Flow Field and Downstream Surface Temperatures of Cylindrical and Diffuser Shaped Film Cooling Holes1

Cited by 15 publications

References 26 publications

Effect of High Freestream Turbulence on Flowfields of Shaped Film Cooling Holes

Effect of High Freestream Turbulence on Flowfields of Shaped Film Cooling Holes

Unsteady Flow Field Characterization of Effusion Cooling Systems with Swirling Main Flow: Comparison Between Cylindrical and Shaped Holes

Experimental Investigations on Aero-Thermal Interaction of Film Cooling Airs Ejected From Multiple Holes: Shallow Hole Angle

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