Heat Transfer Enhancement by Impingement Cooling in a Combustor Liner Heat Shield

Lauffer, Diane; Wolfersdorf, Jens von; Dahlke, Stefan; Liebe, R.

doi:10.1115/gt2007-27908

Cited by 7 publications

(4 citation statements)

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“…Thus, it was possible to avoid uncertainties due to comparing results from different experiments. More details on the equipment used for the TLC measurements are given in [11] and [12]. The evaluation of the TLC data was done with the program ProTeIn developed at the Institute of Aerospace Thermodynamics (ITLR).…”

Section: Measurement Methods and Equipmentmentioning

confidence: 99%

Experimental Study of Heat Transfer in Gas Turbine Blades Using a Transient Inverse Technique

Heidrich

Wolfersdorf

Schnieder

2009

Heat Transfer Engineering

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To enhance specific power output and thermal efficiency of gas turbine engines, industry searches for ways to increase the turbine inlet temperatures. Therefore, temperatures of turbine blades increase as well and necessitate active cooling of these components. Experimental design work on such internal cooling schemes is carried out to find acceptable compromises between heat transfer and pressure losses. It is often carried out by using transient thermochromic liquid crystal techniques in combination with Plexiglas models. However, for real turbine blades this experimental technique is inappropriate due to the lack of optical access. Therefore, to study actual turbine blades there is need for development of noninvasive, nondestructive methodologies. This article describes a measurement technique that allows determination of internal heat transfer coefficients of real turbine blades experimentally. Thus, a test rig with a rapidly responding heater was designed to fulfill the requirement of a sudden increase in the air temperature within the cooling passages. The outer surface temperatures were measured using infrared thermography. To estimate the spatial distribution of internal heat transfer coefficients from transient surface temperatures the inverse heat transfer problem was solved. As optimization algorithm the Levenberg-Marquardt method was chosen. Outer surface temperature data was measured for a rectangular reference model with rib turbulators and compared with simultaneously acquired data using the thermochromic liquid crystal technique. It is concluded that the new experimental measurement technique could be used to quantitatively determine internal heat transfer coefficients.

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Section: Measurement Methods and Equipmentmentioning

confidence: 99%

Experimental Study of Heat Transfer in Gas Turbine Blades Using a Transient Inverse Technique

Heidrich

Wolfersdorf

Schnieder

2009

Heat Transfer Engineering

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“…Esposito et al [5] performed related studies for the influence of corrugated walls and extended port geometries on the heat transfer of impingement cooling. Lauffer et al [6] investigated different impingement cooling schemes and showed an increase of the Nusselt number locally and spatially with an increasing jet Reynolds number.…”

Section: Related Past Investigationsmentioning

confidence: 99%

Impact of Swirl Flow on the Cooling Performance of an Effusion Cooled Combustor Liner

Wurm¹,

Schulz²,

Bauer

et al. 2012

Journal of Engineering for Gas Turbines and Power

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An experimental study on combustor liner cooling of modern direct lean injection combustion chambers using coolant ejection from both effusion cooling holes and a starter film has been conducted. The experimental setup consists of a generic scaled three sector planar rig in an open loop hot gas wind tunnel, which has been described earlier in Wurm et al. (2009, “A New Test Facility for Investigating the Interactions Between Swirl Flow and Wall Cooling Films in Combustors, Investigating the Interactions Between Swirl Flow and Wall Cooling Films in Combustors,” ASME Paper No. GT2009-59961). Experiments are performed without combustion. Realistic engine conditions are achieved by applying engine-realistic Reynolds numbers, Mach numbers, and density ratios. A particle image velocimetry (PIV) measurement technique is employed, which has been adjusted to allow for high resolution near wall velocity measurements with and without coolant ejection. As the main focus of the present study is a deeper understanding of the interaction of swirl flows and near wall cooling flows, wall pressure measurements are performed for the definition of local blowing ratios and to identify the impact on the local cooling performance. For thermal investigations an infrared thermography measurement technique is employed that allows high resolution thermal studies on the effusion cooled liner surface. The effects of different heat shield geometry on the flow field and performance of the cooling films are investigated in terms of near wall velocity distributions and film cooling effectiveness. Two different heat shield configurations are investigated which differ in shape and inclination angle of the so called heat shield lip. Operating conditions for the hot gas main flow are kept constant. The pressure drop across the effusion cooled liner is varied between 1% and 3% of the total pressure. Results show the impact of the swirled main flow on the stability of the starter film and on the effusion cooling performance. Stagnation areas which could be identified by wall pressure measurements are confirmed by PIV measurements. Thermal investigations reveal reduced cooling performance in the respective stagnation areas.

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“…In electronics and power electronics devices [1], personal computer central processing units [2], blades and casings of gas turbines [3][4][5][6][7][8][9][10], combustion chamber liners of gas turbine engines [11,12], and magnetically confined plasma fusion reactors [13,14] macroscale and microscale multi-jet impingement and impingement-effusion high-heat flux cooling systems are utilized. To enhance heat transfer, a very high, nearly uniform heat transfer coefficient (HTC) distribution can be obtained at the stagnation zones of immersed jets injected from multiple orifices or nozzles having a one-dimensional (1D) or two-dimensional (2D) configuration, located over a smooth or roughened impingement surface.…”

Section: Introductionmentioning

confidence: 99%

Heat Transfer Enhancement by Mitigating the Adverse Effects of Crossflow in a Multi-Jet Impingement Cooling System in Hexagonal Configuration by Coaxial Cylindrical Protrusion—Guide Vane Pairs

Untuç,

Unverdi

2023

Applied Sciences

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A novel compound multi-jet impingement system for enhanced cooling of a flat surface by augmenting its area with cylindrical protrusions (CPs) equipped with coaxial guide vanes (CGVs) and reducing deflection of jets by crossflow has been developed for high-heat removal applications. The cooling performance of coaxial circular jets impinging on the top faces of CPs placed in hexagonal configuration on a flat plate is evaluated by three-dimensional (3D) computational fluid dynamics (CFD) simulations. Jets impinging on the top faces of the protrusions are directed to their lateral faces and then to the base plate by the CGVs around the protrusions, resulting in up to 62.8% improvement in heat transfer rate with a minor increase in pressure drop. Effects of protrusion height and diameter on the pressure drop and cooling performance are studied for jet Reynolds (Re number range of 5000–20,000. Due to both shortened jet impingement lengths as the height of protrusions is increased and directing the expended fluid away from the impinging jets by CGVs, adverse effects of jet–crossflow interactions on cooling performance and fluid pumping power are significantly reduced. Performance evaluation criterion (PEC) of the novel compound multi-jet impingement cooling system (CMJICS) can be as high as 1.52.

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Heat Transfer Enhancement by Impingement Cooling in a Combustor Liner Heat Shield

Cited by 7 publications

References 0 publications

Experimental Study of Heat Transfer in Gas Turbine Blades Using a Transient Inverse Technique

Experimental Study of Heat Transfer in Gas Turbine Blades Using a Transient Inverse Technique

Impact of Swirl Flow on the Cooling Performance of an Effusion Cooled Combustor Liner

Heat Transfer Enhancement by Mitigating the Adverse Effects of Crossflow in a Multi-Jet Impingement Cooling System in Hexagonal Configuration by Coaxial Cylindrical Protrusion—Guide Vane Pairs

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