Overall Effectiveness of a Blade Endwall With Jet Impingement and Film Cooling

Mensch, Amy; Thole, Karen A.

doi:10.1115/1.4025835

Cited by 69 publications

(38 citation statements)

References 39 publications

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“…Once validated, the simulations provide additional insight into endwall temperatures and heat transfer that cannot be easily measured. This study builds upon the experimental work by Mensch and Thole [2] on a conjugate endwall with impingement and film cooling, to examine the thermal effects of a TBC.…”

Section: Introductionmentioning

confidence: 99%

Conjugate Heat Transfer Measurements and Predictions of a Blade Endwall With a Thermal Barrier Coating

Mensch

Thole

Craven

2014

Journal of Turbomachinery

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Multiple thermal protection techniques, including thermal barrier coatings (TBCs), internal cooling and external cooling, are employed for gas turbine components to reduce metal temperatures and extend component life. Understanding the interaction of these cooling methods, in particular, provides valuable information for the design stage. The current study builds upon a conjugate heat transfer model of a blade endwall to examine the impact of a TBC on the cooling performance. The experimental data with and without TBC are compared to results from conjugate computational fluid dynamics (CFD) simulations. The cases considered include internal impingement jet cooling and film cooling at different blowing ratios with and without a TBC. Experimental and computational results indicate the TBC has a profound effect, reducing scaled wall temperatures for all cases. The TBC effect is shown to be more significant than the effect of increasing blowing ratio. The computational results, which agree fairly well to the experimental results, are used to explain why the improvement with TBC increases with blowing ratio. Additionally, the computational results reveal significant temperature gradients within the endwall, and information on the flow behavior within the impingement channel.

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Section: Introductionmentioning

confidence: 99%

Conjugate Heat Transfer Measurements and Predictions of a Blade Endwall With a Thermal Barrier Coating

Mensch

Thole

Craven

2014

Journal of Turbomachinery

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“…3, which shows the seven blade, six passage linear cascade. The blade geometry used was a generic airfoil common in the literature [1,2,22,24,[28][29][30][31][32][33][34][35][36]. The conducting portion of the endwall is shown in green.…”

Section: Experimental Methods and Uncertaintymentioning

confidence: 99%

“…The overall thermal performance of a turbine endwall geometry with impingement and film cooling was investigated by Mensch et al [1,2] with matched Bi experiments and simulations. The external heat transfer for an endwall differs from that of a flat plate, leading edge or airfoil surface, due to the influence of passage secondary flows including the horseshoe and passage vortices.…”

Section: Relevant Literaturementioning

confidence: 99%

“…The distribution of the external endwall heat transfer coefficients for the airfoil geometry in this study was investigated by Lynch et al [22] through both experiments and computational predictions with a constant wall heat flux boundary condition. For the conjugate endwall studies [1,2], the endwall was cooled with the same cooling features as the current study. Results indicated that the internal impingement cooling had a greater influence than film cooling on the scaled endwall temperatures.…”

Section: Relevant Literaturementioning

confidence: 99%

“…As will be discussed in the following sections, recent experiments and simulations have begun to investigate conjugate heat transfer effects to provide scaled metal temperatures. This study focus on the conjugate heat transfer results due to variations in the internal impingement cooling geometry, building upon the results for a blade endwall with impingement and film cooling by Mensch et al [1,2]. Conjugate experiments and computational simulations are used to examine the influence of internal impingement cooling geometry on wall temperatures and internal heat transfer coefficients.…”

Section: Introductionmentioning

confidence: 99%

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Conjugate heat transfer analysis of the effects of impingement channel height for a turbine blade endwall

Mensch

Thole

2015

International Journal of Heat and Mass Transfer

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Advancements in cooling for applications such as gas turbines components require improved understanding of the complex heat transfer mechanisms and the interactions between those mechanisms. Critical cooling applications often rely on multiple thermal protection techniques, including internal cooling and external film cooling in gas turbine airfoils, to efficiently cool components and limit the use of coolant. Most research to quantify the effectiveness of such cooling technologies for gas turbine applications has isolated internal and external cooling in separate experiments. The research presented in this paper uses a conjugate heat transfer approach to account for the combined effects of both internal and external cooling. The geometry used for this study is a turbine blade endwall that includes impingement and film cooling as well as the relevant conduction through the endwall. Appropriate geometric and flow parameters were scaled to ensure engine relevant dimensionless temperatures were obtained. Using the conjugate heat transfer approach, the effect of varying the height of the impingement channel was examined using spatially resolved external wall temperatures obtained from both experiments and simulations. A one-dimensional heat transfer analysis was used to derive the average internal heat transfer coefficients from the experimental results. Both experiments and simulations showed good agreement between area averaged cooling effectiveness and impingement heat transfer coefficients. The cooling effectiveness and heat transfer coefficients peaked for an impingement channel height of around three impingement hole diameters. However, the heat transfer coefficients were more sensitive than the overall effectiveness to the changes in height of the impingement channel.

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Flow and heat transfer studies of multijet impingement cooling for different configurations: A review

Gudla

Pujari

2022

Heat Trans

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Increasing the gas turbine engine's turbine intake temperature has long been a potential strategy for increasing the specific work output of the engine. However, the melting temperature of the turbine blades and vane material limits the maximum intake temperature. As a result, internal and external cooling techniques are commonly used to maintain the vane material in a safe condition. This study provided an overview of internal impingement cooling to highlight the significance of geometrical variations, such as flat plate, curve plate, and actual vanes. It was observed that flat and curved plate impingement heat transfer studies were reported extensively, whereas limited studies were found on the conjugate effects on airfoil surfaces. The importance of conjugate heat transfer studies and their impact has recently been described in the literature. In most of the literature, a wide range of instruments, such as Laser Doppler Velocimeter, Particle Image Velocimeter, liquid crystal sheets, and so forth, were used for experimental investigations. According to most studies, the local value of internal surface temperature and heat transfer coefficient are vital factors of local flow behavior. Jet‐to‐jet spacing, jet‐to‐plate spacing, jet hole diameter, and jet Reynolds numbers played a crucial role in both numerical and experimental analyses. Different geometric variations strongly influence flow behavior. Therefore, the usual method for determining interior temperature distributions and heat transfer coefficients by considering generalized geometries like the flat and curved plate may not produce accurate conjugate solutions. Most of the computational studies on the flat and curved plate indicate the usage of κ−ω shear stress transport and κ–ε realizable model to predict the heat transfer coefficient.

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Overall Effectiveness of a Blade Endwall With Jet Impingement and Film Cooling

Cited by 69 publications

References 39 publications

Conjugate Heat Transfer Measurements and Predictions of a Blade Endwall With a Thermal Barrier Coating

Conjugate Heat Transfer Measurements and Predictions of a Blade Endwall With a Thermal Barrier Coating

Conjugate heat transfer analysis of the effects of impingement channel height for a turbine blade endwall

Flow and heat transfer studies of multijet impingement cooling for different configurations: A review

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