Effect of Rotation on a Gas Turbine Blade Internal Cooling System: Numerical Investigation

Massini, Daniele; Burberi, Emanuele; Carcasci, Carlo; Cocchi, Lorenzo; Facchini, Bruno; Armellini, Alessandro; Casarsa, Luca; Furlani, Luca

doi:10.1115/1.4034799

Cited by 30 publications

(8 citation statements)

References 36 publications

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“…Moving at Z ¼ 70 mm, this effect is amplified and the jet is spread all over the LE cavity. This evidence is confirmed by CFD analysis [38] and also helps to explain the recorded insensitivity of the overall cooling performances to rotation, presented in Fig. 11(a), which is in contrast to the open literature results [19][20][21][22][23][24][25].…”

Section: Resultssupporting

confidence: 79%

Effect of Rotation on a Gas Turbine Blade Internal Cooling System: Experimental Investigation

Massini

Burberi

Carcasci

et al. 2016

Volume 5B: Heat Transfer

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A detailed aerothermal characterization of an advanced leading edge cooling system has been performed by means of experimental measurements. Heat transfer coefficient distribution has been evaluated exploiting a steady-state technique using Thermocromic Liquid Crystals (TLC), while flow field has been investigated by means of Particle Image Velocimetry (PIV). The geometry key features are the multiple impinging jets and the four rows of coolant extraction holes, which mass flow rate distribution is representative of real engine working conditions. Tests have been performed in both static and rotating conditions, replicating a typical range of jet Reynolds number (Rej), from 10000 to 40000, and Rotation number (Roj) up to 0.05. Different cross-flow conditions (CR) have been used to simulate the three main blade regions (i.e. tip, mid and hub). The aerothermal field turned out to be rather complex, but a good agreement between heat transfer coefficient and flow field measurement has been found. In particular, jet bending strongly depends on crossflow intensity, while rotation has a weak effect on both jet velocity core and area-averaged Nusselt number. Rotational effects increase for the lower cross-flow tests. Heat transfer pattern shape has been found to be substantially Reynolds-independent.

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Section: Resultssupporting

confidence: 79%

Effect of Rotation on a Gas Turbine Blade Internal Cooling System: Experimental Investigation

Massini

Burberi

Carcasci

et al. 2016

Volume 5B: Heat Transfer

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“…The analysis of the heat transfer distribution on the inner side of the effusion plate is supported by CFD simulations: the combination of measured and calculated data enables a complete analysis of thermal and fluid-dynamic phenomena, and thus provides significant information on the unique behaviour of each geometry. A similar approach have been already followed by the authors in the past for the investigation of different cooling configurations based on impinging jets [14,15,16].…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical investigation on the role of holes arrangement on the heat transfer in impingement/effusion cooling schemes

Andreini

Cocchi

Facchini

et al. 2018

International Journal of Heat and Mass Transfer

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In the present work, two different impingement/effusion geometries have been investigated, both having staggered hole configuration and an equal number of impingement and effusion holes. The first geometry, which is designed in case of low coolant availability, has impingement hole pitch-to-diameter ratios of 10.5 in both orthogonal directions, a jet-to-target plate spacing of 6.5 hole diameters, with effusion holes inclined of 20 • with respect to the target surface. The second geometry, which is designed in case of high coolant availability, has impingement hole pitch-to-diameter ratios of 3.0, a jet-to-target plate spacing of 2.5 diameters and normal effusion holes. For each geometry, two relative arrangements between the impingement and effusion holes have been investigated, as well as various Reynolds numbers for the sparser geometry.The experimental investigation has been performed by applying a transient technique, using narrow band thermochromic liquid crystals (TLCs) for surface temperature measurement. A CFD analysis has also been performed in order to support interpretation of the results. Results show unique heat transfer patterns for every investigated geometry. Weak jet-jet interactions have been recorded for the sparser array geometry, while intense secondary peaks and a complex heat transfer pattern are observed for the denser one, which is also strongly influenced by the presence and position of effusion holes. For both the geometries, effusion holes increase heat transfer with respect to impingement-only, which can be mainly attributed to a reduction in flow recirculation for the sparser geometry and to the suppression of spent coolant flow for the denser one.

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“…Burberi et al [14] and Massini et al [15] experimentally and numerically investigated the effect of rotation on the jet impingement heat transfer with respect to the leading edge of the gas turbine blade. The Reynolds number of the jet varied from 10,000 to 40,000, and the rotation number of the jet (Roj) varied from 0 to 0.05.…”

Section: Introductionmentioning

confidence: 99%

Numerical Analysis and Experimental Validation of the Jet Impingement Cooling of a Turbine-Blade Leading Edge at Different Rotation Speeds

Safi

Hamdan

Omari

et al. 2023

Preprint

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Herein, experimental and numerical validation studies were conducted on internal channel cooling in which seven jets impinging inside a rotating semi-cylindrical channel. These studies were conducted by considering a Reynolds number of 7,500 for a jet at five rotation speeds (ranging from 0 to 200 rpm). Numerical analysis was performed using the shear stress transport (SST) k–ω turbulence model with a properly analyzed fine mesh containing eight million nodes. A test setup with required instrumentation was developed inhouse for this study. Two temperature measurement techniques, namely thermochromic liquid crystals (TLCs) and thermocouples, were adopted. Further, the target surface temperature contours were precisely analyzed by comparing the TLC temperature measurements with the numerical temperature results. The captured temperature contours indicated points of minimum-temperature regions, which corresponded to the jet impingement regions. By examining the temperature distribution along the axial centerline, a good agreement was established between the numerical results and the experimental measurements. For Reynolds number of 7,500, increasing ration speed from 0 to 250 rpm has reduced the variation in temperature between different jets. The size of inlet port to feeding duct has a strong imapact on jet formation, which led to different mass flow rate across jets. Furthermore, a small deviation between numerical and experimental data can be observed near the end side of the channel owing to the radial and lateral heat transfer losses and outlet flow restriction.

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Effect of Rotation on a Gas Turbine Blade Internal Cooling System: Numerical Investigation

Cited by 30 publications

References 36 publications

Effect of Rotation on a Gas Turbine Blade Internal Cooling System: Experimental Investigation

Effect of Rotation on a Gas Turbine Blade Internal Cooling System: Experimental Investigation

Experimental and numerical investigation on the role of holes arrangement on the heat transfer in impingement/effusion cooling schemes

Numerical Analysis and Experimental Validation of the Jet Impingement Cooling of a Turbine-Blade Leading Edge at Different Rotation Speeds

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