Heat Transfer in a Complex Trailing Edge Passage for a High Pressure Turbine Blade: Part 1 — Experimental Measurements

Bunker, Ronald S.; Wetzel, Todd G.; Rigby, David L.

doi:10.1115/gt2002-30212

Cited by 10 publications

(4 citation statements)

References 12 publications

(8 reference statements)

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“…Jia et al [73] and Watanabe and Takahashi [99] include experimentally measured friction factors, Nusselt numbers, and streamwise velocity fluctuations, which are compared to numerically predicted results. Rigby and Bunker [85] employ a full threedimensional Navier-Stokes equation solver to investigate the same complex trailing edge passage of a high pressure turbine blade investigated experimentally by Bunker et al [61].…”

Section: Dimpled Surfacesmentioning

confidence: 99%

“…Jia et al [73] and Watanabe and Takahashi [99] include experimentally measured friction factors, Nusselt numbers, and streamwise velocity fluctuations, which are compared to numerically predicted results. Experimental investigation of a complex trailing edge passage of a high pressure turbine blade is described by Bunker et al [61]. Rigby and Bunker [85] employ a full three-dimensional Navier-Stokes equation solver to investigate the same arrangement.…”

Section: Effects Of Rotation On Local Nusselt Numbers Spatiallymentioning

confidence: 99%

See 1 more Smart Citation

Heat Transfer Augmentation Technologies for Internal Cooling of Turbine Components of Gas Turbine Engines

Ligrani

2013

International Journal of Rotating Machinery

167

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To provide an overview of the current state of the art of heat transfer augmentation schemes employed for internal cooling of turbine blades and components, results from an extensive literature review are presented with data from internal cooling channels, both with and without rotation. According to this survey, a very small number of existing investigations consider the use of combination devices for internal passage heat transfer augmentation. Examples are rib turbulators, pin fins, and dimples together, a combination of pin fins and dimples, and rib turbulators and pin fins in combination. The results of such studies are compared with data obtained prior to 2003 without rotation influences. Those data are comprised of heat transfer augmentation results for internal cooling channels, with rib turbulators, pin fins, dimpled surfaces, surfaces with protrusions, swirl chambers, or surface roughness. This comparison reveals that all of the new data, obtained since 2003, collect within the distribution of globally averaged data obtained from investigations conducted prior to 2003 (without rotation influences). The same conclusion in regard to data distributions is also reached in regard to globally averaged thermal performance parameters as they vary with friction factor ratio. These comparisons, made on the basis of such judgment criteria, lead to the conclusion that improvements in our ability to provide better spatially-averaged thermal protection have been minimal since 2003. When rotation is present, existing investigations provide little evidence of overall increases or decreases in overall thermal performance characteristics with rotation, at any value of rotation number, buoyancy parameter, density ratio, or Reynolds number. Comparisons between existing rotating channel experimental data and the results obtained prior to 2003, without rotation influences, also show that rotation has little effect on overall spatially-averaged thermal performance as a function of friction factor.

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Section: Dimpled Surfacesmentioning

confidence: 99%

“…Jia et al [73] and Watanabe and Takahashi [99] include experimentally measured friction factors, Nusselt numbers, and streamwise velocity fluctuations, which are compared to numerically predicted results. Experimental investigation of a complex trailing edge passage of a high pressure turbine blade is described by Bunker et al [61]. Rigby and Bunker [85] employ a full three-dimensional Navier-Stokes equation solver to investigate the same arrangement.…”

Section: Effects Of Rotation On Local Nusselt Numbers Spatiallymentioning

confidence: 99%

Heat Transfer Augmentation Technologies for Internal Cooling of Turbine Components of Gas Turbine Engines

Ligrani

2013

International Journal of Rotating Machinery

167

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“…Some previous works in high aspect ratio cooling channels include Bunker et al, Zhang et al, and Sparrow and Cur. In these studies, the channel aspect ratios are kept at 14:1, 10:1, and 18:1, respectively. Bunker et al tested a channel that combined the trailing edge and the adjacent rib channel of an aero engine airfoil (Bunker, Wetzel, & Rigby, 2002). Zhang et al utilized ribbed and grooved walls on the same surface in search for the optimum thermal performance (Zhang, Gu, & Han, 1994).…”

Section: Rib-shaped Turbulatorsmentioning

confidence: 99%

Effect of Rib Aspect Ratio on Heat Transfer and Friction in Rectangular Channels

Tran¹

2011

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The heat transfer and friction augmentation in the fully developed portion of a 2:1 aspect ratio rectangular channel with orthogonal ribs at channel Reynolds numbers of 20,000, 30,000, and 40,000 is studied both experimentally and computationally. Ribs are applied to the two opposite wide walls. The rib aspect ratio is varied systematically at 1, 3, and 5, with a constant rib height and constant rib pitch (rib-pitch-to-rib-height ratio of 10). The purpose of the study is to extend the knowledge of the performance of rectangular channels with ribs to include high aspect ratio ribs. The experimental investigation is performed using the transient Thermochromic Liquid Crystals technique to measure the distribution of the local Nusselt numbers on the ribbed walls. Overall channel pressure drop and friction factor augmentation is also obtained with the experimental setup. A numerical simulation is also performed by solving the 3-D Reynoldsaveraged Navier-Stokes equations using the realizable-k-ϵ turbulence model for closure. Flow visualization is obtained from the computational results as well as numerical predictions of local distributions of Nusselt numbers and overall channel pressure drop. Results indicate that with

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“…Nowadays complex multipass systems using several cooling methods in combination are widely used. Since such systems are often developed by combining results achieved from simplified single-pass experiments, there is a high demand for understanding such a system altogether [1][2][3]. Full cooling circuits of a blade differ from their single-pass predecessors mainly in geometrical complexity.…”

Section: Introductionmentioning

confidence: 99%

Transient Heat Transfer Experiments in Complex Passages

Poser

Wolfersdorf

Semmler

2005

Heat Transfer: Volume 1

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Transient heat transfer experiments were performed in a model of a multi-pass gas turbine blade cooling circuit. The inner surface of the Plexiglas model was coated with thermochromic liquid crystals in order to determine the internal heat transfer coefficients. A change in inlet temperature is applied using a precooled heat exchanger. As for simple geometries the analytical solution of Fourier's equation can often be directly used for data evaluation, one ought to pay attention to complex passages. The reason has to be seen that the flow in complex passages has to be characterized by local and time dependent fluid temperatures. As a direct consequence data evaluation might be limited to small evaluation areas especially far downstream. Otherwise the uncertainties in the heat transfer results will increase substantially. In the present study the sensitivity of the transient method for complex passages has been analyzed theoretically and applied experimentally.1

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Heat Transfer in a Complex Trailing Edge Passage for a High Pressure Turbine Blade: Part 1 — Experimental Measurements

Cited by 10 publications

References 12 publications

Heat Transfer Augmentation Technologies for Internal Cooling of Turbine Components of Gas Turbine Engines

Heat Transfer Augmentation Technologies for Internal Cooling of Turbine Components of Gas Turbine Engines

Effect of Rib Aspect Ratio on Heat Transfer and Friction in Rectangular Channels

Transient Heat Transfer Experiments in Complex Passages

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