Characteristics of Partial Length Circular Pin Fins as Heat Transfer Augmentors for Airfoil Internal Cooling Passages

Arora, Sahil; Abdel-Messeh, W.

doi:10.1115/89-gt-87

Cited by 12 publications

(6 citation statements)

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“…Their results showed that the partial length pin fins did not outperform the full length fins in terms of heat transfer but when the heat transfer and pressure loss are both considered, some of their partial length pin fin arrays were superior. Arora and Abdel-Messeh [2] also investigated the partial length circular pin fin concept and found that both the array averaged heat transfer and friction factor decreases with increasing gap distance. Pin fins with oblong cross-sections are investigated by Metzger et al [3] for various pin orientations with respect to the main flow.…”

Section: Introductionmentioning

confidence: 99%

Elliptical Pin Fins as an Alternative to Circular Pin Fins for Gas Turbine Blade Cooling Applications: Part 1 — Endwall Heat Transfer and Total Pressure Loss Characteristics

Uzol

Camcı

2001

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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Detailed experimental investigation of the wall heat transfer enhancement and total pressure loss characteristics for two alternative elliptical pin fin arrays is conducted and the results are compared to the conventional circular pin fin arrays. Two different elliptical pin fin geometries with different major axis lengths are tested, both having a minor axis length equal to the circular fin diameter and positioned at zero degrees angle of attack to the free stream flow. The major axis lengths for the two elliptical fins are 1.67 and 2.5 times the circular fin diameter, respectively. The pin fin arrays with H/D = 1.5 are positioned in a staggered 2 row configuration with 3 fins in the first row and 2 fins in the second row with S/D = X/D = 2. Endwall heat transfer and total pressure loss measurements are performed two diameter downstream of the pin fin arrays (X/D = 2) in a rectangular cross-section tunnel with an aspect ratio of 4.8 and for varying Reynolds numbers between 10000 and 47000 based on the inlet velocity and the fin diameter. Liquid Crystal Thermography is used for the measurement of convective heat transfer coefficient distributions on the endwall inside the wake. The results show that the wall heat transfer enhancement capability of the circular pin fin array is about 25–30% higher than the elliptical pin fin arrays in average. However in terms of total pressure loss, the circular pin fin arrays generate 100–200% more pressure loss than the elliptical pin fin arrays. This makes the elliptical fin arrays very promising cooling devices as an alternative to conventional circular pin fin arrays used in gas turbine blade cooling applications.

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Section: Introductionmentioning

confidence: 99%

Elliptical Pin Fins as an Alternative to Circular Pin Fins for Gas Turbine Blade Cooling Applications: Part 1 — Endwall Heat Transfer and Total Pressure Loss Characteristics

Uzol

Camcı

2001

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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show abstract

“…Chyu et al used cube and diamond shaped pins to enhance the heat transfer coefficient from a surface [22]. The cubeshaped pins have the highest mass transfer coefficients among the shapes considered and round pins have the lowest mass transfer coefficients.…”

Section: Pin-fin Coolingmentioning

confidence: 99%

Rhomboid Concave and Convex Dimples Applied for Cooling in Gas Turbines

2016

IJSR

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The scope of this work is to contribute towards a more efficient cooling design platforms for gas turbines. Concave and convex schemes of rhomboid dimples, arranged irregularly in a cooling channel, are numerically modeled and studied for their effects on heat transfer and cooling of turbine blades. Research is fulfilled in Gambit and Fluent based on a mathematical model and specified boundary conditions for modeling of aero-and thermodynamic characteristics of flow in cooling ducts. The proposed design shape and arrangement of dimples is found to be very promising and effective for intensive heat transfer and cooling in gas turbines and other industrial applications.

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“…Arora and Abdel -Messeh studied the effects of partial length pins in a rectangular channel [10]. The surface containing pins is not affected by the pin tip clearance.…”

Section: Pin Array and Partial Length Pin Arrangementmentioning

confidence: 99%

Review on Heat Transfer Augmentation Techniques: Application in Gas Turbine Blade Internal Cooling

Gupta¹,

Chaube²,

Verma³

et al. 2012

JESTR

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Gas turbines play a vital role in the today's industrialized society, and as the demands for power increase, the power output and thermal efficiency of gas turbines must also increase. Modern high-speed aero-engines operate at elevated temperatures about 2000 K to achieve better cycle efficiencies. However, the presently available alloys cannot resist temperatures much higher than 1350 K. Internal cooling techniques for gas turbine blades have been studied for several decades. The internal cooling techniques of the gas turbine blade includes: jet impingement, rib turbulated cooling, and pin-fin cooling which have been developed to maintain the metal temperature of turbine vane and blades within acceptable limits in this harsh environment. The designers need detailed hot gas path heat transfer and temperature distributions along with the detailed flow and heat transfer data to understand the flow physics and to improve the current internal cooling designs. Gas turbine blades are cooled internally by passing the coolant through several artificially roughened serpentine passages to remove heat conducted from the outside surface. The cooling passages located in the middle of the airfoils are often lined with rib turbulators. Near the leading edge of the blade, jet impingement (coupled with film cooling) is commonly used. Pin-fins and dimples can be used in the trailing edge portion of the blades. These techniques have also been combined to further increase the heat transfer from the airfoil walls. For internal cooling, focus is now placed on the effect of rotation on rotor blade coolant passage heat transfer. To better understand the complex three-dimensional flow physics in the complicated blade internal coolant passage geometry, the computational flow and heat transfer results are presented and reviewed at improving the internal cooling of gas-turbine blades.

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Characteristics of Partial Length Circular Pin Fins as Heat Transfer Augmentors for Airfoil Internal Cooling Passages

Cited by 12 publications

References 0 publications

Elliptical Pin Fins as an Alternative to Circular Pin Fins for Gas Turbine Blade Cooling Applications: Part 1 — Endwall Heat Transfer and Total Pressure Loss Characteristics

Elliptical Pin Fins as an Alternative to Circular Pin Fins for Gas Turbine Blade Cooling Applications: Part 1 — Endwall Heat Transfer and Total Pressure Loss Characteristics

Rhomboid Concave and Convex Dimples Applied for Cooling in Gas Turbines

Review on Heat Transfer Augmentation Techniques: Application in Gas Turbine Blade Internal Cooling

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