Heat transfer from low aspect ratio pin fins

Michael E. Lyall, Alan A. Thrift, Karen Ann Thole, Atul Kohli

Research output: Contribution to journalArticle

38 Citations (Scopus)

Abstract

The performance of many engineering devices from power electronics to gas turbines is limited by thermal management. Heat transfer augmentation in internal flows is commonly achieved through the use of pin fins, which increase both surface area and turbulence. The present research is focused on internal cooling of turbine airfoils using a single row of circular pin fins that is oriented perpendicular to the flow. Low aspect ratio pin fins were studied whereby the channel height to pin diameter was unity. A number of spanwise spacings were investigated for a Reynolds number range between 5000 and 30,000. Both pressure drop and spatially resolved heat transfer measurements were taken. The heat transfer measurements were made on the endwall of the pin fin array using infrared thermography and on the pin surface using discrete thermocouples. The results show that the heat transfer augmentation relative to open channel flow is the highest for smallest spanwise spacings and lowest Reynolds numbers. The results also indicate that the pin fin heat transfer is higher than the endwall heat transfer.

Original languageEnglish (US)
Article number011001
JournalJournal of Turbomachinery
Volume133
Issue number1
DOIs
StatePublished - Jan 31 2011

Fingerprint

Fins (heat exchange)
Aspect ratio
Heat transfer
Reynolds number
Open channel flow
Thermocouples
Power electronics
Airfoils
Pressure drop
Gas turbines
Turbulence
Turbines
Cooling

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering

Cite this

Lyall, Michael E. ; Thrift, Alan A. ; Thole, Karen Ann ; Kohli, Atul. / Heat transfer from low aspect ratio pin fins. In: Journal of Turbomachinery. 2011 ; Vol. 133, No. 1.
@article{0b6d224c3a074d6e8de7a90e461b3577,
title = "Heat transfer from low aspect ratio pin fins",
abstract = "The performance of many engineering devices from power electronics to gas turbines is limited by thermal management. Heat transfer augmentation in internal flows is commonly achieved through the use of pin fins, which increase both surface area and turbulence. The present research is focused on internal cooling of turbine airfoils using a single row of circular pin fins that is oriented perpendicular to the flow. Low aspect ratio pin fins were studied whereby the channel height to pin diameter was unity. A number of spanwise spacings were investigated for a Reynolds number range between 5000 and 30,000. Both pressure drop and spatially resolved heat transfer measurements were taken. The heat transfer measurements were made on the endwall of the pin fin array using infrared thermography and on the pin surface using discrete thermocouples. The results show that the heat transfer augmentation relative to open channel flow is the highest for smallest spanwise spacings and lowest Reynolds numbers. The results also indicate that the pin fin heat transfer is higher than the endwall heat transfer.",
author = "Lyall, {Michael E.} and Thrift, {Alan A.} and Thole, {Karen Ann} and Atul Kohli",
year = "2011",
month = "1",
day = "31",
doi = "10.1115/1.2812951",
language = "English (US)",
volume = "133",
journal = "Journal of Turbomachinery",
issn = "0889-504X",
publisher = "American Society of Mechanical Engineers(ASME)",
number = "1",

}

Heat transfer from low aspect ratio pin fins. / Lyall, Michael E.; Thrift, Alan A.; Thole, Karen Ann; Kohli, Atul.

In: Journal of Turbomachinery, Vol. 133, No. 1, 011001, 31.01.2011.

Research output: Contribution to journalArticle

TY - JOUR

T1 - Heat transfer from low aspect ratio pin fins

AU - Lyall, Michael E.

AU - Thrift, Alan A.

AU - Thole, Karen Ann

AU - Kohli, Atul

PY - 2011/1/31

Y1 - 2011/1/31

N2 - The performance of many engineering devices from power electronics to gas turbines is limited by thermal management. Heat transfer augmentation in internal flows is commonly achieved through the use of pin fins, which increase both surface area and turbulence. The present research is focused on internal cooling of turbine airfoils using a single row of circular pin fins that is oriented perpendicular to the flow. Low aspect ratio pin fins were studied whereby the channel height to pin diameter was unity. A number of spanwise spacings were investigated for a Reynolds number range between 5000 and 30,000. Both pressure drop and spatially resolved heat transfer measurements were taken. The heat transfer measurements were made on the endwall of the pin fin array using infrared thermography and on the pin surface using discrete thermocouples. The results show that the heat transfer augmentation relative to open channel flow is the highest for smallest spanwise spacings and lowest Reynolds numbers. The results also indicate that the pin fin heat transfer is higher than the endwall heat transfer.

AB - The performance of many engineering devices from power electronics to gas turbines is limited by thermal management. Heat transfer augmentation in internal flows is commonly achieved through the use of pin fins, which increase both surface area and turbulence. The present research is focused on internal cooling of turbine airfoils using a single row of circular pin fins that is oriented perpendicular to the flow. Low aspect ratio pin fins were studied whereby the channel height to pin diameter was unity. A number of spanwise spacings were investigated for a Reynolds number range between 5000 and 30,000. Both pressure drop and spatially resolved heat transfer measurements were taken. The heat transfer measurements were made on the endwall of the pin fin array using infrared thermography and on the pin surface using discrete thermocouples. The results show that the heat transfer augmentation relative to open channel flow is the highest for smallest spanwise spacings and lowest Reynolds numbers. The results also indicate that the pin fin heat transfer is higher than the endwall heat transfer.

UR - http://www.scopus.com/inward/record.url?scp=79251520661&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=79251520661&partnerID=8YFLogxK

U2 - 10.1115/1.2812951

DO - 10.1115/1.2812951

M3 - Article

VL - 133

JO - Journal of Turbomachinery

JF - Journal of Turbomachinery

SN - 0889-504X

IS - 1

M1 - 011001

ER -