Trailing edge cooling of a gas turbine blade with perforated blockages with inclined holes

Heeyoon Chung; Jun Su Park; Ho Seong Sohn; Dong Ho Rhee; Hyung Hee Cho

doi:10.1016/j.ijheatmasstransfer.2014.01.062

Trailing edge cooling of a gas turbine blade with perforated blockages with inclined holes

Heeyoon Chung, Jun Su Park, Ho Seong Sohn, Dong Ho Rhee, Hyung Hee Cho

Department of Mechanical Engineering

Research output: Contribution to journal › Article › peer-review

15 Citations (Scopus)

Abstract

An improved hole array to enhance the cooling performance of a perforated blockage was proposed in this paper. The internal passage in the trailing region of the blade was modeled as a wide square channel with three parallel blockages. Various configurations of perforated blockages were tested with a fixed Reynolds number based on the channel hydraulic diameter. The baseline design had holes positioned along the centerline of the blockage in the lateral direction, and the array pattern, hole size, and hole direction were manipulated to enhance the cooling performance. Experiments were performed to obtain information on heat transfer and pressure loss. A naphthalene sublimation method was adopted to obtain detailed heat transfer distributions on the surfaces, using the correlation between heat and mass transfer. The pressure was measured at several points to evaluate the pressure loss. The proposed inclined hole array showed noticeably improved cooling performance, as much as 50% higher than the conventional configuration.

Original language	English
Pages (from-to)	9-20
Number of pages	12
Journal	International Journal of Heat and Mass Transfer
Volume	73
DOIs	https://doi.org/10.1016/j.ijheatmasstransfer.2014.01.062
Publication status	Published - 2014 Jun

Bibliographical note

Funding Information:
This work was supported by the aerospace research program (KA00157) of Korea Aerospace Research Institute (KARI) and the human resources development program (No.20134030200200) of the Korean Institute of Energy Technology Evaluation and Planning (KETEP). Those programs are funded by the Korean government Ministry of Trade, Industry and Energy. This paper was originally presented at the ASME Turbo Expo 2013: Turbine technical conference and Exposition (GT2013-95445).

All Science Journal Classification (ASJC) codes

Condensed Matter Physics
Mechanical Engineering
Fluid Flow and Transfer Processes

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10.1016/j.ijheatmasstransfer.2014.01.062

Cite this

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title = "Trailing edge cooling of a gas turbine blade with perforated blockages with inclined holes",

abstract = "An improved hole array to enhance the cooling performance of a perforated blockage was proposed in this paper. The internal passage in the trailing region of the blade was modeled as a wide square channel with three parallel blockages. Various configurations of perforated blockages were tested with a fixed Reynolds number based on the channel hydraulic diameter. The baseline design had holes positioned along the centerline of the blockage in the lateral direction, and the array pattern, hole size, and hole direction were manipulated to enhance the cooling performance. Experiments were performed to obtain information on heat transfer and pressure loss. A naphthalene sublimation method was adopted to obtain detailed heat transfer distributions on the surfaces, using the correlation between heat and mass transfer. The pressure was measured at several points to evaluate the pressure loss. The proposed inclined hole array showed noticeably improved cooling performance, as much as 50% higher than the conventional configuration.",

author = "Heeyoon Chung and Park, {Jun Su} and Sohn, {Ho Seong} and Rhee, {Dong Ho} and Cho, {Hyung Hee}",

note = "Funding Information: This work was supported by the aerospace research program (KA00157) of Korea Aerospace Research Institute (KARI) and the human resources development program (No.20134030200200) of the Korean Institute of Energy Technology Evaluation and Planning (KETEP). Those programs are funded by the Korean government Ministry of Trade, Industry and Energy. This paper was originally presented at the ASME Turbo Expo 2013: Turbine technical conference and Exposition (GT2013-95445).",

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doi = "10.1016/j.ijheatmasstransfer.2014.01.062",

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AU - Sohn, Ho Seong

AU - Rhee, Dong Ho

AU - Cho, Hyung Hee

N1 - Funding Information: This work was supported by the aerospace research program (KA00157) of Korea Aerospace Research Institute (KARI) and the human resources development program (No.20134030200200) of the Korean Institute of Energy Technology Evaluation and Planning (KETEP). Those programs are funded by the Korean government Ministry of Trade, Industry and Energy. This paper was originally presented at the ASME Turbo Expo 2013: Turbine technical conference and Exposition (GT2013-95445).

PY - 2014/6

Y1 - 2014/6

N2 - An improved hole array to enhance the cooling performance of a perforated blockage was proposed in this paper. The internal passage in the trailing region of the blade was modeled as a wide square channel with three parallel blockages. Various configurations of perforated blockages were tested with a fixed Reynolds number based on the channel hydraulic diameter. The baseline design had holes positioned along the centerline of the blockage in the lateral direction, and the array pattern, hole size, and hole direction were manipulated to enhance the cooling performance. Experiments were performed to obtain information on heat transfer and pressure loss. A naphthalene sublimation method was adopted to obtain detailed heat transfer distributions on the surfaces, using the correlation between heat and mass transfer. The pressure was measured at several points to evaluate the pressure loss. The proposed inclined hole array showed noticeably improved cooling performance, as much as 50% higher than the conventional configuration.

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Trailing edge cooling of a gas turbine blade with perforated blockages with inclined holes

Abstract

Bibliographical note

All Science Journal Classification (ASJC) codes

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