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

Research output: Chapter in Book/Report/Conference proceedingConference contribution

6 Citations (Scopus)

Abstract

We propose an improved hole array to enhance the cooling performance of a perforated blockage. 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. 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 languageEnglish
Title of host publicationASME Turbo Expo 2013
Subtitle of host publicationTurbine Technical Conference and Exposition, GT 2013
DOIs
Publication statusPublished - 2013
EventASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013 - San Antonio, Tx, United States
Duration: 2013 Jun 32013 Jun 7

Publication series

NameProceedings of the ASME Turbo Expo
Volume3

Other

OtherASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013
CountryUnited States
CitySan Antonio, Tx
Period13/6/313/6/7

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

  • Engineering(all)

Fingerprint Dive into the research topics of 'Trailing edge cooling of a gas turbine blade with perforated blockages with inclined holes'. Together they form a unique fingerprint.

Cite this