Heat transfer and secondary flow with a multicavity gas turbine blade tip

Jung Shin Park, Sang Hoon Lee, Won Suk Lee, Jin Taek Chung, Jae Su Kwak

Research output: Contribution to journalArticlepeer-review

16 Citations (Scopus)


Multicavity gas turbine blade tips were formed by adding ribs in the blade tip cavities of squealer tips, and the effects of the tip clearance size, the number and the installation angle of the ribs on the tip heat transfer, and the blade passage total pressure loss were investigated experimentally. Tests were conducted in a low-speed linear cascade. The transient liquid crystal technique and a seven-hole probe were used to measure the heat transfer and flowfield, respectively. Results showed that a multicavity tip was able to reduce the total pressure loss coefficient, and the total pressure loss coefficients decreased as the number of ribs increased. Additional ribs on the tip cavity reduced the heat transfer coefficients on the cavity surface near the leading edge, but induced an additional high heat transfer coefficient region downstream from the rib due to the flow reattachment.

Original languageEnglish
Pages (from-to)120-129
Number of pages10
JournalJournal of Thermophysics and Heat Transfer
Issue number1
Publication statusPublished - 2016

ASJC Scopus subject areas

  • Condensed Matter Physics
  • Aerospace Engineering
  • Mechanical Engineering
  • Fluid Flow and Transfer Processes
  • Space and Planetary Science


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