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DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.40
page 8

Jun Su Park
School of Mechanical Engineering, Yonsei University, Seoul 120-749 Korea

Dong Hyun Lee
School of Mechanical Engineering Yonsei University, Seoul 120-749 Korea

Woo Jin Lee
School of Mechanical Engineering, Yonsei University, Seoul 120-749 Korea

Hyung-Hee Cho
School of Mechanical Engineering, Yonsei University, Seoul 120 749, South Korea

Dong-Ho Rhee
Korea Aerospace Research Institute Daejeon, 305-333, Korea

Shin-Hyung Kang
School of Mechanical and Aerospace Engineering, Seoul National University Seoul, Korea


Detailed heat/mass transfer coefficients were measured on the tip and inner rim surfaces of a rotor blade with a squealer rim. The blade was a two-dimensional version of a modern first-stage gas turbine rotor blade with a squealer rim. The experimental apparatus was equipped with a linear cascade of three blades, the axial chord length of which was 237 mm and the pitch was 213 mm. Measurements were made at three different tip clearances, of about 1%, 2%, and 3% of the axial chord length, and the rim height was fixed at 6% of the axial chord length. The main flow Reynolds number based on the axial chord was 1.5×105. High heat transfer rates were observed near the leading edge in all cases, due to the reattachment of leakage flow. The peak values moved toward the suction-side edge and the magnitude and area of high heat/mass transfer increased near the leading edge as the tip clearance increased.

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