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TURBINE-09. Proceedings of International Symposium on Heat Transfer in Gas Turbine Systems
August, 9-14, 2009, Antalya, Turkey

DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst


ISBN Print: 978-1-56700-263-8

HEAT TRANSFER CHARACTERISTICS ON TIP AND INNER RIM SURFACES OF A BLADEWITH SQUEALER RIM

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

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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