Unsteady Heat Transfer and PRessure Measurements on the Airfoils of a Rotating Transonic Turbine with Multiple Cooling Configurations

[+] Author and Article Information
Jeremy B. Nickol

The Ohio State University Gas Turbine Laboratory 2300 West Case Rd, Columbus OH 43235 USA

Randall M. Mathison

The Ohio State University Gas Turbine Laboratory 2300 West Case Rd, Columbus OH 43235 USA

Michael G. Dunn

The Ohio State University Gas Turbine Laboratory 2300 West Case Rd, Columbus OH 43235 USA

Jong S. Liu

Honeywell International Phoenix, AZ 85034 USA

Malak Malak

Honeywell International Phoenix, AZ 85034 USA

1Corresponding author.

ASME doi:10.1115/1.4036059 History: Received November 15, 2016; Revised February 01, 2017


Measurements are presented for a high-pressure transonic turbine stage operating at design-corrected conditions with forward and aft purge flow and blade film cooling in a short-duration blowdown facility. Four different film-cooling configurations are investigated: simple cylindrical-shaped holes, diffusing fan-shaped holes, an advanced-shaped hole, and uncooled blades. A rainbow turbine approach so that all four blade types can be examined simultaneously. Double-sided Kapton heat-flux gauges are installed at midspan on all three film-cooled blade types, and single-sided Pyrex heat-flux gauges are installed on the uncooled blades. Kulite pressure transducers are installed at midspan on cooled blades with round and fan-shaped cooling holes. Experimental results are presented as time-averaged values and as time-accurate ensemble-averages. In addition, the results of a steady RANS CFD computation are compared to the time-averaged data. The computational and experimental results show that cooled blades reduce heat transfer into the blade significantly from the uncooled case, but the overall differences in heat transfer among the three cooling configurations are small. This challenges previous conclusions for simplified geometries that show shaped cooling holes outperform cylindrical holes by a great margin. It suggests that the more complicated flow physics associated with an airfoil operating in an engine-representative environment reduce the effectiveness of the shaped cooling holes. Time-accurate comparisons provide insight into the complicated interactions that drive these flows and make it difficult to characterize cooling benefits.

Copyright (c) 2017 by ASME
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