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ISSN Online: 2377-424X

ISBN Print: 0-89116-559-2

International Heat Transfer Conference 8
August, 17-22, 1986, San Francisco, USA

ENHANCED COOLING OF GAS TURBINE BLADE TRAILING EDGE WITH CURVED AIR FLOW IN PIN-FINNED WEDGED PASSAGE

Get access (open in a dialog) DOI: 10.1615/IHTC8.2130
pages 1231-1236

要約

The trailing edge of gas turbine blades can be cooled using pin-finned radial passages with chordwise exhaut gaps along the blade span. In this article test results are presented of flow rate fraction from eight exits and of distributions of air temperatures at the exit and of wall temperatures in such cooling passages with different top opening position and areas. For data reduction the test piece was divided into 7 slices. The average air temperature Tfi chordwise and spanwise average velocities ui, vi were pridicted. Therefore, the distributions of heat transfer coefficients and Reynolds numbers in slices were obtained. The values of Nui/Nuo ranged from 1.74 to 3.77 and were substantially larger than for straight flow in pin-finned passages.