Effects of hole pitch variation on overall and internal effectiveness in the leading edge region of a simulated turbine blade with heat flux measurements

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Effects of hole pitch variation on overall and internal effectiveness in the leading edge region of a simulated turbine blade with heat flux measurements

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Title: Effects of hole pitch variation on overall and internal effectiveness in the leading edge region of a simulated turbine blade with heat flux measurements
Author: Dyson, Thomas Earl
Abstract: In this study, the cooling of a simulated blade under increasing pitch between holes was examined. The change in non-dimensional surface temperature, phi, was measured experimentally to quantify this performance loss. This critical quantification of the sensitivity of cooling to pitch between holes has not been studied previously. A range of blowing ratios and angles of attack were tested. Data are presented in terms of the laterally averaged phi, and in terms of the minimum phi, arguably more important from a design perspective. Increasing the pitch 13% produced no measureable change using either parameter. An increase of 26% in pitch produced only a 4% loss in lateral averages, while some hot points dropped by 10%. These small changes are due to compensating effects of increased internal and through-hole convective cooling. A limit to these effects was shown when increasing pitch 53%. While performance loss in the average was still relatively small at 15%, the minimum phi decreased by 27%. Heat flux gauges were used to gather data on the internal and external surface. The internal impingement used in this study represents a more accurate representation of internal cooling for an actual engine part than has been previously studied, providing a starting point for exploring the differences between engine configurations and those generally investigated in the literature. External heat flux measurements were used to measure the ratio of heat flux with and without film cooling. These results call into question the use of the net heat flux reduction parameter, which is commonly used to quantify overall film cooling performance.
Subject: Overall effectiveness Pitch variation Impingement cooling Relative curvature Concave Heat flux Angle of attack Turbine blade Leading edge Film cooling
URI: http://hdl.handle.net/2152/ETD-UT-2010-05-1215
Date: 2010-05

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