Transitional Flow on Axial Turbomachine Blading
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Correlations of data from constant-pressure flows are shown to seriously overestimate the transition length on axial turbomachine blades in regions of positive pressure gradient. The differences largely can be ascribed to the influence of the pressure gradient on the mechanism of laminar-turbulent transition. A hypothesis of continuous breakdown of laminar instability waves, together with an estimate of the dominant disturbance frequency, is introduced to model the minimum possible length of transitional flow in terms of local boundary-layer parameters. This model should be preferable to a point transition assumption for predicting turbomachine blade flows. In practice, the transition length most probably will lie between the predictions of the minimum length model and those of constant-pressure flow correlations.
The article of record as published may be found at http://dx.doi.org/10.2514/3.10150Presented as Paper 87-0010 at the AIAA 25th Aerospace Sciences Meeting, Reno, NV, Jan. 12-15, 1987
RightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
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