Abstract
Topic of this contribution is the detection of the laminar-turbulent boundary layer transition on the prismatic blade using infrared thermography. Several Reynolds and Mach numbers were investigated, and their influence on the boundary layer transition was evaluated. Results are in good agreement with experiments that were performed earlier with hot-film anemometry.
Highlights
The kinetic energy loss of the flow caused by the presence of the turbomachinery blades in subsonic flow regimes is strongly dependent on the character of the boundary layer (BL) on the blades and on the separation of the BL before the trailing edge
That the BL transition occurs near the trailing edge of the blade (s/c > 0.8) where the Root mean square (RMS) values of the signals increase for all measured regimes of flow
This configuration was found to be unsatisfactory for the detection of BL transition; the images can be used for the demonstration of the artefacts that were observed during the Infrared thermography (IRT) measurement
Summary
The kinetic energy loss of the flow caused by the presence of the turbomachinery blades in subsonic flow regimes is strongly dependent on the character of the boundary layer (BL) on the blades and on the separation of the BL before the trailing edge. The character of BL is dependent on the flow conditions which are commonly described by similarity criteria such as Mach and Reynolds numbers. The kinetic energy loss can be determined experimentally by the pressure measurement behind the trailing edges of the blades. Nowadays the Computational Fluid Dynamics (CFD) is widely used in the turbomachinery design and analysis of the flow field. Turbulent computations are used very often and the results are satisfying for high Reynolds number regimes (higher than 106), where the transition of the BL starts very early behind the leading edge
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