Aerodynamic losses and surface heat transfer in a strut /endwall intersection flow
This thesis presents the results of an investigation into aerodynamic losses and surface heat transfer of a strut/endwall intersection flow field. This type of geometry is prevalent in many aerospace applications, such as wing/body junctions on aircraft, rotor/stator blades in turbomachinery and support struts in turbofan bypass ducts. The changes in aerodynamic drag and surface heat transfer due to the presence of this geometry are of interest to aerospace companies seeking small improvements in performance which contribute to large reductions in operating costs over the lifetime of a product. Aerodynamic losses (i.e. drag) were evaluated from flow-field data obtained with a seven-hole pressure probe using loss equations derived from a control-volume analysis of the integral conservation equations. In addition, a methodology was developed for this type of flow field that allows separation of losses into inviscid and viscous contributions. Strut profile drag, total drag and interference drag were computed for the strut/endwall intersection geometry and compare favorably with previous results. The endwall heat transfer of the strut/endwall intersection was measured using a new heat transfer measurement system that was developed for this research. This system is an expansion of the laser-scanning Temperature Sensitive Paint technique. Results from transition detection and impinging jet experiments conducted during system development are also reported. A map of endwall convective heat transfer in the leading edge region of the strut is presented. The endwall heat transfer results are similar to those found in other investigations of endwall heat transfer for the strut/endwall geometry. ^
Major Professor: John P. Sullivan, Purdue University.
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