The effects of low-profile vortex generators on flow in a transonic fan-blade cascade

: Two dimensional fully-mixed-out flow conditions were measured downstream of a two-passage transonic fan-blade cascade which had low-profile vortex generators (VGs) attached to the suction surfaces of the blades. The simulation was conducted using a blowdown wind tunnel at a Mach number of 1.4. The objective was to assess the effects of vortex generating devices on the suction surface shock-boundary layer interaction and the resulting losses. Measurements are reported from tests made with older aluminum blading, with and without VGs, and with a nominally similar new set of steel blading, with and without VGs. Differences between the old and new blading were found to be most significant. While shock structures appeared to be similar with VGs attached, dye injection showed that the shock-induced boundary layer separation was greatly suppressed and the downstream flow was much steadier. With VGs, the flow turning was improved by 0.94 degrees, but the flow loss coefficient increased by about 8%. An extension of the study is needed to fully assess the potential of using low-profile VGs in military fan engines. (AN)

: Two dimensional flow measurements of Mach number and flow angle were conducted downstream of a transonic fan-blade cascade at a mach number of 1.4 to provide baseline data for assessing the effect of vortex generating devices on the suction surface shock-boundary layer interaction. The experimental program consisted of the design and calibration of a traversing three-port pneumatic probe to measure Mach number and flow angle and initial cascade measurements to provide baseline data for the fully-mixed-out total pressure loss coefficient and flow turning angle. Similar tests are planned with the vortex generating devices installed. Comparisons with and without the vortex generating devices are needed to quantify the overall effect on the shock-boundary interaction in a transonic fan-blade passage, and to assess the potential for using vortex generating devices in military engine fans.

https://calhoun.nps.edu/bitstream/10945/30868/1/94Mar_Austin.pdf

Mach number, flow angle, and loss measurements downstream of a transonic fan-blade cascade

Simulation of shock-boundary layer interaction in a fan blade passage

AIAA 93-1980 Simulation of Shock-Boundary Layer Interaction in a Fan Blade Passage

Model Fan Passage Flow Simulation

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The effects of low-profile vortex generators on flow in a transonic fan-blade cascade

The effects of low-profile vortex generators on flow in a transonic fan-blade cascade

Mach number, flow angle, and loss measurements downstream of a transonic fan-blade cascade

Simulation of shock-boundary layer interaction in a fan blade passage

AIAA 93-1980 Simulation of Shock-Boundary Layer Interaction in a Fan Blade Passage

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