Experimental investigation of axial-flow compressor stator blades designed to obtain high turning angles by means of boundary-layer suction

Costello, G. R., Cummings, R. L., Serovy, G. K.
naca-rm-e52d18
1952


In order to determine the practicability of using blade boundary-layer control to obtain high turning angles in a stator-blade row, a set of slotted stator blades, designed by a potential-flow method for a 45 degree turning angle with a low solidity using 1 percent boundary-layer bleed, was tested in a single-stage compressor. Several slot configurations were tested in order to reduce the large secondary flows produced by the original blades. In addition, a means of boundary-layer control was installed on the hub ahead of the stator blades to improve the entrance conditions. The over-all performance of the stage was obtained for a range of weight flows at each of three speeds with and without hub suction. These results together with wake surveys indicate that, although design turning was obtained, the slots created large local pressure gradients which caused separation from the walls and greatly increased the secondary flows.

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