An investigation of the three-dimensional flow immediately down-stream of an annular cascade of nozzle blades was made to obtain a good physical picture of the flow at blade-hub discharge Mach numbers of 1.18, 1.31, and 1.41. The blades were designed for axial entry and a constant discharge angle of 59° 45' from axial.nThe energy loss core at the blade tip was found to decrease in size with increasing Mach number and did not seem to affect appreciably the general pattern of angle distribution. The loss core at the blade hub, however, increased in size with increasing Mach number, and at the higher Mach numbers the center of the loss core was found to be in the region of large discharge angle gradients in the blade wake.
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