| 摘要 |
A gas turbine engine airfoil shaped component is disclosed including in one form a compressor blade or vane having a tip portion capable of producing a relatively low pressure near the leading edge of the tip to induce a local jet of stream-wise momentum flow. In one form the tip portion includes a camber angle distribution that produces relatively large change in camber angle near the leading edge but relatively flat distribution for remainder of blade. In one form the tip portion includes relatively large change in camber angle near trailing edge. |
