Patent ID: 9309769
Filing Date: 2016-04-12
CPC Classification: F01D,F04D,F05D,Y02T

Claim Text:
1. An apparatus comprising: a compressor blade of a gas turbine engine capable of being rotated to produce a pressure rise in a working fluid during operation of the gas turbine engine, the compressor blade including a main blade portion having a first camber shape that is blended with a tip portion having a second camber shape, the second camber shape producing a relatively low pressure near the leading edge of the tip to induce a local jet of stream-wise momentum flow, wherein the second camber shape is blended into the first camber shape starting at about 2/3 of a height of the compressor blade, wherein the second camber shape includes a normalized camber angle defined as  where β wherein the normalized camber angle reaches at least 0.4 in the first 10% of normalized chord.