Abrasive blade tip with improved wear at high interaction rate

A turbine engine component comprising:

• an airfoil portion having a tip;
• said tip comprising reduced corners proximate a leading edge and a trailing edge of said airfoil;
• a composite abrasive coating bonded to said tip;
• said composite abrasive coating comprising an adhesion layer bonded to said tip;
• a layer of grit particles bonded to said adhesion layer in a matrix material surrounding an unexposed portion of said grit particles;
• said matrix material coupled to said adhesion layer;
• wherein said composite abrasive coating is thicker proximate said corners.

A process for coating a turbine engine blade with an abrasive, said process comprising:

• reducing the thickness of a tip of said blade proximate at least one corner of said tip;
• applying an adhesion layer onto said tip of said blade;
• adhering a plurality of grit particles to said adhesion layer, wherein narrow spaces are formed between said grit particles;
• filling said narrow spaces between said grit particles with a matrix material;
• surrounding each of said first grit particles with said matrix material exposing a portion of said first grit particles above said matrix material and said second grit particles;
• wherein said grit particles and said matrix material have a thickness greater than the reduced thickness of said tip proximate said at least one corner.