Leading edge plating on low pressure compressor vane for weight and strength optimization
AssigneePratt & Whitney Canada Corp.
InventorsPaul Aitchison, Muthukumar Mathivanan, Anthony Brown, Tammy Yam
Life of this patent
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Abstract
A vane including an airfoil body extending from a root to a tip defining a longitudinal axis therebetween, wherein the airfoil body includes a leading edge between the root and the tip. The vane includes a pressure side and a suction side and a recess area on the leading edge. The recess area includes a pressure side recess area and a suction side recess area, and a metal is deposited on the recess area. A method of manufacturing the vane and a gas turbine engine including the vane are also disclosed.
Claims15
A vane comprising an airfoil body extending from a root to a tip defining a longitudinal axis therebetween,
- wherein the airfoil body includes a leading edge between the root and the tip,
- wherein the airfoil body includes a pressure side and a suction side and a recess area on the leading edge,
- wherein the recess area includes a pressure side recess area having a pressure side base surface forming a straight edge and a suction side recess area having a suction side base surface having a curved edge, wherein the pressure side base surface meets the suction side base surface,
- a deposited metal on the recess area, wherein the deposited metal in the recess area has a thickness of 0.001 inch (0.03 mm) to 0.015 inch (0.4 mm);
- and
- wherein the airfoil body is made of a metal having a density equal to or less than a density of the deposited metal.
Dependencies are inferred from the claim text.