General Electric Company

James Earl Kopriva

Robert Francis Manning

Victor Hugo Silva Correia

George Joe-Kueng Chan

Mark Douglas Gledhill

Robert Edward Athans

Donald Brett DeSander

The disclosure relates to a gas turbine engine and a method of controlling an upstream extent of a bow wave from an airfoil having a pressure side and a suction side in the turbine engine. In one aspect, the method includes forming a vortex at a leading edge of the airfoil.

Turbine engine airfoil and method

An assembly for a turbine engine comprises a circumferential band defining an air flow path, a component having a leading edge and extending from the band into the flow path, and a trough located in a surface of the band along the leading edge.

Turbine engine assembly with a component having a leading edge trough

A method of fabricating a rotor blade is provided. The method includes forming at least one passageway within the rotor blade, wherein the passageway extends substantially radially from a root of the rotor blade to a tip of the rotor blade, and coupling a shroud to the tip of the rotor blade. The shroud includes at least one substantially radially-outward extending wall that at least partially defines an outer plenum that is radially outward from at least the shroud, wherein the outer plenum is in flow communication with the passageway.

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Wichester, MA, United States of America

James Earl Kopriva