Abstract: An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.

Abstract: An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.

Abstract: Methods of providing an undercut on a support member for a coversheet and coversheet support systems having undercuts are provided. A coversheet support system may include a spar. The spar may include a support member on an outer surface of the spar. The support member may extend outward from the outer surface of the spar. The support member may include an outer surface and an undercut. The undercut may be located in a portion of the support member between the outer surface of the spar and the outer surface of the support member. In addition, the coversheet support system may include a coversheet. The coversheet may be metallurgically bonded to the outer surface of the support member.

Abstract: An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.

Abstract: An engine including a turbine section with a number of vane assemblies attached to a support housing. The assemblies are secured to the support housing with fasteners and retaining clips for the fasteners.

Abstract: An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.

Abstract: Methods of providing an undercut on a support member for a coversheet and coversheet support systems having undercuts are provided. A coversheet support system may include a spar. The spar may include a support member on an outer surface of the spar. The support member may extend outward from the outer surface of the spar. The support member may include an outer surface and an undercut. The undercut may be located in a portion of the support member between the outer surface of the spar and the outer surface of the support member. In addition, the coversheet support system may include a coversheet. The coversheet may be metallurgically bonded to the outer surface of the support member.

Abstract: An engine including a turbine section with a number of vane assemblies attached to a support housing. The assemblies are secured to the support housing with fasteners and retaining clips for the fasteners.

Abstract: A system for monitoring the displacement of turbine blades that includes a turbine blade with a cutting tooth and one or more sensor wires, each sensor wire including a severable portion, that become severed by the cutting tooth as turbine blade displacement occurs. The sensor wires may be embedded in a honeycomb, which may be an area of abradable material attached to turbine shrouds. The sensor wires may include a plurality of radial sensor wires embedded in the honeycomb at varying predetermined radial distances from a turbine rotor. The sensor wires also may include a plurality of axial sensor wires embedded in the honeycomb at varying predetermined axial locations along the length of the honeycomb.

Abstract: A system for monitoring the displacement of turbine blades that includes a turbine blade with a cutting tooth and one or more sensor wires, each sensor wire including a severable portion, that become severed by the cutting tooth as turbine blade displacement occurs. The sensor wires may be embedded in a honeycomb, which may be an area of abradable material attached to turbine shrouds. The sensor wires may include a plurality of radial sensor wires embedded in the honeycomb at varying predetermined radial distances from a turbine rotor. The sensor wires also may include a plurality of axial sensor wires embedded in the honeycomb at varying predetermined axial locations along the length of the honeycomb.

Abstract: A closed loop inner shroud assembly for a gas turbine. The shroud assembly may include a shroud body, a cover plate, an inlet though the cover plate to the shroud body, a serpentine passageway through the shroud body, and an outlet from the shroud body to the cover plate.

Abstract: A damper for the blades of a turbine rotor for attenuating the vibrations excited in a radial direction by configuring the damper to have at least two legs bearing against the blade and the disc supporting the blade for grounding the radial vibrations transmitted radially through the damper and offsetting the center of gravity of the damper from the point of contact with the blade.