A turbine blade includes a blade tip defining pressure side cooling apertures. The turbine blade defines a serpentine cooling passage having a first, second, and third legs, and first and second junction portions. The first leg extends radially and is connected to the second leg by the first junction portion proximate the blade tip. The second leg extends radially between the first and second junction portions. The second junction portion connects the second leg to the third leg which extends radially toward the blade tip and is connected to a trailing edge cooling aperture to exhaust the gas to an exterior of the turbine blade. The turbine blade defines a plenum connected to the first junction portion. At least one tip cooling aperture connects to the plenum and is radially outward of the third leg and axially aftward of at least a portion of the third leg.

Methods of servicing a fuel nozzle are provided. a method of servicing a fuel nozzle includes a step of machining away material from a nozzle tip of the fuel nozzle to form an annular groove within the nozzle tip. The method further includes a step of inserting a replacement coupon into the annular groove. The replacement coupon having a radially outermost that corresponds to the annular groove and a post-removal contact surface. The method further includes a step of fixedly coupling the radially outermost of the replacement coupon to the annular groove.

An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.

A turbine blade repair method is provided. The turbine blade repair method includes quantizing a position and a shape of a damaged portion of a turbine blade into numerical values, calculating a momentum loss of the turbine blade due to removal of the damaged portion, modeling a shape of a repair portion to replace the damaged portion so that the repair portion has the same momentum as the damaged portion, removing the damaged portion, and forming the modeled repair portion by performing an additive manufacturing at a position of the removed damaged portion.

A method may include removing a portion of a base component adjacent to a damaged portion of the base component to define a repair portion of the base component. The base component may include a cobalt- or nickel-based superalloy, and the repair portion of the base component may include a through-hole extending from a first surface of the base component to a second surface of the base component. The method also may include forming a braze sintered preform to substantially reproduce a shape of the through-hole. The braze sintered preform may include a Ni- or Co-based alloy. The method additionally may include placing the braze sintered preform in the through-hole and heating at least the braze sintered preform to cause the braze sintered preform to join to the repair portion of the base component and change a microstructure of the braze sintered preform to a brazed and diffused microstructure.

Methods of servicing a fuel nozzle are provided. a method of servicing a fuel nozzle includes a step of machining away material from a nozzle tip of the fuel nozzle to form an annular groove within the nozzle tip. The method further includes a step of inserting a replacement coupon into the annular groove. The replacement coupon having a radially outermost that corresponds to the annular groove and a post-removal contact surface. The method further includes a step of fixedly coupling the radially outermost of the replacement coupon to the annular groove.

The present disclosure provides a system and method of repairing a flange of an engine case having a damaged section of attachment tabs and/or flange region. One or more damaged attachments tabs extending away from a flange are removed along with a first portion of the flange, thus leaving a second portion of the flange. A replacement component is produced comprising a replacement flange portion and one or more replacement tabs. The replacement flange portion is placed in contact with the second portion of the flange and the replacement flange portion is secured to the second portion of the flange.

A tool for balancing a turbine engine module in a balancer, the module including a stator, a rotor and a shaft, the balancer including at least one power drive unit and a table equipped with two support of the shaft of the module. The tool includes at least: one stator support, fixed on the table of the balancer behind the supports, a tubular false bearing, configured to support a bearing for guiding the rotor in the stator and protruding outside of the stator, a guiding sleeve of the shaft, confining a support of the false bearing, and received on the supports of the balancer, a rear support plate of the stator, fixed to the support of the stator, and immobilising the rotor with respect to the stator, a front support plate of the stator, fixed to the stator support, and immobilising and centring the false bearing.

A method of repairing an airfoil is provided. The method includes providing an airfoil with a damaged section and removing the damaged section by machining or cutting an upper section of the airfoil. A replacement section is configured to mate with an upper surface of the airfoil. A presintered preform is provided to join the airfoil and the replacement sections through a resistance brazing process. The presintered preform is configured to mate with the upper surface of the airfoil and a lower surface of the replacement section and inserted between this upper surface and lower surface, creating a stacked airfoil comprising three mated sections in abutting contact. The stacked airfoil is resistance brazed such that only the braze material of the presintered preform melts and the upper surface of the airfoil and the lower surface of the replacement section remain below the grain boundary temperature of the material of the airfoil.

A system for regenerating fastener holes in a replacement tip section of a rotor blade includes a first fixture, a second fixture, and a third fixture positionable adjacent a tip section of the rotor blade. The first fixture is used to verify a position of an opening formed in the spar. The second fixture includes a removable bushing having a drillable opening. The drillable opening is aligned with the at least one opening formed in the spar and defines at least one hole to be formed in the replacement tip section. The third fixture includes a countersink opening. The countersink opening is aligned with the at least one hole to be formed in the replacement tip section and the at least one opening formed in the spar to define a countersink feature to be formed in the at least one hole.