An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil body defining a recessed region and including at least one rib dimensioned to loop about a respective pocket within a perimeter of the recessed region. At least one cover skin is welded to the airfoil body along the at least one rib to enclose the recessed region. The at least one cover skin is welded to the at least one rib along a respective weld path. The weld path defines a weld width, the at least one rib defines a rib width, and a ratio of the weld width to the rib width is equal to or greater than 3:1 for each position along the weld path. A method of forming a gas turbine engine component is also disclosed.

Shaft assemblies, turbomachines, and methods of servicing a turbomachine are provided. A shaft assembly includes a first shaft having a first rabbet annularly defined therein. The first rabbet includes a first axially extending face and a first radially extending face. A second shaft coupled to the first shaft. The second shaft includes a second rabbet annularly defined therein and positioned opposite the first rabbet. The second rabbet includes a second axially extending face and a second radially extending face. A patch ring is mounted between the first rabbet and the second rabbet. The patch ring includes a main body positioned between and in contact with the first axially extending face and the second axially extending face. A first arm extends radially outward from the main body, and a second arm extends radially inward from the main body.

A service apparatus for use in maintaining a turbine assembly (100) includes a carriage (132, 304) configured to move through a cavity of the turbine assembly (100), a motorized system (218, 500, 600, 700, 800) coupled to the carriage (132, 304), and a maintenance device (128, 400) coupled to the motorized system (218, 500, 600, 700, 800). The motorized system (218, 500, 600, 700, 800) is configured to move the maintenance device (128, 400) relative to the carriage (132, 304). The motorized system (218, 500, 600, 700, 800) includes a first motor (710, 720, 805) configured to move the maintenance device (128, 400) in a first direction (324) and a second motor (710, 720, 805) configured to move the maintenance device (128, 400) in a second direction (324).

The invention relates to a method of repairing a blade (1) made of composite material, extending in a so-called axial direction (X), the said blade (1) comprising a root (2) and a blade (3), the axial end of which opposite the root (2) comprises an area to be repaired, the said blade (3) comprising an intrados (4) surface and an extrados (5) surface.

One of spacing between the base-side first tooth and the base-side second tooth or spacing between the base-side second tooth and the base-side third tooth is greater than spacing between the tip-side first tooth and the tip-side second tooth. When, in a cross-section perpendicular to an extension direction of a plurality of teeth, a straight line that connects tooth bottom portions formed between each adjacent teeth in the blade height direction is a first line, an intersection between the first line and a second line that includes a linear portion of a tip-side tooth surface of each of the plurality of teeth is a first intersection, and an intersection between the first line and a third line that includes a linear portion of a base-side tooth surface of each of the plurality of teeth is a second intersection, a distance between the first intersection and the second intersection in the base-side first tooth is greater than a distance between the first intersection and the second intersection in each tooth other than the base-side first tooth.

There is provided a cobalt-based alloy product comprising: in mass %, 0.08-0.25% C; 0.1% or less B; 10-30% Cr; 5% or less Fe and 30% or less Ni, the total amount of Fe and Ni being 30% or less; W and/or Mo, the total amount of W and Mo being 5-12%; at least one of Ti, Zr, Hf, V, Nb and Ta, the total amount of Ti, Zr, Hf, V, Nb and Ta being 0.5-2%; 0.5% or less Si; 0.5% or less Mn; 0.003-0.04% N; and the balance being Co and impurities. The cobalt-based alloy product is a polycrystalline body of matrix phase crystal grains, wherein MC type carbide phase grains are dispersively precipitated in the matrix phase crystal grains at an average intergrain distance of 0.13 to 2 μm and M.sub.23C.sub.6 type carbide phase grains are precipitated on grain boundaries of the matrix phase crystal grains.

The invention relates to a method for repairing flow channel segments of a turbomachine. The method comprises providing a monocrystalline or directionally solidified flow channel segment whose length and width extend along the flow channel, each being greater than the thickness thereof, and whose width and length delimit a surface which constitutes a bounding surface of a flow channel and has damage, cleaning the bounding surface to remove impurities, remelting at least a part of the bounding surface in a surface region so that melted material solidifies epitaxially in an inner region facing toward the unmelted material and forms a structural region in which the monocrystalline or directionally solidified structure is preserved, and that melted material solidifies in a polycrystalline fashion in an outer region which faces toward the flow channel and forms an edge region, and removing the edge region.

An atomizing spray nozzle device includes an atomizing zone housing that receives different phases of materials used to form a coating. The atomizing zone housing mixes the different phases of the materials into a two-phase mixture of ceramic-liquid droplets in a carrier gas. The device also includes a plenum housing fluidly coupled with the atomizing housing and extending from the atomizing housing to a delivery end. The plenum housing includes an interior plenum that receives the two-phase mixture of ceramic-liquid droplets in the carrier gas from the atomizing zone housing. The device also includes one or more delivery nozzles fluidly coupled with the plenum chamber. The delivery nozzles provide outlets from which the two-phase mixture of ceramic-liquid droplets in the carrier gas is delivered onto one or more surfaces of a target object as the coating on the target object.

Disclosed is an apparatus for inspecting an airfoil, the apparatus having: a pair of opposing walls connected by a base; a pair of chucks, wherein one of the pair of chucks is secured to one of the pair of opposing walls and the other one of the chucks is secured to the other one of the pair of opposing walls; and a profile gauge supported by the pair of opposing walls and configured to move between the pair of chucks.

A method can comprise: determining, via a processor, whether serviceable limits are met for an inspected bladed rotor; generating, via the processor, a three-dimensional model including a repair blend profile for a defect in response to determining the inspected bladed rotor does not meet the serviceable limits; performing, via the processor, a first set of simulations on the three-dimensional model; determining, via the processor, whether a first set of results of the first set of simulations meet an experience based criteria; performing, via the processor, a second set of simulations on the three-dimensional model in response to a first result in the first set of results not meeting a first objective parameter in the experience based criteria; and determining, via the processor, whether a second set of results and the first set of results meet a deterministic criteria.