A compressor adapted for use in for a gas turbine engine includes a diffuser and a housing. The diffuser is arranged circumferentially around an axis and includes a fore plate, an aft plate spaced apart axially from the fore plate to define a flow path therebetween, and a plurality of vanes that extend between the fore plate and the aft plate. The housing is arranged circumferentially about the axis and located adjacent the diffuser.

A compressor adapted for use in for a gas turbine engine includes a diffuser and a housing. The diffuser is arranged circumferentially around an axis and includes a fore plate, an aft plate spaced apart axially from the fore plate to define a flow path therebetween, and a plurality of vanes that extend between the fore plate and the aft plate. The housing is arranged circumferentially about the axis and located adjacent the diffuser.

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.

A method of repairing a tip for an airfoil is disclosed herein. In various embodiments, the method comprises: removing a portion of the airfoil that reduces a radial height of the airfoil and at least partially removes a defect of the airfoil; removing a remainder of the defect; joining, via gas tungsten arc welding, a filler material to the airfoil to repair the defect; and joining a first mating surface of the airfoil to a second mating surface of a blade tip body via a solid-state joining process.

A method for repairing a damaged leading or trailing edge region of a metallic turbine blade, which has a suction-side blade wall, a pressure-side blade wall and a leading edge and a trailing edge, includes: removing the damaged leading or trailing edge region, with a cutout being formed; providing a replacement part which can be inserted in form-fitting fashion into the cutout and which restores the intended geometry of the turbine blade; inserting the replacement part in form-fitting fashion into the cutout in a predetermined insertion direction, and cohesively connecting the replacement part to the turbine blade, wherein mechanical connection of the replacement part and turbine blade using separate fastening elements is performed in addition to the cohesive connection.

A turbine blade tip shroud has a first cutter tooth extending from a tip rail from one of the upstream side and the downstream side of the tip rail and adjacent the leading edge of the body. The tip shroud also includes a second cutter tooth extending from the tip rail from the other side of the tip rail at a position axially distant from the first cutter tooth. The cutter teeth are thus axially offset. The tip shroud can be initially manufactured with this shape or may be modified from a used tip shroud having, for example, opposing cutter teeth near a leading edge of a body of the tip shroud. Various tip shroud surface profiles, which are expressed in terms of Cartesian coordinates, are also provided.

An airfoil component for attaching to a cropped airfoil is provided. The cropped airfoil comprises a cropped airfoil attachment section and a cropped first side opposite a cropped second side, which each extend axially between a cropped first edge and a cropped second edge to define a cropped chord length. The airfoil component comprises a body having a component first side opposite a component second side. The body defines an attachment section for attaching the airfoil component to the cropped airfoil at the cropped airfoil attachment section. The attachment section extends axially between a component first edge and a component second edge to define a component chord length, and the attachment section is oversized with respect to the cropped airfoil attachment section such that the component chord length is longer than the cropped chord length. Systems and methods also are provided.

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

A component of a rotary machine extends to an axial direction and a radial direction vertical thereto, and has an inner channel, extending from a first end of a core of a center of the component and to a second end at a radial limiting surface of the component and which is at least partially closed. A blank includes the core of the component and is limited by an outer surface in the radial direction. The blank is subtractively processed in a first subtractive process step, such that an outer contour is elaborated in the area of the outer surface, which extends in the radial direction, and a part of the channel is manufactured, which radially extends in the blank to the first end. The channel is formed by a build-up process on the blank.