A rotor blade is provided for a gas turbine engine. This rotor blade includes a rotor blade pair including a mount, a first airfoil and a second airfoil. The mount includes a forked body with a first leg and a second leg. The first airfoil is connected to the first leg. The second airfoil is connected to the second leg and arranged circumferentially next to the first airfoil.

A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of disk mounts. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is axially between and mounted to the first rotor disk and the second rotor disk. The disk mounts connect the first rotor disk and the second rotor disk together. The disk mounts include a first disk mount. The first disk mount is integral with the first rotor disk. The first disk mount projects axially through the second rotor disk.

An apparatus is provided for a rotor assembly with a rotational axis. This apparatus includes a rotor blade including an airfoil, a neck and an attachment. The neck radially connects the airfoil and the attachment. The attachment extends axially between an attachment first axial side and an attachment second axial side. A first end portion of the attachment projects axially out from the neck to the attachment first axial side. A second end portion of the attachment projects axially out from the neck to the attachment second axial side.

A rotor blade for a turbomachine is provided. The rotor blade includes a platform, an airfoil extending from the platform, and a cooling circuit extending within the platform and the airfoil. The cooling circuit includes a plurality of cooling passages defined by a plurality of ribs. The plurality of ribs includes an offset rib.

An exhaust baffle component for an aircraft starter includes a plurality of frames arranged with one another as a single component. At least one of the plurality of frames may include an attachment flange extending therefrom and defining a receiving aperture. Each frame of the plurality of frames may include one or more louvers stacked relative to one another and spaced from one another to define an air opening therebetween. The attachment flange may extend from the frame at a substantially central region of an upper portion of the frame to substantially align the receiving aperture with a starter aperture of a starter component to facilitate securement of the attachment flange to the starter component.

A method of repairing an airfoil according to an example of the present disclosure includes, among other things, providing an airfoil body, the airfoil body having external walls extending between a leading edge and a trailing edge, providing a baffle, the baffle including a baffle body defining an internal passage, and sidewalls of the baffle body defining a first contour, defining a cavity in the airfoil body, the cavity extending inwardly from the external walls to define a second contour complementary to the first contour, and inserting the baffle into the cavity. An airfoil arrangement is also disclosed.

A transition piece assembly improves the cooling of a transition piece by increasing a flow of compressed air toward a transition piece casing. The assembly includes a transition piece including an inlet and an outlet; a transition piece casing spaced apart from the transition piece, the transition piece casing enclosing the transition piece to form an annular interspace between an inner circumferential surface of the transition piece casing and an outer circumferential surface of the transition piece, the transition piece casing including an outer circumferential surface over which compressed air flows; a support member for supporting the transition piece casing, the support member inserted into the annular interspace and seated on the outer circumferential surface of the transition piece; and a guide member that is fixed with respect to the transition piece casing and includes an axially perpendicular structure to guide the compressed air toward the transition piece casing.

A gas turbine engine component includes a static component with at least one first flow channel. The labyrinth seal rotates relative to the static component. The labyrinth seal is spaced from the static component by a second flow channel. The flow passing between the labyrinth seal and the static component will have a first portion that travels through the at least one first flow channel and a second portion that travels through the second flow channel with the first portion of the flow being reintroduced into the second flow channel to create a flow restriction.

The present technique presents a turbomachine component having an airfoil e.g. a vane of a gas turbine. The airfoil wall defines an internal space which includes a first and a second cooling channels having a first and a second impingement inserts, that define a first main and a first peripheral flow channels in the first cooling channel and a second main and a second peripheral flow channels in the second cooling channel, respectively. Impingement jets ejected from the main flow channels via impingement holes of the corresponding impingement inserts are received in the corresponding peripheral flow channels. A channel connecting conduit conducts a flow of the cooling air from the first cooling channel to the second cooling channel. The channel connecting conduit includes an inlet connected to an outlet of the first cooling channel, and an outlet connected to an inlet of the second cooling channel.

A component includes a component body. The component further includes a first passage disposed in the component body. The first passage includes a first end and a second end opposite the first end. The component further includes a second passage. The second passage extends from the second end of the first passage. The second passage includes a turn. The component further includes a third passage. The third passage extends from the second end of the first passage. The component further includes a first projection extending from a passage surface of the component body within the first passage. The first projection is disposed between the first and the second end of the first passage and is configured to direct debris transiting the first passage away from the second passage and into the third passage.