Abstract: 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.

Abstract: 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.

Abstract: A gas turbine engine includes first and second structures secured to one another at a bolted flange joint. A seal is supported by a third structure. A cover is arranged over the bolted flange joint and discrete from the first and second structures. The cover provides a seal land that engages the piston seal and protects the first structure from the adverse thermal environment.

Abstract: An alignment tool for use in a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a clamp portion, a component engagement portion and an arm portion that extends between the clamp portion and the component engagement portion. The clamp portion establishes a fixed datum surface for positioning a component within the gas turbine engine.

Abstract: A runner assembly includes a runner with an aperture, a cradle, and a fastener. The cradle includes a planar base with an aperture, a tab extending from the base, and fingers extending from the base. The fastener extends through the apertures for attaching the runner to the cradle, and the fingers are adjacent to the runner and constrain the runner with respect to the cradle and the fastener.

Abstract: An alignment tool for use in a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a clamp portion, a component engagement portion and an arm portion that extends between the clamp portion and the component engagement portion. The clamp portion establishes a fixed datum surface for positioning a component within the gas turbine engine.

Abstract: An air bleed system for a jet engine is provided. The air bleed system is located in the low pressure compressor chamber and comprises a movable bleed valve and a stationary, annular bleed case having a forward section and an aft section and ligaments connecting the two sections and providing structural support to the bleed case. The ligaments are machined from the bleed case into an aerodynamic shape that maximizes the flow of air through the bleed ports.

Abstract: A synchronizing assembly for a gas turbine engine has a synchronizing ring. A bumper assembly has a cradle and a bumper held within the cradle. The cradle is secured to the synchronizing ring by at least one fastener without the fastener extending through the bumper. An engine is also disclosed.

Abstract: A system for minimizing non-integral vibrations in rotor blades located in a compressor section of a gas turbine engine includes a casing having a plurality of bleed slots, at least one of the bleed slots being located in close proximity to a row of rotor blades, a plurality of structural ligaments, at least one of the structural ligaments extending between two adjacent ones of the bleed slots; and a channel for reducing the height of at least one of the structural ligaments so as to minimize the non-integral vibrations in the rotor blades in the row.

Abstract: A bumper assembly includes a bracket and a pad. The pad is connected to the bracket by a first rivet. Additionally, a synchronizing ring assembly for a gas turbine engine includes a ring section and a bumper assembly. The bumper assembly is connected to a side surface of the ring section and extends axially adjacent an inner radial surface of the ring. The bumper assembly is disposed adjacent a gap at an end of the ring section.

Abstract: A gas turbine engine includes first and second structures secured to one another at a bolted flange joint. A seal is supported by a third structure. A cover is arranged over the bolted flange joint and discrete from the first and second structures. The cover provides a seal land that engages the piston seal and protects the first structure from the adverse thermal environment.

Abstract: A valve includes a body with bleed ports and a ring. The ring surrounds the body and includes two adjacent ring segments. The ring is movable between an open position and a closed position, the latter of which prevents flow through the ports.

Abstract: A runner assembly includes a runner with an aperture, a cradle, and a fastener. The cradle includes a planar base with an aperture, a tab extending from the base, and fingers extending from the base. The fastener extends through the apertures for attaching the runner to the cradle, and the fingers are adjacent to the runner and constrain the runner with respect to the cradle and the fastener.

Abstract: A link includes a link body with two ends, a ring bore with a ring bore axis and a bearing, a mount bore with a mount bore axis and a bearing. The link also has an end curvature at the end having the ring bore wherein the curvature axis is substantially perpendicular to the ring bore axis.

Abstract: A bracket for use with a four bar linkage, has a head portion having a triangular shape, and a shank extending from a corner of the triangular head portion, the shank thickening depthwise and narrowing widthwise along its length.

Abstract: An actuation system for a bleed valve includes first and second bell cranks connected by a connecting link. The first bell crank has a first arm that is coupled to a bleed valve and a second arm that is coupled to the connecting link. The connecting link has a first end coupled to the second arm of the first bell crank and a second end coupled to a first arm of the second bell crank. A second arm of the second bell crank is coupled to an actuating element. Input is communicated through the actuating element to move the bleed valve between open and closed positions via the first and second bell cranks.

Abstract: A valve includes a body with bleed ports and a ring. The ring surrounds the body and includes two adjacent ring segments. The ring is movable between an open position and a closed position, the latter of which prevents flow through the ports.

Abstract: A synchronizing assembly for a gas turbine engine has a synchronizing ring. A bumper assembly has a cradle and a bumper held within the cradle. The cradle is secured to the synchronizing ring by at least one fastener without the fastener extending through the bumper. An engine is also disclosed.

Abstract: A system for minimizing non-integral vibrations in rotor blades located in a compressor section of a gas turbine engine includes a casing having a plurality of bleed slots, at least one of the bleed slots being located in close proximity to a row of rotor blades, a plurality of structural ligaments, at least one of the structural ligaments extending between two adjacent ones of the bleed slots; and a channel for reducing the height of at least one of the structural ligaments so as to minimize the non-integral vibrations in the rotor blades in the row.

Abstract: A bumper assembly includes a bracket and a pad. The pad is connected to the bracket by a first rivet. Additionally, a synchronizing ring assembly for a gas turbine engine includes a ring section and a bumper assembly. The bumper assembly is connected to a side surface of the ring section and extends axially adjacent an inner radial surface of the ring. The bumper assembly is disposed adjacent a gap at an end of the ring section.