Abstract: An airfoil has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.70-0.83 inch (17.8-21.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 0.34-0.45 inch (8.5-11.5 mm). The airfoil element includes at least three of a first mode with a frequency of 3748±15% Hz, a second mode with a frequency of 6416±15% Hz, a third mode with a frequency of 14418±15% Hz, a fourth mode with a frequency of 17417±15% Hz, a fifth mode with a frequency of 19326±15% Hz and a sixth mode with a frequency of 26648±15% Hz.

Abstract: A synchronization ring for a variable vane assembly of a gas turbine engine may include a first ring portion and a second ring portion. The first ring portion and the second ring portion may be detachably coupled together to jointly define a plurality of cylindrical bores circumferentially distributed around the synchronization ring and extending radially through the synchronization ring.

Abstract: The present disclosure provides devices and methods related to rotor disk bosses. For example, a rotor disk assembly comprises a first rotor disk, wherein the first rotor disk comprises a web, disposed between a rim and a bore. The rotor disk assembly further comprises a second rotor disk operatively coupled to the first rotor disk, an inter-disk device disposed on the second rotor disk and extending axially toward the first rotor disk, and a boss disposed on the first rotor disk, wherein the boss protrudes axially from the web toward the inter-disk device.

Abstract: An assembly for operating a device, such as a variable vane, has an arm, a stem to which the arm is connected, the stem having a slot, and a member having a tab which fits into the slot.

Abstract: A synchronization ring for a variable vane assembly of a gas turbine engine may include a first ring portion and a second ring portion. The first ring portion and the second ring portion may be detachably coupled together to jointly define a plurality of cylindrical bores circumferentially distributed around the synchronization ring and extending radially through the synchronization ring.

Abstract: A synchronizing ring assembly for a variable guide vane system is disclosed. The synchronizing ring assembly is disposed about an engine axis and includes a synchronizing ring having a radially outer surface with a clevis bracket mounted to the radially outer surface of the synchronizing ring and defining radially extending openings through the clevis bracket. A plurality of fasteners are configured and adapted to be received within the radially extending openings in the clevis bracket for securing the clevis bracket to the radially outer surface of the synchronizing ring.

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: The present disclosure provides devices and methods related to rotor disk bosses. For example, a rotor disk assembly comprises a first rotor disk, wherein the first rotor disk comprises a web, disposed between a rim and a bore. The rotor disk assembly further comprises a second rotor disk operatively coupled to the first rotor disk, an inter-disk device disposed on the second rotor disk and extending axially toward the first rotor disk, and a boss disposed on the first rotor disk, wherein the boss protrudes axially from the web toward the inter-disk device.

Abstract: The present disclosure provides devices and methods related to rotor disk bosses. For example, a rotor disk assembly comprises a first rotor disk, wherein the first rotor disk comprises a web, disposed between a rim and a bore. The rotor disk assembly further comprises a second rotor disk operatively coupled to the first rotor disk, an inter-disk device disposed on the second rotor disk and extending axially toward the first rotor disk, and a boss disposed on the first rotor disk, wherein the boss protrudes axially from the web toward the inter-disk device.

Abstract: An exemplary variable vane actuation system includes, among other things, a vane arm with a vane stem contact surface and a radially outward facing surface. The vane stem contact surface is to contact a vane stem of a variable vane and thereby actuate the variable vane about a radially extending axis. The vane stem contact surface is angled relative to both the radially extending axis and the radially outward facing surface.

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: The present disclosure provides devices and methods related to rotor disk bosses. For example, a rotor disk assembly comprises a first rotor disk, wherein the first rotor disk comprises a web, disposed between a rim and a bore. The rotor disk assembly further comprises a second rotor disk operatively coupled to the first rotor disk, an inter-disk device disposed on the second rotor disk and extending axially toward the first rotor disk, and a boss disposed on the first rotor disk, wherein the boss protrudes axially from the web toward the inter-disk device.

Abstract: An assembly for operating a device, such as a variable vane, has an arm, a stem to which the arm is connected, the stem having a slot, and a member having a tab which fits into the slot.

Abstract: A synchronizing ring assembly for a variable guide vane system is disclosed. The synchronizing ring assembly is disposed about an engine axis and includes a synchronizing ring having a radially outer surface with a clevis bracket mounted to the radially outer surface of the synchronizing ring and defining radially extending openings through the clevis bracket. A plurality of fasteners are configured and adapted to be received within the radially extending openings in the clevis bracket for securing the clevis bracket to the radially outer surface of the synchronizing ring.

Abstract: An exemplary variable vane actuation system includes, among other things, a vane arm with a vane stem contact surface and a radially outward facing surface. The vane stem contact surface is to contact a vane stem of a variable vane and thereby actuate the variable vane about a radially extending axis. The vane stem contact surface is angled relative to both the radially extending axis and the radially outward facing surface.

Abstract: A rotor disk for a gas turbine engine includes a hub; a rim with a forward portion and an aft portion; and a plurality of circumferentially spaced radial scallops in the rim to form cooling slots between two disks when the rotor disk is connected to another rotor disk.

Abstract: An anti-vortex assembly for a gas turbine engine includes a support ring including a seat surrounding an opening and a bleed tube including a base with a bearing face sealing against the seat. A retaining ring is mounted within the support ring and engages the base of the bleed air tube to hold the bleed tube within the support ring.

Abstract: An assembly includes a first part, a second part, a sleeve, and a fastener. The first part has a first hole with a threaded portion therein. Additionally, the first hole has a first counterbore. The second part has a second hole with a second counterbore. The second counterbore is arranged to oppose the first counterbore. The sleeve is inserted into the second counterbore and extends to insert into the first counterbore. The fastener has a threaded end portion and a reduced diameter portion and extends through the first hole and into the second hole. The reduced diameter portion of the fastener is surrounded by the sleeve when the fastener is inserted to mount the first part with the second part.

Abstract: A rotor disk for a gas turbine engine includes a hub; a rim with a forward portion and an aft portion; and a plurality of circumferentially spaced radial scallops in the rim to form cooling slots between two disks when the rotor disk is connected to another rotor disk.

Abstract: A compressor section to be mounted in a gas turbine engine has a plurality of compressor rotors arranged from an upstream location toward a downstream location. A tie shaft applies an axial force at one end of the compressor section to a downstream one of the compressor rotors, and biases the compressor rotors against a hub at the opposite end. Vane sections are mounted intermediate the compressor rotors. The vane sections include at least some variable vanes driven by actuators mounted at a radially outer position and at least some of the fixed vanes are cantilever mounted , such that they are spaced from a compressor rotor, but unsecured at a radially inner end.