Abstract: A method for enhancing interaction between a customer and a customer service representative of a company is provided. A graphical user interface (GUI) of a windows control tool is displayed. A type of an interaction between the customer and the customer service representative at a computer operated by the company is determined. One or more applications associated with the type of interaction are launched based on a predetermined display layout associated with the type of interaction. One or more application windows corresponding to the launched applications are arranged on a screen based on the predetermined display layout associated with the type of interaction. The windows control tool is configured to control the one or more application windows based on customer service representative's input. The GUI of the windows control tool displays a plurality of window objects corresponding to the one or more launched applications.

Abstract: Integrally bladed rotors (IBRs) are described. The IBRs include a central hub, an outer rim defining an outer circumference of the central hub, the outer rim defining a plurality of platforms, a plurality of circumferentially distributed blades, wherein a blade extends from each of the plurality of platforms, a rotor slot arranged between two adjacent blades, wherein the rotor slot is defined by a cut within the outer rim, and a rotor slot insert installed within the rotor slot, the rotor slot insert sized and shaped to fit within the rotor slot and prevent air leakage from a first side of the central hub to a second side of the central hub through the rotor slot during operation of the integrally bladed rotor.

Abstract: A vane arm assembly for a gas turbine engine is provided including: a vane arm having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by an aperture wall; a vane stem extending through the aperture of the vane arm; a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and an impedance clip partially enclosing a portion of the second end of the vane arm to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.

Abstract: A variable vane actuation system of a gas turbine engine is provided. The variable vane actuation system including: a variable vane; a vane stem operably associated with the variable vane, wherein the variable vane is configured to rotate with the vane stem; a vane arm having vane stem end and a vane pin end opposite the vane stem end, the vane arm being operably connected to the vane stem at the vane stem end; and a rotational variable differential transformer operably connected to the vane stem, the rotational variable differential transformer configured to detect an amount of rotation of the vane stem.

Abstract: A rotor blade for a gas turbine engine includes a blade extending from a root and a contoured tip portion at a first end of the blade. The first end is opposite the root. The contoured tip portion includes a first sloped region and a second sloped region. The second sloped region is steeper than the first sloped region, relative to a platform.

Abstract: Integrally bladed rotors (IBRs) are described. The IBRs include a central hub, an outer rim defining an outer circumference of the central hub, the outer rim defining a plurality of platforms, a plurality of circumferentially distributed blades, wherein a blade extends from each of the plurality of platforms, a rotor slot arranged between two adjacent blades, wherein the rotor slot is defined by a cut within the outer rim, and a rotor slot insert installed within the rotor slot, the rotor slot insert sized and shaped to fit within the rotor slot and prevent air leakage from a first side of the central hub to a second side of the central hub through the rotor slot during operation of the integrally bladed rotor.

Abstract: A vane arm assembly for a gas turbine engine is provided including: a vane arm having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by an aperture wall; a vane stem extending through the aperture of the vane arm; a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and an impedance clip partially enclosing a portion of the second end of the vane arm to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.

Abstract: A rotor system for a gas turbine engine may comprise a shrouded blade assembly. The shrouded blade assembly may include a blade configured to rotate about a central longitudinal axis of the gas turbine engine, an inner diameter shroud located at a proximal end of the blade, and a blade tip shroud located at a distal end of the blade. A radial seal assembly may be located radially outward of a distal surface of the blade tip shroud.

Abstract: A variable vane actuation system of a gas turbine engine is provided. The variable vane actuation system including: a variable vane; a vane stem operably associated with the variable vane, wherein the variable vane is configured to rotate with the vane stem; a vane arm having vane stem end and a vane pin end opposite the vane stem end, the vane arm being operably connected to the vane stem at the vane stem end; and a rotational variable differential transformer operably connected to the vane stem, the rotational variable differential transformer configured to detect an amount of rotation of the vane stem.

Abstract: A vane arm assembly for a gas turbine engine. The vane arm assembly includes a vane arm defining an aperture at an end thereof with an aperture wall. The vane arm assembly also includes a vane stem extending through the aperture of the vane arm. The vane arm assembly further includes a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem. The vane arm assembly yet further includes an impedance ring disposed within the aperture of the vane arm and within an impedance ring groove defined by the vane stem to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.

Abstract: Tracks (35), fastened to static structure of an aircraft engine nozzle, guide sliders (32) journaled in struts (27, 28) fastened to a flap (23) of the nozzle. Each slider and attached journal axle or bolt (33) is formed of cobalt, and each track slider surface (61) and journal bushings (43, 44) are formed of a nickel alloy to reduce wear from rubbing. Track slides (40, 41) are mounted to the static structure of the nozzle by blind bolts (68) having a tool recess (70) at its threaded tip to prevent the bolt (68) from turning as a nut is secured. Each slider has limited rotation due to a pin (102), thereon engaging a slot in a tab (100) of the bushing (43) to assist in inserting the slider (32) into the beveled ends of the tracks (35, 36), when mounting or replacing a flap.

Abstract: A rotor blade for a gas turbine engine includes a blade extending from a root and a contoured tip portion at a first end of the blade. The first end is opposite the root. The contoured tip portion includes a first sloped region and a second sloped region. The second sloped region is steeper than the first sloped region, relative to a platform.

Abstract: Tracks (35), fastened to static structure of an aircraft engine nozzle, guide sliders (32) journaled in struts (27, 28) fastened to a flap (23) of the nozzle. Each slider and attached journal axle or bolt (33) is formed of cobalt, and each track slider surface (61) and journal bushings (43, 44) are formed of a nickel alloy to reduce wear from rubbing. Track slides (40, 41) are mounted to the static structure of the nozzle by blind bolts (68) having a tool recess (70) at its threaded tip to prevent the bolt (68) from turning as a nut is secured. Each slider has limited rotation due to a pin (102), thereon engaging a slot in a tab (100) of the bushing (43) to assist in inserting the slider (32) into the beveled ends of the tracks (35, 36), when mounting or replacing a flap.

Abstract: Tracks (35), fastened to static structure of an aircraft engine nozzle, guide sliders (32) journaled in struts (27, 28) fastened to a flap (23) of the nozzle. Each slider and attached journal axle or bolt (33) is formed of cobalt, and each track slider surface (61) and journal bushings (43, 44) are formed of a nickel alloy to reduce wear from rubbing. Track slides (40, 41) are mounted to the static structure of the nozzle by blind bolts (68) having a tool recess (70) at its threaded tip to prevent the bolt (68) from turning as a nut is secured. Each slider has limited rotation due to a pin (102), thereon engaging a slot in a tab (100) of the bushing (43) to assist in inserting the slider (32) into the beveled ends of the tracks (35, 36), when mounting or replacing a flap.

Abstract: A multi axis slide carriage system includes a channeled track, a slide, a shaft and a slide carriage bracket. The channeled track extends along a first axis. The slider slides along the first axis within the channeled track, and includes a slider segment aperture extending therein along a second axis. The shaft includes a slider segment connected to a carriage bracket segment. The slider segment slides along the second axis within the slider segment aperture. The slide carriage bracket is positioned adjacent to the channeled track, and is connected to the carriage bracket segment.

Abstract: A flexible seal system for a gas turbine engine includes an annular mounting bracket, an annular support bracket, an annular flexible seal and a plurality of mounting spacers. The flexible seal extends axially between a first mounting segment and a second mounting segment. The first mounting segment is connected axially between the mounting bracket and the support bracket, and includes a plurality of mounting apertures that extend axially through the first mounting segment. Each of the mounting spacers is arranged within a respective one of the mounting apertures, and extends axially between the mounting bracket and the support bracket.

Abstract: A gas turbine engine system includes an airframe support, a gas turbine engine mounted to the airframe support, a nozzle exhaust mounted to the airframe support, and a flexible annular seal having a first end that is attached to the gas turbine engine and a second end that is attached to an exhaust nozzle. The flexible annular seal may include a flexible annular wall that permits relative deflection between the gas turbine engine and the exhaust nozzle to facilitate the reduction of undesirable load transfer.

Abstract: Tracks (35), fastened to static structure of an aircraft engine nozzle, guide sliders (32) journaled in struts (27, 28) fastened to a flap (23) of the nozzle. Each slider and attached journal axle or bolt (33) is formed of cobalt, and each track slider surface (61) and journal bushings (43, 44) are formed of a nickel alloy to reduce wear from rubbing. Track slides (40, 41) are mounted to the static structure of the nozzle by blind bolts (68) having a tool recess (70) at its threaded tip to prevent the bolt (68) from turning as a nut is secured. Each slider has limited rotation due to a pin (102), thereon engaging a slot in a tab (100) of the bushing (43) to assist in inserting the slider (32) into the beveled ends of the tracks (35, 36), when mounting or replacing a flap.

Abstract: An article includes a body portion made of a metal and configured for use in a gas turbine engine, a sensing feature monolithically formed with the body portion, and an interior passage connected to the sensing feature and passing through the body portion. An article with integrated sensing features may be made additive manufacturing, resulting in a structure having internal passageways connecting an aperture at one surface of the monolithic article to a second aperture at another surface of the monolithic article at the opposite end of the internal passageway.

Abstract: A set of adjustable and convertible headphones includes a headband, an adjustment member, and an earpiece. The adjustment member is connected to the headband by a hinge; earpiece has a channel receiving the adjustment member and is slidably connected to the adjustment member. Rotation of the adjustment member with respect to the headband is spring-loaded in only one direction. The adjustment member and the earpiece in combination include a detent mechanism for resisting sliding movement of the earpiece with respect to the adjustment member. The adjustment member may be completely removed from the channel, thereby disconnecting the earpiece from the headband. The earpiece may then be replaced by another ear covering (e.g., an earmuff, an ear protector, etc.) as desired. The replacement ear covering may include an audio speaker, for example an audio/earmuff combination earpiece.