United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Alex J Simpson

Bryan P Dube

Sean P Zamora

Lane Mikal Thornton

Daniel A Snyder

Christopher J Peters

Robert H Bush

Timothy A Swanson

Shelton O Duelm

Christopher Treat

David A Niezelski

John E Paul

Edward A Krystowski

Robert T Knowlton

Zachary D Ryan

Andrew D Burdick

Timothy Charles Nash

Paul R Senofonte

Hannes A Alholm

Richard F Norman

Christina A Stenman

Kyle J Osga

Joseph J Czapski, Jr

Bessem Jlidi

A forward outer diameter ring includes a flowpath ring extending circumferentially about a central axis and extending axially from a first end to a second end relative to the central axis. The second end of the flowpath ring is axially aft of the first end. A hoop stiffener is connected to the second end of the flowpath ring and extends circumferentially around the second end of the flowpath ring. The hoop stiffener includes a first stiffener end connected to the second end of the flowpath ring and a second stiffener end axially aft of the first stiffener end. The hoop stiffener further includes tabs formed in the second stiffener end. The tabs are circumferentially spaced apart from one another and connect the case segments to the second stiffener end. The case segments are circumferentially arranged about the central axis relative one another.

Thermally compliant forward outer-diameter ring for a gas turbine engine

Disclosed is a linkage assembly for a gas turbine engine having a link having a first end, a second end, and a rod extending therebetween, the first end having a first sliding bearing disposed within a first sliding bearing housing, a fastener comprising a first flange and a second flange, a pin extending between the first flange and the second flange, wherein the first sliding bearing is pivotally connected to the pin; and a biasing member secured between the first flange and the sliding bearing housing, the biasing member contacting the sliding bearing housing and biasing the link against rotation about a center axis for the rod of the link.

Linkage assembly preventing axial rotation of the link rod for a gas turbine engine

Linkage assembly preventing axial rotation of the link rod

A non-contact seal assembly includes a plurality of seal shoes, a seal base and a plurality of spring elements. A first of the spring elements includes a first mount, a second mount and a spring beam. The spring beam extends a length longitudinally along a centerline from the first mount to the second mount. The spring beam includes opposing first and second surfaces. The first surface is disposed a first distance from the centerline, and the second surface is disposed a second distance from the centerline. The first distance and the second distance change as the spring beam extends longitudinally along the centerline to provide at least a portion of the spring beam with a tapered geometry. The portion of the spring beam has a longitudinal length that is at least about five percent of the length of the spring beam.

Shaped spring element for a non-contact seal device

A bearing joint assembly may include a bearing sleeve, a first collar, a first mount, a pair of second mounts and a fastener, which projects through the bearing sleeve and secures the bearing sleeve to the second mounts. The bearing sleeve extends axially along a centerline and includes a spherical bearing. The first collar is configured with the bearing sleeve. A first annular channel is formed by and extends axially between the spherical bearing and the first collar. The first mount is mounted on and slidably engages the spherical bearing. The spherical bearing and the first collar are axially between the second mounts.

Spherical bearing sleeve configured with one or more discrete collars

A bearing joint assembly includes a bearing sleeve, a first mount, a pair of second mounts and a fastener. The bearing sleeve extends axially along a centerline and includes a spherical bearing, a first collar and a second collar. The spherical bearing is axially between the first collar and the second collar. An annular channel is formed by and extends axially between the spherical bearing and the first collar. The first mount is mounted on and slidably engages the spherical bearing. The bearing sleeve is axially between the second mounts. The fastener projects through the bearing sleeve and secures the bearing sleeve to the second mounts.

Spherical joint assembly with a spherical bearing between integral collars

A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and at least one rib that protrudes from the wall and extends to a rib end, the rib end having a curved transition portion near a location where the at least one rib meets the wall.

Gas turbine engine component having contoured rib end

A gas turbine engine includes an array of airfoils that include first and second segments. The first segment includes a first number of airfoils that are circumferentially spaced from one another a first angular spacing. The second segment includes a second number of airfoils that are circumferentially spaced from one another a second angular spacing. A sum of the first and second number of airfoils corresponds to a total number of airfoils in the array. The first angular spacing is based upon a first effective number of total airfoils in the array that is different than the total number of airfoils.

Gas turbine engine stator vane asymmetry

A drive link assembly includes a case having a spherically formed inner ring. A clevis is affixed to a surface of the case such that is disposed horizontally between a first end and a second end of the clevis. A spacer having a spherical inset portion is positioned on the surface horizontally between the clevis and the spherically formed inner ring, such that the spherical inset portion is aligned with the spherically formed inner ring. A spherical bearing is seated within the spherically formed inner ring. A rod is affixed to an outer surface of the spherical bearing.

Enhanced durability drive link for high load misalignment

A gas turbine engine includes an array of airfoils. Each airfoil includes a first circumferentially extreme position. The first circumferentially extreme positions of the airfoils are circumferentially spaced apart from one another a pitch. Each airfoil includes a second circumferentially extreme position circumferentially spaced from the first circumferentially extreme position in an angular spacing that is at least one half the pitch.

Gas turbine engine airfoil curvature

A liner assembly includes a plurality of flaps arranged about a central axis and operable to move relative to the central axis. Each of the plurality of flaps defines a forward end and an aft end, lateral sides, and an inner surface and an outer surface relative to the central axis. Each of the plurality of flaps has a thickness between the inner surface and the outer surface, and thickness varies in a lateral direction between the lateral sides.

Convergent-divergent gas turbine nozzle comprising movable flaps having a variable thickness in a lateral direction

A mechanism included in a convergent-divergent nozzle connected to an aft portion of a gas turbine engine, which mechanism includes a convergent flap configured to be kinematically connected to the aft portion of the gas turbine engine, a divergent flap pivotally connected to the convergent flap and configured to be kinematically connected to the aft portion of the gas turbine engine, at least one actuator configured to be connected to the aft portion of the gas turbine engine and to mechanically prescribe the position of the convergent flap and the divergent flap by moving through one or more positions, and at least one biasing apparatus. The biasing apparatus is configured to position at least one of the convergent flap and the divergent flap independent of the positions of the actuator by substantially balancing a force on the at least one of the convergent flap and the divergent flap produced by a gas pressure on the nozzle.

Nozzle-area ratio float bias

A gas turbine engine has the convergent flaps and seals of an adjustable cross-sectional area nozzle connected to associated liners with a thermally compliant bracket. The bracket includes spaced feet with an intermediate notch spaced away from the liner. In this manner, a temperature gradient along the liner can be easily compensated at the connection of the bracket to the liner by adjustment within the notch. In other features, the bracket is riveted to the liner, providing further resistance to thermal expansion due to temperature gradiations.

Growing community of inventors

Tolland, CT, United States of America

Alex J Simpson