General Electric Company

Cilag International Gmbh

Ethicon, Gmbh

Bryce Loring Heitman

Joseph Daniel Dennis, Jr

Ryan M Asher

John E Brady

Darrell Glenn Senile

Rafael J Ruiz Ortiz

Ion V Nicolaescu

Joseph E Hollo

Matthew C Miller

Jan Christopher Schilling

Brian D Black

Sarah Alexandra Worthington

Jason R Lesko

Richard C Smith

Shawn C Snyder

David Alexander Monroe

Amy M Krumm

Matthew S Schneider

Andrew Kolpitcke

Timothy S Holland

Fajian Zhang

Geni M Giannotti

Andrew John Breslin

Monica L Rivard

Monica L Zeckel

Steven James Murphy

Chad Paul Boudreaux

Cory G Kimball

Stephen M Leuck

Wei Guo

Patrick J Minnelli

Craig T Davis

Frederick L Estera

Benjamin M Boyd

Nathan T Cummings

Tony C Siebel

James Anthony McCrea

David Scott Stapleton

Michael Ray Tuertscher

Michael Todd Radwanski

Joseph Isosaki

Gregory Scott Phelps

Brian Gregg Feie

Greg Scott Phelps

Yachuan Yu

Junhua Zhu

Laura Isabelle Armanios

A surgical instrument, has an end effector that includes an ultrasonic blade, and a clamp arm that moves relative to the ultrasonic blade from an opened position toward an intermediate position and a closed position. The clamp arm is offset from the ultrasonic blade to define a predetermined gap in the intermediate position between the opened position and the closed position. A clamp arm actuator connects to the clamp arm and moves from an opened configuration to a closed configuration to direct the clamp arm from the opened position toward the intermediate position and the closed position. A spacer connects with the clamp arm to inhibit movement of the clamp arm from the intermediate position toward the closed position for maintaining the predetermined gap between the clamp arm and the ultrasonic blade.

Surgical instrument with selectively actuated gap-setting features for end effector

A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.

Shroud hanger assembly

A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud, which is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.

A surgical instrument has a first modular assembly and a second modular assembly. The first modular assembly has a body, an ultrasonic waveguide, an ultrasonic blade connected to a distal end of the ultrasonic waveguide, and a coupling member that movably couples with the body. The second modular assembly has a clamp arm assembly with a first pivot coupling, a clamp pad assembly with a second pivot coupling, and a distal outer sheath that selectively couples to the body of the first modular assembly via the coupling member. The distal outer sheath has an interior surface that houses a portion of the ultrasonic waveguide, and this interior surface also houses the first pivot coupling and the second pivot coupling.

Surgical instrument with removable clamp arm assembly

An ultrasonic surgical instrument includes a body, a shaft, an ultrasonic transducer, a waveguide, and an end effector coupled to a distal end of the shaft. A rotation knob is rotatably coupled to the body and is configured to rotate the shaft, the waveguide, and the end effector together relative to the body. A torque transfer structure is positioned radially outwardly of and in direct contact with the waveguide at an acoustic node thereof. The torque transfer structure is rotationally fixed relative to the waveguide and is configured to rotationally couple the waveguide with the shaft and the rotation knob. The waveguide includes a first axial constraining feature defining a distally facing surface, and the torque transfer structure includes a second axial constraining feature defining a proximally facing surface configured to abut the distally facing surface to constrain the waveguide axially relative to the torque transfer structure and the body.

Acoustic drivetrain with external collar at nodal position

Nozzles and nozzle assemblies for gas turbine engines are provided. A nozzle includes an airfoil having an exterior surface defining a pressure side and a suction side extending between a leading edge and a trailing edge, an outer band disposed radially outward of the airfoil, the outer band including a radially outwardly-facing end surface, and an inner band disposed radially inward of the airfoil, the inner band including a radially inwardly-facing end surface. The nozzle further includes a flange extending radially from one of the radially outwardly-facing end surface or the radially inwardly-facing end surface. The flange is formed from a ceramic matrix composite material and includes a plurality of ceramic matrix composite plies stacked together and generally having an L-shape in a circumferential cross-sectional view.

Nozzle and nozzle assembly for gas turbine engine

An airfoil assembly for a gas turbine engine and a method of transferring load from the ceramic matrix composite (CMC) airfoil assembly to a metallic vane assembly support member are provided. The airfoil assembly includes a forward end and an aft end with respect to an axial direction of the gas turbine engine. The airfoil assembly includes a radially outer end component, a radially inner end component, and a hollow airfoil body extending therebetween. The radially outer end component including a radially outwardly-facing end surface having a non-compression load-bearing feature extending radially outwardly and formed integrally with the outer end component, the load-bearing feature configured to mate with a complementary feature formed in a radially inner surface of a first airfoil assembly support structure and selectively positioned orthogonally to a force imparted into the airfoil assembly.

Method and system for interfacing a ceramic matrix composite component to a metallic component

Shroud assemblies for gas turbine engines are provided. A shroud assembly includes a hanger having a forward hanger arm, a rear hanger arm, and a hanger body extending between the forward hanger arm and the rear hanger arm. The shroud assembly further includes a shroud having a forward surface, a rear surface, and an inner surface and outer surface extending between the forward surface and the rear surface, the outer surface radially spaced from the inner surface, the shroud connected to the hanger. The shroud assembly further includes a support member positioned axially forward of the forward hanger arm, the support member having a radially outer portion connected to the forward hanger arm and a radially inner portion axially spaced from the shroud such that a gap is defined between the radially inner portion and an axially adjacent surface of the shroud.

Shroud assembly for gas turbine engine

Shrouds and shroud assemblies for gas turbine engines are provided. A shroud includes a shroud body. The shroud body includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a flange extending from the shroud body, and a bore hole defined in the flange. The bore hole extends generally circumferentially through the flange between a first opening and a second opening.

Shroud assembly and shroud for gas turbine engine

Methods for positioning neighboring nozzles of a gas turbine engine are provided. A method includes assembling a first nozzle assembly. The first nozzle assembly includes a first nozzle and a first nozzle support structure. The method further includes assembling a second nozzle assembly. The second nozzle assembly includes a second nozzle and a second nozzle support structure. The method further includes adjusting the first nozzle assembly and the second nozzle assembly such that an engineering dimension between the first nozzle and the second nozzle is within a predetermined engineering tolerance, and joining the first nozzle support structure and the second nozzle support structure together.

Methods for positioning neighboring nozzles of a gas turbine engine

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Cincinnati, OH, United States of America

Bryce Loring Heitman