General Electric Company

Vetco Gray Inc.

Li Zheng

Nicholas Joseph Kray

Changjie Sun

Trevor Howard Wood

Kishore Ramakrishnan

Scott Roger Finn

Pinghai Yang

Teresa Tianshu Chen-Keat

Bugra Han Ertas

Yuri Alexeyevich Plotnikov

Gary Willard Bryant, Jr

Giridhar Jothiprasad

Chad Yates

Tod Winton Davis

Yanyan Wu

Thomas Malkus

Ruben Egberto Fairman

Xichang Zhang

Mitchell Jay Headley

Benjamin Thomas Van Oflen

Daryl John Burford

Pawel Pres

Tomas Muchenik

Michael Scott Hartle

An airfoil assembly for a turbine engine having a composite spar, a sleeve, and a set of lobes. The composite spar includes an exterior spar portion, where at least part of the exterior spar portion of the composite spar is received at a sleeve inner surface of the sleeve. The set of lobes extends from the composite spar and is received by a set of recesses at the sleeve inner surface.

Airfoil assembly having a composite spar

Methods, apparatus, systems, and articles of manufacture are disclosed for a variable bleed valve assembly. An example variable bleed valve assembly a variable bleed valve (VBV) door corresponding to a bleed port and a first unison ring, the VBV door coupled to the first unison ring, the first unison ring to move in a circumferential direction between a first position and a second position causing the VBV door to move between the first position and the second position.

Bleed valve assemblies

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine; a fan including a plurality of fan blades rotatably driven by the turbomachine; a nacelle surrounding at least in part the plurality of fan blades of the fan; and a clearance control system including a control ring positioned at least partially within the nacelle, coupled to the nacelle, or both for control of a clearance gap between the plurality of fan blades and the nacelle.

Clearance control system for a gas turbine engine

Morphable rotor blades for a turbine engine systems include a root portion and an airfoil portion having a morphable portion including a morphable material that changes shape in response to a stimulus.

Morphable rotor blades and turbine engine systems including the same

An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane formed of a first material, and an edge guard disposed about an edge of the fan blade. The edge guard may include a matrix composite that has a toughness that is greater than a toughness of the first material. The airfoil may include a fan blade or an outlet guide vane. The first material of the airfoil may include a metal alloy and/or a matrix composite. A method of manufacturing an airfoil for a fan section of a turbine engine may include manufacturing an edge guard, attaching the edge guard to the airfoil.

Airfoils for a fan section of a turbine engine

Cover plate connections for a hollow fan blade are disclosed. An example fan blade includes a hollow body including a surface defining an airfoil, the hollow body including an aperture extending through the surface, a cover plate, and at least one connection element to couple the cover plate to the surface such that the cover plate encloses the aperture.

Cover plate connections for a hollow fan blade

Methods, apparatus, systems, and articles of manufacture are disclosed to implement an integrated stator-fan frame assembly. An integrated fan exit stator-fan frame strut assembly for a gas turbine engine includes a fan exit stator portion having an airfoil including a leading edge and a trailing edge, and a fan frame strut portion including a leading edge and a trailing edge, the leading edge of the fan frame strut portion aerodynamically integrated with the trailing edge of the fan exit stator portion.

Integrated stator-fan frame assembly

Methods, apparatus, systems, and articles of manufacture are disclosed to implement a low radius ratio fan blade for a gas turbine engine. A fan blade for a gas turbine engine includes an airfoil including a leading edge and a trailing edge extending between a root and a tip of the airfoil, a distance between the leading edge and the trailing edge defining a flow path length, a leading edge hub point defined by a radially innermost point of the leading edge, and an axial dovetail including a pair of opposed pressure faces, an axial length of the axial dovetail less than the flow path length, a top edge of the axial dovetail separating the pressure faces from the airfoil, the top edge of the axial dovetail radially outward of the leading edge hub point.

Low radius ratio fan blade for a gas turbine engine

Methods, apparatus, systems, and articles of manufacture to provide damping of an airfoil are disclosed. An example airfoil is disposed in a flow path, the airfoil including a shell defining an exterior surface of the airfoil and forming a cavity in an interior surface of the airfoil, and a lattice damper disposed in the cavity, the lattice damper to reduce vibrational loads exerted on the airfoil.

Methods and apparatus to provide damping of an airfoil

An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane, and an edge guard attached thereto. The edge guard may include a heating conduit disposed within at least a portion of the edge guard. An anti-icing system for a plurality of fan blades or outlet guide vanes may include a fluid supply pathway configured to supply heating fluid to respective ones of a plurality of heating conduits within the edge guards attached to respective ones of a plurality of fan blades and/or to a plurality of outlet guide vanes. The heating fluid may include bleed air from a core air flowpath. A method of inhibiting icing on an airfoil may include flowing a heating fluid into a heating conduit disposed within an edge guard attached to the airfoil and heating the edge guard with the heating fluid.

Anti-icing systems and airfoils for a fan section of a turbine engine

Blades including integrated damping structures are disclosed herein. An airfoil to be disposed within a flow path of a gas turbine engine, the gas turbine engine defining an axial axis, a radial axis and a circumferential axis comprising an airfoil body including a first face, a second face and a recessed portion formed in the second face, and an airfoil cap having a first surface, the airfoil cap disposed within the recessed portion, the first surface substantially flush with the second face.

Blades including integrated damping structures and methods of forming the same

A method for generating a computer model of a composite component includes generating a surface mesh based on a ply drop region and a ply curved surface and generating node data including a plurality of node points relative to the ply drop region. The method also includes receiving composite data relating to a plurality of composite plies and generating a three dimensional model based on the composite data. The method further includes receiving layup table information and applying the node data, based on the layup table information, to generate a curve through a center of the surface mesh to define a plurality of element sets. The method also includes receiving composite draping data and determining, based on the draping data, where each element set intersects the three dimensional model. The method also includes analyzing an angle deviation of the plies based on the intersection of the element sets.

System and methods of generating a computer model of a composite component

A wellhead assembly having a tubular magnetized in at least one selected location, and a sensor proximate the magnetized location that monitors a magnetic field from the magnetized location. The magnetic field changes in response to changes in mechanical stress of the magnetized location, so that signals from the sensor represent loads applied to the tubular. Analyzing the signals over time provides fatigue loading data useful for estimating structural integrity of the tubular and its fatigue life. Example tubulars include a low pressure housing, a high pressure housing, conductor pipes respectively coupled with the housings, a string of tubing, a string of casing, housing and tubing connections, housing and tubing seals, tubing hangers, tubing risers, and other underwater structural components that require fatigue monitoring, or can be monitored for fatigue.

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Niskayuna, NY, United States of America

Li Zheng