General Electric Company

Ge Infrastructure Technology, LLC

Changjie Sun

Ananda Barua

Sathyanarayanan Raghavan

Nicholas Joseph Kray

Li Zheng

Neelesh Nandkumar Sarawate

Darren Lee Hallman

Prabhjot Singh

Arun Karthi Subramaniyan

Arvind Rangarajan

Kenneth Martin Lewis

Yu Mukherjee

Daniel Jason Erno

Zachary John Snider

Thomas Earl Dyson

Larry Steven Rosenzweig

Dean Michael Robinson

Wenfeng Lu

Douglas Glenn Decesare

Gautam Suresh Naik

Bugra Han Ertas

William Dwight Gerstler

Joshua Tyler Mook

Trevor Howard Wood

Bhaskar Nanda Mondal

Kishore Ramakrishnan

Brendon James Leary

Aigbedion Akwara

Daniel Gene Dunn

Atanu Saha

Jinjie Shi

Donald Albert Bradley

John Matthew Sassatelli

Giridhar Jothiprasad

Suryarghya Chakrabarti

Raymond Floyd Martell

Lana Maria Osusky

Shenyan Huang

George Hanna Ghanime

Min Zou

Anthony Joseph Vinciquerra

Vandana Prabhakar Rallabandi

Thomas Malkus

Wanming Zhang

Christopher Jon Potokar

Evan John Dozier

Mitchell Jay Headley

Marcia Boyle Johnson

Jordan Tesorero

Claire Fridtjof Lang

Joseph Block

Yang Jiao

Anthony Poli

Sreekar Karnati

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

Airfoil include a body extending along a spanwise direction between a root end and a tip end, the body comprising a plurality of acoustic cavities each having an inlet on the airfoil; and at least one cooling channel having an inlet section an outlet section and a middle section within the airfoil extending between the inlet section and the outlet section; and at least one porous face sheet positioned on at least one inlet of the plurality of acoustic cavities.

Airfoils for turbofan engines

Turbine shroud

A method of forming an erosion shield for a turbine blade includes depositing a layer of filler material defining an upper surface. The method also includes depositing a layer of erosion-resistant material across the upper surface of the layer of filler material. An interface is defined between the layer of filler material and the layer of erosion-resistant material and has a shape of the upper surface. The method also includes machining the layer of filler material to produce the erosion shield. The erosion shield has the layer of erosion-resistant material, the machined layer of filler material, and the interface defined therebetween. An inner surface of the erosion shield is defined by the machined layer of filler material that is sized and shaped for attaching to a leading edge of the turbine blade. Each of the interface and the inner surface extend a length of the erosion shield.

Erosion-shielded turbine blades and methods of manufacturing the same

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

Methods for manufacturing dual phase soft magnetic components include combining a plurality of soft ferromagnetic particles with a plurality of paramagnetic particles to form a component structure, wherein the plurality of soft ferromagnetic particles each comprise an electrically insulative coating, and, heat treating the component structure to consolidate the plurality of soft ferromagnetic particles with the plurality of paramagnetic particles.

Dual phase soft magnetic particle combinations, components and manufacturing methods

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

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 ceramic matrix composite (CMC) component and method of fabrication including a plurality of counterflow elongated functional features. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies forming a densified body and a plurality of elongated functional features formed therein the densified body. Each of the plurality of functional features is configured longitudinally extending and in alignment with the plurality of ceramic matrix composite plies. Each of the plurality of elongated functional features includes an inlet configured in cross-ply configuration. The plurality of elongated functional features are configured to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The plurality of functional features are configured in alternating flow configuration.

Ceramic matrix composite component including counterflow channels and method of producing

An industrial asset item definition data store may contain at least one electronic record defining the industrial asset item. An automated support structure creation platform may include a support structure optimization computer processor. The automated support structure optimization computer processor may be adapted to automatically create support structure geometry data associated with an additive printing process for the industrial asset item. The creation may be performed via an iterative loop between a build process simulation engine and a topology optimization engine.

Optimizing support structures for additive manufacturing

A method, medium, and system to receive a specification defining a model of a part to be produced by an additive manufacturing (AM) process; execute an AM simulation on the model of the part to determine a prediction of thermal distortions to the part; execute a topology optimization (TO) to create TO supports that counteract the predicted thermal distortions; generate at least one rule-based support based on a geometry of the part to interface with the part at one or more regions other than the TO supports; combining the TO supports and the at least one rule-based support to generate a set of hybrid supports; save a record of the set of hybrid supports; and transmit the record of the set of hybrid supports to an AM controller to control an AM system to generate a support structure for an AM production of the part.

Hybrid support structures for additively printed parts

A nested lattice structure for use in a damping system for a turbine blade includes a first lattice structure including: a first outer passage including a hollow interior; a second outer passage including a hollow interior; and an outer node including a hollow interior and forming an intersection of the first outer passage and the second outer passage. The nested lattice structure includes a second lattice structure nested within the hollow interior of the first lattice structure. The second lattice structure includes: a first inner passage; a second inner passage; and an inner node forming an intersection of the first inner passage and the second inner passage. Each of the first inner passage, the second inner passage, and the inner node are nested within the respective first outer passage, the second outer passage, and the outer node.

Distributed nested cell damping system

A method and system to receive a specification defining a model of a part to be produced by an additive manufacturing (AM) process; define a design space to enclose the part and a support structure for the part, the support structure to support the part and printed with the part during the AM process; execute an iterative topology optimization(TO) based at least in part on the specification for the part and the defined design space, to generate a TO support structure that counteracts predicted gravity-based distortions during the AM process; save a record of the generated TO support structure; and transmit the record of the TO support structure to an AM controller, the AM controller to control an AM system to generate an instance of the part and the TO support structure based on the record.

Optimized support design for sintering parts with complex features

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Clifton Park, NY, United States of America

Changjie Sun