General Electric Company

General Electric Company Polska Sp. Z O.o.

Ge Marmara Technology Center Muhendislik Hizmetleri Ltd

Nicholas Joseph Kray

Nitesh Jain

Arthur William Sibbach

Abhijeet Jayshingrao Yadav

David William Crall

Scott Roger Finn

Ravindra Shankar Ganiger

Daniel Edward Mollmann

Gary Willard Bryant, Jr

Gregory Carl Gemeinhardt

Li Zheng

Elzbieta Kryj-Kos

Peggy Lynn Baehmann

Douglas Duane Ward

Stefaan Guido Van Nieuwenhove

Tod Winton Davis

Viswanadha Gupta Sakala

Dong-Jin Shim

Kishore Budumuru

Nagamohan Govinahalli Prabhakar

Brandon Wayne Miller

Narendra Digamber Joshi

Apostolos Pavlos Karafillis

Changjie Sun

Manoj Kumar Jain

Thomas Chadwick Waldman

Ian Francis Prentice

Todd Alan Anderson

Michael John Franks

Yanyan Wu

Kirti Arvind Petkar

Qiang Li

Mark Ernest Vermilyea

Trevor Howard Wood

Praveen Sharma

Max Robert Farson

Aaron Todd Sellinger

Andrew Breeze-Stringfellow

Ming Xie

Wendy Wenling Lin

Suresh Subramanian

Francis Howard Little

Andrew J Lammas

Gerald Alexander Pauley

Ambika Shivamurthy

Abhijit Sinha Roy

Bin Wei

Jan Christopher Schilling

Kishore Ramakrishnan

Thomas James Batzinger

James Thompson

Andrew Lee Trimmer

Frank Worthoff

Joshua L Miller

Donald Lee Gardner

Michael Scott Lamphere

Shatil Sinha

Egbert Geertsema

Jian Ying Li

Michael Harvey Schneider

Howard Paul Weaver

Leslie L Langenbrunner

Benjamin James Roby

Gary W Bryant

Thomas Ory Moniz

Bugra Han Ertas

Hiranya Kumar Nath

Bhaskar Nanda Mondal

Waseem Ibrahim Faidi

Prabhjot Singh

Vidyashankar Ramasastry Buravalla

Edward James Nieters

Michael Edward Eriksen

Changting Wang

James Norman Barshinger

Giridhar Jothiprasad

Shridhar Champaknath Nath

Veeraraju Vanapalli

Arun Kumar

Dean Michael Robinson

Nicholas M Daggett

Bowden Kirkpatrick

Sesha Subramanian

Sultan Shair

Shivam Mittal

Pinghai Yang

Joel Francis Kirk

Ram Kumar Upadhyay

Thomas Malkus

Naleen Kumar Verma

Ruben Egberto Fairman

Kevin Lee Kirkeng

Xiaomei Fang

Deepak Ghiya

Bhujabal Prashant Mahadeo

Haiyan Sun

Edward Atwood Rainous

Paul Izon

Ming Cheng Li

Outlet guide vane mounts with an airfoil structure are disclosed herein. The airfoil structure includes an airfoil platform, a composite material, a load spreader block, and a shim material, the composite material and a load spreader block positioned on the airfoil platform, the composite material having a first stiffness and the load spreader block having a second stiffness, and a shim material positioned between the composite material and the load spreader block, the shim material having a third stiffness different from at least one of the first stiffness or the second stiffness.

Outlet guide vane mount

A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

Turbine engine with composite airfoils

A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion. The leading edge protector includes at least one projection extended past a base of the airfoil to a root of the airfoil.

Collars to retain multiple fan blades for use with an aircraft engine are disclosed herein. An example gas turbine engine includes a plurality of fan blades and a collar coupled to the plurality of fan blades. The collar includes a first mating piece and a second mating piece coupled to the first mating piece. The first and second mating pieces define an opening configured to receive a first root of a first fan blade of the plurality of fan blades, and the first and second mating pieces define a slot to retain a second root of a second fan blade of the plurality of fan blades.

Pitch-controlled blade retention collar

A composite airfoil assembly has a composite airfoil, a spar, and a wrap. The composite airfoil has an outer wall and a composite skin. The outer wall extends between a root and a tip. The outer wall defines an interior. The composite skin at least partially defines the outer wall. The spar having a spar centerline axis, a stem, a base, and a transition interconnecting the base and the stem.

Composite airfoil assembly having a composite airfoil and spar

A gas turbine engine includes a fan section, a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. Sets of blades can be rotatably driven about the longitudinal axis in the fan section, the compressor section, and the turbine section. The airfoil structure defining one or more of the blades or vanes can include a structure which includes a woven or foam core, with a laminate skin, and an exterior coating.

Turbine engine airfoil with a woven core

A composite airfoil assembly for a gas turbine engine. The composite airfoil assembly includes a composite airfoil having opposite pressure and suction sides and opposite leading and trailing edges. The pressure side and the suction side extend axially between the leading edge and the trailing edge. The composite airfoil has a laminate skin that is applied to at least a portion of a core. A first cladding and a second cladding, having adjacent segments, are located on the pressure side or the suction side of the composite airfoil.

Composite airfoil assembly for a turbine engine

A turbine engine with an engine core defining an engine centerline and comprising a rotor assembly and a stator assembly. The turbine engine including a primary stage of airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor assembly. A subsidiary stage of airfoils located upstream of the primary stage of airfoils and circumferentially arranged about the engine centerline.

Turbine engine with a primary stage of airfoils and a subsidiary stage of airfoils

An engine component for a turbine engine. The engine component has a composite structure and a cover structure. The composite structure has a composite structure outer wall and a composite structure edge. The cover structure encases at least a portion of the composite structure outer wall. The cover structure has a main body. The main body extends along the at least a portion of the composite structure outer wall.

Engine component

Hybrid composite components, such as gas turbine engine containment assemblies, a hybrid composite component having an annular composite shell and an annular metallic shell joined with the composite shell. A containment assembly including a containment case extending along an axial direction about a longitudinal centerline of the gas turbine engine. The containment case has an inner surface and an outer surface spaced apart along a radial direction and includes a first composite shell joined with a metallic shell. The metallic shell defining a first portion of the inner surface and the first composite shell defining a second portion of the inner surface.

Hybrid composite components

The disclosure herein relates to an automated fiber placement assembly for forming a component by the successive layering of strips of fiber tows with a pressure roller. The pressure roller has a rotational axis about which the pressure roller rotates to apply the strip of fiber tows to the component. The pressure roller can be shaped complementary to a non-uniform surface of the component for even application of the strip of fiber tows to the component.

Automated fiber placement assembly with pressure roller

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 composite airfoil assembly for a turbine engine. The composite airfoil assembly includes a woven core having a core exterior. The woven core includes a first region, a second region, and a transition region. A skin is applied to at least a portion of the woven core at the core exterior.

Growing community of inventors

Mason, OH, United States of America

Nicholas Joseph Kray