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

Jan Christopher Schilling

Kishore Ramakrishnan

Bin Wei

Thomas James Batzinger

James Thompson

Andrew Lee Trimmer

Joshua L Miller

Frank Worthoff

Donald Lee Gardner

Michael Scott Lamphere

Shatil Sinha

Egbert Geertsema

Michael Harvey Schneider

Jian Ying Li

Howard Paul Weaver

Leslie L Langenbrunner

Benjamin James Roby

Gary W Bryant

Marcia Boyle Johnson

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

Arun Kumar

Shridhar Champaknath Nath

Veeraraju Vanapalli

Dean Michael Robinson

Bowden Kirkpatrick

Sesha Subramanian

Nicholas M Daggett

Sultan Shair

Shivam Mittal

Pinghai Yang

Joel Francis Kirk

Thomas Malkus

Ram Kumar Upadhyay

Naleen Kumar Verma

Ruben Egberto Fairman

Kevin Lee Kirkeng

Haiyan Sun

Xiaomei Fang

Deepak Ghiya

Bhujabal Prashant Mahadeo

Edward Atwood Rainous

Paul Izon

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

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

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.

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.

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Mason, OH, United States of America

Nicholas Joseph Kray