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

Li Zheng

Gregory Carl Gemeinhardt

Peggy Lynn Baehmann

Elzbieta Kryj-Kos

Douglas Duane Ward

Gary Willard Bryant, Jr

Stefaan Guido Van Nieuwenhove

Viswanadha Gupta Sakala

Dong-Jin Shim

Tod Winton Davis

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

Yanyan Wu

Kirti Arvind Petkar

Qiang Li

Samar Jyoti Kalita

Mark Ernest Vermilyea

Trevor Howard Wood

Praveen Sharma

Michael John Franks

Max Robert Farson

Aaron Todd Sellinger

Andrew Breeze-Stringfellow

Wendy Wenling Lin

Francis Howard Little

Andrew J Lammas

Gerald Alexander Pauley

Ambika Shivamurthy

Abhijit Sinha Roy

Jan Christopher Schilling

Bin Wei

Kishore Ramakrishnan

Thomas James Batzinger

James Thompson

Ming Xie

Andrew Lee Trimmer

Suresh Subramanian

Joshua L Miller

Donald Lee Gardner

Michael Scott Lamphere

Shatil Sinha

Michael Harvey Schneider

Jian Ying Li

Egbert Geertsema

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

Shridhar Champaknath Nath

Arun Kumar

Veeraraju Vanapalli

Frank Worthoff

Giridhar Jothiprasad

Dean Michael Robinson

Bowden Kirkpatrick

Sesha Subramanian

Sultan Shair

Nicholas M Daggett

Shivam Mittal

Pinghai Yang

Joel Francis Kirk

Ram Kumar Upadhyay

Naleen Kumar Verma

Ruben Egberto Fairman

Kevin Lee Kirkeng

Thomas Malkus

Haiyan Sun

Xiaomei Fang

Bhujabal Prashant Mahadeo

Edward Atwood Rainous

Paul Izon

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.

Composite airfoil assembly for a turbine engine

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.

A composite airfoil with an airfoil core and a wall surrounding the airfoil core. The wall including a first set of stacked plies including a first type of ply having directional fibers extending in a first direction, and defining at least a portion of an exterior surface, the exterior surface extending between a leading edge and a trailing edge to define a chordwise direction and between a root and a tip to define a spanwise direction. At least one stiffener located between the airfoil core and the wall, the at least one stiffener having a second set of stacked plies.

Composite airfoil for a turbine engine

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.

Growing community of inventors

Mason, OH, United States of America

Nicholas Joseph Kray