General Electric Company

Other

Nuovo Pignone Spa

Scott Roger Finn

Nicholas Joseph Kray

Wendy Wen-Ling Lin

Apostolos Pavlos Karafillis

John J Fitzgerald

Peggy Lynn Baehmann

Manoj Kumar Jain

Nagamohan Govinahalli Prabhakar

Thomas Chadwick Waldman

Nitesh Jain

Iacopo Giovannetti

Andrea Massini

Dong-Jin Shim

William Elliot Bachrach

Mojibur Rahman

David William Crall

Ravindra Kumar Pandey

Ian Francis Prentice

Bulent Aksel

Frank Worthoff

Massimo Giannozzi

Gregory Carl Gemeinhardt

Li Zheng

Benjamin James Roby

Peter Michael Finnigan

Julian O'Flynn

Qi Zhu

Christophe Lanaud

William Elliott Bachrach

Jan Christopher Schilling

Trevor Howard Wood

Kishore Ramakrishnan

Weiping Wang

James Thompson

Ming Xie

Wendy Wenling Lin

Craig Douglas Young

Warren Rosal Ronk

Kevin Warner Flanagan

James Claude Carnahan

Stephen Mark Whiteker

William Howard Hasting

Douglas Duane Ward

Donald Joseph Kasperski

Mustafa Dindar

Joseph T Stevenson

Shatil Sinha

Arjan Johannes Hegeman

Lee Alan Blanton

Guy Wayne DeLeonardo

Xiaomei Fang

Govindarajan Rengarajan

Edward Atwood Rainous

Curt Brian Curtis

Qiang Li

Xiaolan Wei

Bo Wang

Joel Primmer White

Robert Paul Tyler

Rachel Marie Suffield

Pranav Dhoj Shah

Dong Jin Shim

Donald Frederick Mowbray

Deepali Bhate

Donald Fredrick Mowbray

Massimo Gainnozzi

Julian O'FLYNN

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 apparatus a multiple layer structure having a sub-portion defining an impact zone, and having an inner composite fiber layer, an outer composite fiber layer overlying the inner composite fiber layer, and a woven glass layer, where the inner composite fiber layer, outer composite fiber layer, and the woven glass layer overly the impact zone.

Multiple layer structure

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

Walls of gas turbine engine casings, fan cases, and methods for forming walls, e.g., fan case walls, are provided. For example, a wall comprises a plurality of composite plies arranged in a ply layup. The wall is annular and circumferentially segmented into a plurality of regions that include at least one first region and at least one second region. The ply layup in the first and second regions is different such that the ply layup is non-axisymmetric. An exemplary fan case comprises an annular inner shell, a filler layer, an annular back sheet, and an annular outer layer. The back sheet is circumferentially segmented into a plurality of regions, including at least one first region and at least one second region, and comprises a plurality of composite plies arranged in a ply layup that is different in the first and second regions such that the ply layup is non-axisymmetric.

Casing having a non-axisymmetric composite wall

A softwall containment system for a machine includes an inner wall circumscribing a bladed rotatable member of the machine and extending from a forward end to an aft end. The softwall containment system also includes an outer wall circumscribing the inner wall and extending from a forward end to an aft end. The outer wall is spaced radially outwardly from the inner wall. The outer wall extends axially between a first joint coupling the forward end of the inner wall to the forward end of the outer wall and a second joint coupling the aft end of the inner wall to the aft end of the outer wall. The softwall containment system also includes an anti-ballistic material wrap covering the outer wall, the anti-ballistic material wrap including at least one of a first extension extending forward of the first joint and a second extension extending aft of the second joint.

Softwall containment systems

Containment assemblies and methods for forming containment assemblies of gas turbine engines are provided. For example, a containment assembly comprises a containment case including a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. As another example, a containment assembly comprises an inner case and a containment case comprising a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. The containment case includes a greater proportion of the coated fibers at an inner surface of a layer of the containment case than at a location within the containment case that is radially outward from the inner surface. Methods for forming a containment assembly of a gas turbine engine are provided.

Containment case having ceramic coated fibers

An apparatus and method for a multiple layer fan casing surrounding a fan having a plurality of circumferentially spaced blades rotatable about a rotational axis and having a sub-portion defining a blade impact zone, the multiple layers comprising an inner fiber layer confronting the blades, an outer fiber layer overlying the inner carbon layer, a glass layer sandwiched between the inner and outer composite fiber layers.

Fan casing with annular shell

A containment structure for surrounding a rotatable machine includes a double-walled inner shell having a forward end, an aft end, and a substantially cylindrical body extending therebetween. The inner shell includes an inner wall at least partially surrounding a bladed portion of the bladed rotor, and an outer portion that branches radially outward from the inner wall. The containment structure also includes a substantially cylindrical back sheet coupled to the outer portion and disposed radially outward of the inner wall.

Airfoil containment structure including a notched and tapered inner shell

A turbine engine that includes an engine casing including a shell and an angel wing member. The angel wing member includes a base defined at the shell and a tip positioned distal from the base. The turbine engine also includes a backsheet extending over the angel wing member such that an angled region is defined in the backsheet at an interface with the tip. The tip has a predetermined contour capable of mitigating stress concentrations in the angled region induced from said tip.

Turbine engine and containment assembly for use in a turbine engine

A composite airfoil comprises a leading edge and a trailing edge, a pressure side and a suction side extending between the leading edge and the trailing edge, a tip at a radial outer end of the airfoil, a shank at a radial inner end of the airfoil, a dovetail connected to the shank, and a metal patch disposed between the dovetail and the shank.

Composite airfoil metal patch

A backsheet for use in a turbine engine fan case includes a first portion including a first portion first end and an opposing first portion second end. The first portion is tapered between the first portion first end and the first portion second end. The backsheet also includes a second portion coupled to the first portion. The second portion includes a second portion first end and an opposing second portion second end. The second portion defines a constant thickness between the second portion first end and the second portion second end.

Tapered composite backsheet for use in a turbine engine containment assembly

A centrifugal impeller for a turbomachine is provided. The centrifugal impeller comprises a plurality of aerodynamic vanes, each of the aerodynamic vanes having internal walls on which is associated a fabric element.

Centrifugal impeller and turbomachine

A mold for a centrifugal impeller for a turbomachine is provided. The mold comprises at least one annular insert, wherein the annular insert comprises a plurality of aerodynamic vane inserts configured to reproduce an annular assembly of aerodynamic vanes of a finished centrifugal impeller.

Mold for a centrifugal impeller, mold inserts and method for building a centrifugal impeller

A composite article including composite component mounted on a spar including a shank extending heightwise from below component base up into composite component. Tab at an upper end of shank substantially or fully embedded in the composite component and at least one ply surface pattern of the composite component contacting and generally conforming to at least one spar surface pattern on the tab. Spar surface pattern may include spaced apart spar surface protrusions with spar surface spaces therebetween and spar surface protrusions extending outwardly from spar and disposed between tows in ply surface pattern. Tows may be layed up in spar surface spaces. Spar surface pattern may include continuous or segmented spaced spar surface protrusions and spar surface spaces therebetween with tows in ply surface pattern disposed in spar surface spaces. The composite article may be a composite blade or vane including a composite airfoil.

Attachment of composite article

A rotary machine includes a machine stator and a machine rotor rotatable relative to the machine stator and having a metal shaft portion, a composite impeller portion, and at least a first metal ring portion securing the composite impeller portion to the metal shaft portion, the metal ring portion having a first interface with the composite impeller portion and a second interface with the metal shaft portion.

Rotary machine including a machine rotor with a composite impeller portion and a metal shaft portion

Growing community of inventors

Niskayuna, NY, United States of America

Scott Roger Finn