United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Colin J Kling

Darin S Lussier

James J McPhail

Grant O Cook, Iii

James T Roach

Shari L Bugaj

James F O'Brien

Matthew A Turner

JinQuan Xu

William Bogue

Joseph Parkos, Jr

Mark W Costa

Charles R Watson

Gary M Lomasney

Steven Clarkson

David R Lyders

Charles W Brown

Matthew R Rader

Wendell V Twelves

Glenn Levasseur

Thomas J Robertson, Jr

David A Topol

Barry Barnett

Christopher J Hertel

Shelton O Duelm

Carney R Anderson

Scot Adams Webb

Peter V Tomeo

Michael Parkin

Christopher M Quinn

Nicholas J Lawliss

Scott A Smith

Corey L Hubbert

Scot A Webb

Michael Caulfield

Majidullah Dehlavi

Grant O Iii Cook

Darin X Lussier

Iii Grant O Cook

Michael J Parkin

A fan includes a rotor hub comprising a slot and a blade comprising an airfoil extending from a blade root in a first direction. The blade root is configured to be received in the slot. The fan also includes a deformable spacer situated between the rotor hub and the blade root in the slot, a first blade lock situated at a first side of the slot, and a second blade lock situated at a second side of the slot opposite the first side. At least one of the first and second blade locks includes a tab configured to extend between the blade root and the rotor hub and to compress the spacer such that the spacer exerts a force on the blade in the first direction. A method of assembling a fan and another example fan are also disclosed.

Blade spacer

A retention assembly for a fan case liner including a retention bracket including a tab; a damper comprising a forward end opposite an aft end, the damper comprising an exterior surface extending between the forward end and the aft end, the damper having at least one slot formed in the exterior surface; a bracket slot formed in the damper proximate the aft end, the bracket slot configured to receive the tab; and the fan case liner comprising a fan case liner receiver configured to receive the damper, wherein the retention bracket and damper support the fan case liner.

Compliant dampening wedge mount

A rotor assembly is provided that includes a rotor disk, a rotor blade and a rotor spacer. The rotor disk includes a slot. The rotor blade includes a blade root arranged within the slot. The root spacer is arranged within the slot between the rotor disk and the blade root. The root spacer is configured as or otherwise includes a cellular structure with a plurality of internal cells.

Deformable root spacer for a gas turbine engine rotor blade

A gas turbine engine component includes a tubular body section including a plurality of fiber wraps encompassed within a matrix composition and one or more integrally-formed stiffeners extending from an outer surface of the body section and in a component circumferential direction around the body section. The stiffener includes one or more fiber wraps extending radially outwardly from the body section over a form and to the body section from the form.

Integral stiffening rail for braided composite gas turbine engine component

Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

Plated polymer fan

Plated polymer nosecone

A method of fabricating a fan case for a gas turbine engine defines a metallic ring including an outer surface and an inner surface. A first composite material is assembled about the outer surface of the metallic ring. A second composite material is assembled about the first composite material. The first composite material and the second material are cured about the metallic ring within a tool to form a first subassembly. The first subassembly is removed from the tool. A fan case assembly for a gas turbine engine and a gas turbine engine are also disclosed.

Co-molded metallic fan case containment ring

A fan case for a gas turbine engine includes an annular liner and an annular case body. The liner has a plurality of liner fiber layers. The case body surrounds the liner. The case body includes a plurality of first and second fiber layers. The first fiber layers extend axially beyond the second fiber layers in axially forward and aft directions and the second fiber layers are interleaved with the first fiber layers. The first fiber layers each have a first fiber architecture and the second fiber layers each have a second, different fiber architecture.

Fan case with interleaved layers

A fan rotor includes a fan hub and a plurality of fan blades extending radially outwardly from the fan hub. Platforms are positioned intermediate blade sides of adjacent ones of the fan blades. Seals are positioned between the blade sides and platform sides of the platform seals. The seals have an elongated bonding area bonded to one of the platform sides and the fan blade sides. The seal extends radially outwardly from the elongated bonding area to a wedge portion. A gas turbine engine and a seal are also disclosed.

Fan platform wedge seal

A gas turbine engine fan case may comprise a plurality of wound layers that form a laminate and have a nominal radial fan case thickness, where the laminate includes a plurality of discrete fan case radial locations comprising a plurality of radially stacked composite plies that form a radial integral build up in comparison to the nominal radial fan case thickness.

Integrally built up composite fan case

A reinforced component in accordance with various embodiments includes a metal lug configured to be attached to a secondary component. The reinforced component further includes a composite material integrally formed around the metal lug and configured to be retained in place relative to the secondary component via an attachment between the metal lug and the secondary component.

Composite fan platform lug reinforcement

A gas turbine engine is provided. The gas turbine engine comprising: a fan section having a fan; and a containment zone encircling the fan, the containment zone comprising: a ballistic liner composed of a plurality of ring segments located radially outward of the fan; wherein each of the plurality of ring segments include two opposing circumferential ends, and wherein the plurality of ring segments are arranged circumferentially around the fan section and the circumferential ends of each of the plurality of ring segments meet at joints to form the ballistic liner.

Ballistic liner install methods

A fan assembly of a gas turbine engine, a method for fabricating a fan assembly for a gas turbine engine, and a gas turbine engine are disclosed. The fan assembly of the gas turbine engine may include a spinner section, a fan hub section aft of the spinner section, and a joint therebetween. The fan assembly may further include a support ring for internally supporting the spinner, the support ring including a first portion facing the fan hub and a second portion connected to the spinner at the joint, wherein the connection between the second portion and the joint is a bonded connection.

Bonded mount ring spinner

A spinner for a gas turbine engine is disclosed. The spinner may include a body extending between a first and second end comprised of a cured chopped unidirectional fiber pre-impregnated material. The body may have a generally conical shape and may further be plated with a metal or metal alloy.

Gas turbine engine spinner

Growing community of inventors

Middletown, CT, United States of America

Colin J Kling