United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

David R Lyders

Phillip Alexander

Colin J Kling

George Alan Salisbury

Peter Karkos

Kevin M Bell

Matthew E Bintz

James T Roach

James Olaf Hansen

Darin S Lussier

John Henry Vontell, Sr

Christopher J Hertel

Carl Brian Klinetob

Michael Parkin

Fadi S Maalouf

Andrew Pope

Xiaomei Fang

Nicholas D Stilin

Peter T Schutte

Jordan J Franklin

Frank J Euvino, Jr

Calvin Jay Winder

Hamidreza Mohseni

Chong H Park

Matthew R Zsunkan

Pieter Van Lieu

Marc E Holyfiield

C Brian Klinetob

Christopher Avery

Daniel A Rodrigues

Justin Roger DeLarm

Anna Lauren Wright

Marc E Holyfield

Brian C Klinetob

Phillip Alexander Emerson

A gas turbine engine includes a rotor that that has a seal surface, a shaft that has an annular seal channel that opens to the seal surface, and a seal disposed in the annular seal channel for sealing against the seal surface. The seal is made of a composite having carbon fibers disposed in a carbon matrix.

Gas turbine engine with carbon/carbon composite piston seal

A fan blade platform seal includes a platform portion including a first side and a second side opposite the first side. The platform portion further includes a flow path surface extending between the first side and the second side and a bonding surface opposite the flow path surface. The fan blade platform seal further includes a first seal portion including a first bonding segment including a first outer surface, mounted to the platform portion on the first side of the platform portion, and a first inner surface opposite the first outer surface. The fan blade platform seal further includes a stiffening portion mounted to the first inner surface. The stiffening portion includes a first bonding layer bonded to the first inner surface and a stiffening layer bonded to the first bonding layer on a first layer side of the stiffening layer.

Fan blade platform seal and method for forming same

An inspection feature for an adhesive bond portion between parts of a component comprising the inspection feature extending from a surface of the part of the component a predetermined bond line thickness, the inspection feature having a density configured to imitate a defect of the adhesive bond portion responsive to a non-destructive inspection scan.

Comolded non-destructive inspection standard functioning as a bond bump

A platform for a gas turbine engine according to an example of the present disclosure includes, among other things, a platform body that has a gas path surface extending axially between a leading edge and a trailing edge and extending circumferentially between opposed mate faces. A plurality of platform flanges extend from the platform body to define one or more slots. The one or more slots are dimensioned to receive a respective flange of a rotatable hub, and each platform flange has a retention member dimensioned to receive a retention pin to mount the platform body. The platform body includes a composite wrap extending about a perimeter of the platform body to define an internal cavity. At least one honeycomb core has a plurality of cells that is disposed in the internal cavity.

Composite gas turbine engine component

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 grounding clip for an organic matrix composite guide vane with a metallic sheath comprises the organic matrix composite guide vane includes a body having a leading edge and a trailing edge opposite the leading edge and a root end extending between the leading end edge and the trailing edge. The metallic sheath is attached proximate the leading edge and extends to the root end. A metallic attachment fitting has a receiver configured to receive the root end of the organic matrix composite guide vane for coupling the organic matrix composite guide vane to the metallic attachment fitting. The grounding clip is coupled to the sheath proximate the root end; wherein the grounding clip is electrically connected to the metallic attachment fitting and the metallic sheath.

Grounding clip for bonded vanes

A method of forming a circuit in a composite component includes providing a plurality of preform modules comprised of an organic matrix composite material, applying at least one electrical circuit on at least first and second preform modules of the plurality of preform modules, and arranging the first and second preform modules such that the electrical circuit of the first preform module is in contact with the electrical circuit of the second preform module. An additional step includes molding the first and second preform modules together to form a one-piece molded component such that the electrical circuits of the first and second preform modules form a complete circuit.

Method to integrate multiple electric circuits into organic matrix composite

An airfoil for a gas turbine engine includes a substrate and a sheath providing an edge. A cured adhesive secures the sheath to the substrate. The cured adhesive has a fillet that extends beyond the edge that includes a mechanically worked finished surface. A method of manufacturing the airfoil includes the steps of securing a sheath to a substrate with adhesive, curing the adhesive, and mechanically removing a portion of the adhesive extending beyond the sheath.

Fan blade and method of manufacturing same

An inner platform structure of a stator vane for a gas turbine engine includes a male circumferential side opposite a female circumferential side, the male circumferential side includes a male wall received at least partially within a female wall of a neighboring stator vane at an interface with a pad at the interface.

Stator assembly with pad interface for a gas turbine engine

A vane includes a platform with a fixture overmolded by a sheath.

Overmolded vane platform

An electrical probe assembly includes a flexible circuit. A plurality of electrically conductive regions is on a first side of the flexible circuit. The flexible circuit is arranged about an axis formed by rolling the flexible circuit such that the electrically conductive regions form a plurality of isolated electrically conductive bands.

Electrical probe assembly

Gas turbine engine systems involving fairings with locating data are provided. In this regard, a representative a fairing assembly for a gas turbine engine includes: a first locating component having a leading edge, first and second sides extending from the leading edge, and a recess oriented parallel to the leading edge, the recess having a first datum surface, the first locating component being operative to be positioned between a portion of a strut and a portion of an interior surface of a fairing sheath such that the first datum surface establishes a desired orientation of the fairing sheath relative to the strut.

Gas turbine engine systems involving fairings with locating data

A connector for incorporation into a heater system for inlet struts includes a body having a tapered forward end and an opposite rear end. A plurality of forward electrical terminals are formed on the outer surface of the tapered end. A plurality of rearward electrical terminals are formed on the rear end of the body. The rearward electrical terminals are in electrical connection with the forward electrical terminals. The forward electrical terminals on the tapered end are in electrical contact with a plurality of electrical contacts connected to heating elements formed in a heating mat. The heating mat entirely envelops the connector. The heater mat is formed within a substantially rigid outer shell.

Connector for heater

A composite fairing with embedded heating architecture for ice protection includes heating elements arranged on various fairing plies for heating substantially all of the composite fairing. The heating elements are positioned to provide ice protection to substantial portions of the external surface of the composite fairing. Junctions, busbars, and plated through holes are used for delivering electric current to the heating elements on the various fairing plies.

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Middletown, CT, United States of America

David R Lyders