United Technologies Corporation

Hamilton Sundstrand Corporation

Phillip Alexander

Carl Brian Klinetob

John T Pickens

David R Lyders

Michael Parkin

Anthony R Bifulco

John Henry Vontell, Sr

Steven Clarkson

David A Welch

Rajiv A Naik

Kevin J Cummings

George Alan Salisbury

Brian P Huth

Roland R Barnes

Allan J Brockett

David O Kies

Joshua D Brumbaugh

A composite airfoil includes a core that has a three-dimensional network of fibers. The core defines an airfoil section and a root section. A composite skin covers a portion of the core excluding the root section.

Composite airfoil and turbine engine

A gas turbine engine fan assembly includes a rotor disk, a fan blade and a spacer. The rotor disk includes a longitudinally extending slot with a first spacer contact surface. The fan blade includes a root with a second spacer contact surface arranged within the slot. The spacer includes a leaf spring backbone and a compliant member. The leaf spring backbone includes one or more root contact segments connected longitudinally to one or more slot contact segments. A first of the root contact segments contacts the second spacer contact surface, and a first of the slot contact segments contacts the first spacer contact surface. The compliant member is radially between the first spacer contact surface and the first root contact segment, and radially between the second spacer contact surface and the first slot contact segment.

Energy absorbent fan blade spacer

The disclosed composite airfoil includes a three-dimensional composite core extending longitudinally and having a chord-wise direction. The core has a core in-plane thickness extending between opposing sides in a through-plane direction generally perpendicular to the chord-wise and longitudinal directions. A composite skin covers the opposing sides and has an exterior surface providing an airfoil contour. The skin includes a total skin in-plane thickness corresponding to a sum of thicknesses through the skin in the through-plane direction from each of the opposing sides to their adjoining exterior surface. A sum of the core in-plane and total skin in-plane thicknesses at a central portion of the composite airfoil is a total in-plane thickness. The total skin in-plane thickness at the central portion is less than 50% of the total in-plane thickness.

Gas turbine engine composite blade

Systems and methods for positioning fairing sheaths are provided. In this regard, a representative method includes using vacuum pressure to assist in moving opposing portions of a fairing sheath away from each other.

Systems and methods for positioning fairing sheaths of gas turbine engines

A sheath for a fan airfoil having a leading edge, a trailing edge, a tip, a root, a suction side and a pressure side includes a solid portion to wrap around the airfoil lead edge and over the airfoil tip and means for securing the solid portion to the airfoil.

Fan airfoil sheath

A device includes a resilient member having a first end for blocking an access hole and a second end for attachment to a support surface, an opening extending through the resilient member and located between the first and second ends, and a bolt connection location positioned at the second end of the resilient member. The first end of the resilient member blocks the access hole and can be deflected to provide tool access to the bolt connection location through the first opening.

Nosecone bolt access and aerodynamic leakage baffle

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 fairing removal tool and a method of using the tool provide for an improved method of removing a fairing from an engine inlet case. The fairing removal tool employs a hook and notch to engage the fairing and release the bonds joining the fairing to an inner structural element of the inlet case.

Fairing removal tool

An array of blades for use in an engine includes a disk having a slot, a pair of rails adjacent the slot and extending above an upper surface of the slot, and a pair of shoulders located outside the rails. A plurality of radially loaded blades are inserted into the slot. A plurality of snaps overhang the rails and rest on the shoulders. Each of the blades is positioned between a pair of snap seals and overlaps a side edge of each one of the pair of snap seals.

Method for loading and locking tangential rotor blades and blade design

An intermediate-manufactured composite airfoil includes first and second composite skins each having a plurality of fibers in a polymer matrix. A composite core is removably located between the first and second composite skins. The composite core includes a dry, three-dimensional, woven fiber network. The composite core may alternatively include a three-dimensional, woven fiber network in a fully cured polymer matrix.

Intermediate-manufactured composite airfoil and methods for manufacturing

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.

Heating architecture for a composite fairing

An attachment system for use with a variable incidence vane is disclosed. The attachment system includes a vane arm for joining a unison ring to a vane spindle. The vane arm has an arm portion and a bushing connected to the arm portion. The attachment system further has a pin for joining the vane arm to the unison ring. The pin fits within an interior bore in the bushing and is joined to the unison ring by a dual swage.

Variable vane arm/unison ring attachment system

A variable vane arm is disclosed having dual retention capability to ensure vanes of a gas turbine engine remain connected to the vane arm even under surge loads or when fastener preload, or the entire fastener, is lost. The variable vane arm further provides a surge slot to facilitate rotation of the vane even when the vane is operating under surge or otherwise excessively high pressure conditions.

Growing community of inventors

Colchester, CT, United States of America

Phillip Alexander