United Technologies Corporation

Roland R Barnes

Cagdas Yilmaz

Phillip Alexander

Daniel Benjamin

John T Pickens

Peter T Schutte

An integrally bladed disk includes a rotor disk and circumferentially spaced first and second blades. The rotor disk has a rim the periphery of which forms a flow surface. The first and second blades extend integrally outward from the rim. The rim defines a trench in the flow surface between the first and second blades aft of a leading edge of the rim. The trench extends axially forward and rearward of a leading edge of the first blade.

Turbofan flow path trenches

An integrally bladed rotor is utilized in at least a stage of one of a compressor and turbine section. Airfoils extend radially outwardly from a platform, and there is an undercut inward from the platform at a downstream edge of the airfoil.

Gas turbine engine rotor sections held together by tie shaft, and with blade rim undercut

An integrally bladed disk includes a rim and blades. The blades are circumferentially spaced and extend integrally outward from the rim to define a flow path therebetween. The periphery of the rim forms a flow surface and includes a trench that is disposed adjacent the blades.

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.

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Bloomfield, CT, United States of America

Roland R Barnes