United Technologies Corporation

Raytheon Technologies Corporation

Christopher L Potter

Michael Espinoza

Fadi S Maalouf

Eliannah Hunderfund

David A Knaul

Joseph Steele

Steven M Modon

An integrally bladed rotor includes a rotor that has a rim that provides an inner flow surface. Circumferentially spaced apart radially extending airfoils integrally with and from the rotor and joined by an airfoil fillet. An asymmetrical trench is provided in the rim between adjacent airfoils.

Gas turbine engine integrally bladed rotor with asymmetrical trench fillets

A rotating component for a turbine engine includes a main component portion including a web and a platform located at a radially outboard portion of the web, relative to an axis of rotation of the rotating component. A snap surface is located at the platform and is configured to interlock the rotating component with an adjacent rotating component. A transition surface extends from the main component portion to the snap surface and includes two or more different radii.

Rotor for gas turbine engine

The present disclosure includes airfoils for use in gas turbine engines. The airfoils comprise a fillet having a height of greater than 20% of the airfoil body span length. The airfoil may be a blade or a vane. Further, such airfoils may be used in the high pressure compressor section, as well as other gas turbine engine sections.

Airfoil fillet

An integrally bladed rotor includes a rim integral with a web that extends radially inward to a bore. The rim provides an end wall from which integral blades extend radially outward to a tip. The blades have an airfoil that extends in a chord-wise direction from a leading edge to a trailing edge. A fillet circumscribes the airfoil and joins the airfoil to the end wall. The fillet is at one of the leading edge and the trailing edge is truncated at least 50% in an axial direction to provide a face of the rim.

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East Hampton, CT, United States of America

Christopher L Potter