United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

David A Knaul

Anthony R Bifulco

David A Topol

Fadi S Maalouf

Michael Raymond LaFavor

Michael Espinoza

Daniel K Van Ness

Christopher L Potter

Scott J Augustine

Seung-Woo Choi

Orenthral T Morgan

Disclosed is an acoustic liner for a gas turbine engine, having: a face sheet; a first plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the first plurality of resonator chamber cavities defining a first aggregated volume that is configured to target noise attenuation at a first frequency, the first plurality of resonator chamber cavities include first and second resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other; and a second plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the second plurality of resonator chamber cavities define a second aggregated volume that differs from the first aggregated volume and is configured to target noise attenuation at a second frequency, the second plurality of resonator chamber cavities include third and fourth resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other.

Acoustic liner with non-uniform volumetric distribution

A component of a rotor system is provided and includes a disk and a reinforcing ring. The disk includes an airfoil element, a web extending radially inwardly from the airfoil element and an arm element extending axially from the web. The reinforcing ring is formed of fiber reinforced materials and is disposed to fit about the arm element.

Composite reinforced rotor

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 mount interface between two rotating gas turbine engine components includes a rigid ring to provide radial deflection restraint. In one example, the rigid ring is comprised of a metal matrix composite material.

Hoop snap spacer

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Glastonbury, CT, United States of America

David A Knaul