United Technologies Corporation

Rtx Corporation

Javier Nebero Johnson

Jorge I Farah

Eric Beach

Corey D Anderson

Edward Boucher

Rebecca R Dunnigan

Nicholas Broulidakis

Chris Bates

Sushruth G Kamath

Kyra A Thole-Wilson

Caleb N Cross

Manuel A Casares Rivas

Konrad Kuc

Victoria M Imlach

Eric G Leamon

Jeffery A Lovett

Jeffrey A Lovett

Daniel R Brandt

Matthew Murakami

Adam Castles

Edmond Cheung

Caleb Cross

A gas turbine engine including a core having a compressor section fluidly connected to a combustor via a primary flowpath and a turbine section connected to the combustor via the core flow path. An assembly is disposed within the gas turbine engine and includes a first part connected to a second part via a radial stack joint. The first part includes a radially inward facing surface contacting a corresponding radially outward facing surface of the second part. A fastener protrudes through the first part and the second part and is configured to maintain the relative positions of the first part and the second part. A channel is disposed on at least one of the radially inward facing surfaces and is positioned between the fastener and a circumferential edge of the first part. The channel is connected to at least one cooling air source.

Tongue joint including mating channel for cooling

An augmentor vane assembly of a gas turbine engine with an additively manufactured augmentor vane, the additively manufactured augmentor vane having a vane wall with integral longitudinal wall passages formed therein, at least one of the integral longitudinal wall passages including at least one entrance aperture and at least one exit aperture, the at least one exit aperture transverse to the integral longitudinal wall passage.

Augmentor vane assembly of a gas turbine engine with an additively manufactured augmentor vane

A gaspath component includes a flowpath body. A cooling plenum is disposed within the flowpath body. The cooling plenum includes a first region configured to receive a cooling flow and a second region configured to expel the cooling flow from the flowpath body. A metering obstruction is positioned between the first region and the second region and is configured to meter a flow of coolant through the cooling plenum.

Cooling system for a gaspath component of a gas powered turbine

An augmentor vane assembly includes an additively manufactured augmentor vane and a fuel line additively manufactured within the augmentor vane. A method of manufacture including additively manufacturing an augmentor vane having a wall that forms an internal volume therein; and additively manufacturing a fuel line within the augmentor vane that extends through the internal volume.

Additively manufactured augmentor vane of a gas turbine engine with additively manufactured fuel line extending therethrough

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East Hartford, CT, United States of America

Javier Nebero Johnson