Raytheon Technologies Corporation

Rtx Corporation

United Technologies Corporation

Rebecca R Dunnigan

Corey D Anderson

Billie W Bunting

Randall Lee Greenberg

Edward Boucher

Javier Nebero Johnson

Nicholas Broulidakis

Sushruth G Kamath

Eric G Leamon

Kyra A Thole-Wilson

Manuel A Casares Rivas

Daniel R Brandt

Matthew Murakami

Konrad Kuc

Ted Guevel

Victoria M Imlach

Gary D Roberge

Curtis C Cowan

Mark W Colebrook

Edward Guevel

Adam Castles

Austin R O'Mara

Edmond Cheung

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

A cooling system for a gas turbine engine may comprise a plenum extending circumferentially around an outer engine case structure. The plenum may comprise a supply conduit and a return conduit. The supply conduit and the return conduit may be in fluid communication with a heat exchanger. The heat exchanger may be disposed between the outer engine case structure and an inner engine case structure. The plenum may be configured to provide enhance heat transfer for the cooling system.

Heat exchanger supply plenum

A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a base member having a first side configured to mate with a casing and a second side opposite the first side, an annular ring configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, a first O-ring disposed between the annular ring and the fluid transfer tube, a second O-ring disposed between the base member and the annular ring, and an attachment ring configured to secure the annular ring and the base member to the casing.

Sealing configuration to reduce air leakage

A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a base member having a first side configured to mate with a casing and a second side opposite the first side, a housing configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, a bellows surrounding the fluid transfer tube and positioned between the housing and the casing, and a wear ring disposed between the housing and the bellows.

An airflow deflector is provided that includes at least one liner attachment flange, a deflector panel, and at least one deflector leg. The at least one liner attachment flange has a liner side surface and an opposing outer surface. The at least one deflector leg extends between and is attached to the at least one liner attachment flange. The at least one deflector leg extends a distance between the deflector panel and the liner attachment flange to maintain the deflector panel a separation distance from the liner attachment flange. The airflow deflector is configured for insertion of the at least one deflector leg and the deflector panel within a liner aperture.

Airflow deflector and assembly

Growing community of inventors

Sturbridge, MA, United States of America

Rebecca R Dunnigan