Raytheon Technologies Corporation

United Technologies Corporation

Benjamin Bellows

Tracy A Propheter-Hinckley

Brandon W Spangler

James B Hoke

Steven Bruce Gautschi

Ricardo Trindade

Dustin Wayne Davis

Trevor Rudy

Mark F Zelesky

Stephen Karl Kramer

Dennis M Moura

Atul Kohli

David J Hyland

Daniel Bernard Kupratis

Christopher J Hanlon

Dave J Hyland

Jeffery A Lovett

Walter A Ledwith

William F Schneider

Robert H Bush

Sean Danby

Tracy A Propheter-Hinkley

A gas turbine engine includes a core flowpath for flowing a core stream, a second flowpath located radially outward from the core flowpath for flowing a second stream, and an auxiliary flowpath located radially outward from the second flowpath for flowing an auxiliary stream. A heat exchanging device is constructed and arranged to divert a portion of the second stream into the auxiliary flowpath. A turbine exhaust case is constructed and arranged to flow the auxiliary stream into the core flowpath for mixing with the core stream.

Gas turbine engine and an airflow control system

A combustor for a gas turbine engine includes a combustor shell having a shell opening therethrough, a combustor panel having a stud attached thereto, the stud extending through the shell opening. The stud includes a standoff to define an intermediate passage between the combustor shell and the combustor panel. A retainer is attached to the stud. A washer surrounds the stud and is positioned between the retainer and the combustor shell. The washer at least partially defines a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff.

Washer for combustor assembly

A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.

Cooling configurations for combustor attachment features

A fuel injection system for a gas turbine engine includes a fuel nozzle with a fuel injection aperture to inject a fuel jet and a multiple of airflow passages in the fuel nozzle to communicate a multiple of air streams to interact with the fuel jet.

Cavity swirl fuel injector for an augmentor section of a gas turbine engine

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Glastonbury, CT, United States of America

Benjamin Bellows