United Technologies Corporation

Raytheon Technologies Corporation

Christopher R Brdar

Timothy S Snyder

Steven Wayne Burd

John R Buey

Dennis M Moura

John S Tu

Andreas Sadil

Randal G McKinney

George F Titterton, Iii

Jaisukhlal V Chokshi

Derk S Philippona

Fernando K Grant

Bessem Jlidi

Kelly A Vanston

Leong Ma

Shakira A Ramos

Jodie L Herrmann

Matthew J Westergard

Timothy S Synder

A component for a gas turbine engine includes a substrate with a substrate aperture and a coating on the substrate that extends a length of the substrate aperture. A liner assembly for a gas turbine engine includes a hot sheet with a multiple of apertures and a coating on the hot sheet that extends a length of each of the multiple of apertures. A method of forming an aperture to provide film cooling in a component of a gas turbine engine, includes forming a multiple of substrate apertures in a substrate. Each of the multiple of substrate apertures defines a substrate inner periphery. A coating is applied on the substrate after forming the multiple of substrate apertures to define a coating inner periphery at least partially within each of the multiple of substrate apertures. The coating inner periphery is smaller than the substrate inner periphery.

Coated cooling passage

An augmentor for a gas turbine engine includes an augmentor spray bar with a spray bar outlet, and an augmentor spray bar tip. The spray bar tip includes a tip body, a tip bushing and a tip support strut. The tip body includes a first flow passage extending therethrough between a tip inlet and a tip outlet, wherein the tip inlet is connected to the spray bar outlet. The tip bushing includes a bushing bore. The tip body extends through the bushing bore defining a second flow passage between the tip body and the tip bushing. The tip support strut connects the tip body to the tip bushing across the second flow passage.

Augmentor spray bar with tip support bushing

A combustion duct for a gas turbine engine has a combustion liner to receive products of combustion, and deliver the products of combustion downstream toward a turbine rotor. An outer housing is positioned radially outwardly of the combustion liner. A flow sleeve is positioned radially intermediate the outer housing and the combustion liner. A chamber radially outwardly of the flow sleeve receives cooling air. A plurality of holes through the flow sleeve deliver cooling air from the chamber against an outer periphery of the combustion liner. A plurality of tabs are associated with at least some of the holes in the flow sleeve. The tabs are positioned to extend radially inwardly on a downstream side of the holes.

Flow sleeve with tabbed direct combustion liner cooling air

A gas turbine engine augmentor nozzle has an inlet for connection to an augmentor fuel conduit and an outlet for expelling a spray of fuel. A passageway between the inlet and outlet is at least partially bounded by outlet end surface portions diverging from each other. The nozzle may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline toward radial.

Augmentor pilot nozzle

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Rocky Hill, CT, United States of America

Christopher R Brdar