United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Derk S Philippona

Steven Wayne Burd

Jeffery A Lovett

Jeffrey Mark Cohen

Meredith Bright Colket, Iii

Scott A Liljenberg

Donald J Hautman

Andrzej Banaszuk

Christopher R Brdar

Thomas R Clements

Christopher M Pater

Robert J Sayers

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

A method for providing thermo-acoustic coupling of a gas turbine engine augmentor includes determining acoustic resonances and heat release phase relationships associated with the augmentor. A fuel injector of the augmentor is positioned at an axial position relative to a flame holder of the augmentor in response to the determined acoustic resonances and heat release phase relationships associated with the augmentor. Heat release and acoustic pressure oscillation cycles associated with the augmentor are out of phase by at least approximately 100 degrees.

Systems and methods involving reduced thermo-acoustic coupling of gas turbine engine augmentors

An assembly may comprise a first part including a first surface, and a second part including a second surface and a bottom edge having sloped regions and at least one well between the sloped regions. The assembly may further comprise a brazed joint joining the first surface to the second surface. The at least one well may be configured to collect excess braze material from the brazed joint.

Assemblies with brazed joints and methods of fabricating assemblies with brazed joints

A flameholder for an augmentor rotates about an axis radially positioned with a turbine engine. The flameholder is in a streamlined position when the augmentor is not operating to minimize pressure loss and radar cross-section and a turbulent position when the augmentor is operating. A linkage connects the flameholder to an actuator to control the rotational position of the flameholder on the axis. Bypass airflow from the fan cools the flameholders and linkages. The length of the linkages can be varied from one flameholder to another to create asymmetric heat release within the augmentor to avoid screech.

Augmentor variable vane flame stabilization

An augmentor system minimizes acoustic pressure fluctuations on the heat release process within the augmentor by staggering the vanes therein. The alternating axial vane stagger pattern arranges the downstream set of vanes as baffles which prevent the propagation of tangential acoustic waves between the vanes to protect the upstream set of vanes from the effects of transverse acoustic velocity fluctuations which minimizes screech without substantially affecting augmentor performance.

Augmentor with axially displaced vane system

A bypass air valve is provided comprising a liner, a strap, and apparatus for selectively actuating the valve. The liner includes an inner surface, an outer surface, a plurality of first regions, and a plurality of second regions. Each first region includes a plurality of first apertures. The strap includes a plurality of openings and a plurality of third regions. The third regions include a plurality of second apertures. The valve may be selectively actuated into an open position where the first regions are in communication with the openings, and the third regions are in communication with the second regions. The valve may be selectively actuated into a closed position where the first regions are in communication with the third regions, and the second regions are in communication with the openings. The flow path through the first and second apertures in the closed position impedes flow substantially more than the flow path through the first apertures and the openings in the open position, thereby effectively closing bypass air flow through the valve in the closed position.

Bypass air valve for a gas turbine

A method for distributing fuel within a gas turbine engine is provided. An augmentor is provided which includes a plurality of vanes. Each vane includes a pair of side walls, an aft wall, and a plurality of fuel apertures and pressurized gas apertures extending through the side walls. At least one of the pressurized gas apertures is positioned adjacent and forward of all fuel apertures at a particular position. At least one fuel distributor is provided in each vane. Fuel admitted into the fuel distributors flows into the core gas path in a direction substantially perpendicular to the core gas path. Gas admitted into the vanes at a pressure higher than that of the core gas flow, flows a distance into the core gas path in a direction substantially perpendicular to the core gas path. Fuel is selectively admitted into the fuel distributors when the augmentor is enabled. Pressurized gas entering the core gas path forward of the fuel creates a low velocity wake that enables the fuel to distribute circumferentially.

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Tolland, CT, United States of America

Derk S Philippona