United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Gary J Dillard

George P Liang

Stephen Karl Kramer

Michael Joseph Murphy

Albert K Cheung

Russell B Hanson

Sean P Zamora

Timothy J McAlice

Assaf Farah

Gonzalo F Martinez

George W Beal

Dibesh D Joshi

Glenn R Estes

Salvatore D'Alessandro

Salvatore D'ALESSANDRO

An assembly for a combustor for a gas turbine engine, including: a plurality of heat shield panels attached to at least one combustor liner, each one of the plurality of heat shield panels including a panel portion and a first forward rail and a second rearward rail each extending from an outer surface of the panel portion, the panel portion including an inner surface opposite of the outer surface, the panel portion also includes a forward end and a rearward end, the forward end of the panel portion is axially forward of the rearward end of an adjacent heat shield panel of the plurality of heat shield panels such that a gap is defined between the outer surface of the panel portion of one heat shield panel of the plurality of heat shield panels and an inner surface of the panel portion of an adjacent heat shield panel of the plurality of heat shield panels, the panel portion also includes a plurality of apertures extending from the outer surface to the inner surface; and a plurality of cooling pins extending upwardly and away from the outer surface towards a surface of the at least one combustor liner.

Reinforced film floatwall for a gas turbine engine

A combustor liner assembly includes a first liner panel that has a first forward end and a first aft end. A second liner panel has a second forward end and a second aft end. A support band has a plurality of circumferentially spaced holes. The support band is arranged between the first liner panel and the second liner panel. The support band has a protrusion with a first angled surface and a second angled surface. The first angled surface is in engagement with the first aft end and the second angled surface in engagement with the second forward end.

CMC combustor panel attachment arrangement

A combustor for use in a gas turbine engine comprising: an outward shell; an inward shell located radially inward of the outward shell, the inward shell and the outward shell defining a combustion chamber therebetween; an aft outward panel located proximate the outward shell, the aft outward panel extending from an aft end of the combustion chamber to an outward panel joint; an aft inward panel located proximate the inward shell, the aft inward panel extending from the aft end of the combustion chamber to an inward panel joint; and a forward panel located proximate a forward end of the combustion chamber, the forward panel comprising: an outward wall located proximate the outward shell; an inward wall located proximate the inward shell; and a forward wall located proximate the forward end of the combustion chamber, the forward wall extending from the inward wall to the outward wall.

Slot cooled combustor

A heat shield panel for use in a combustor of a gas turbine engine is disclosed. In various embodiments, the heat shield panel includes an inner base layer, an outer base layer, and a grommet having a flange disposed between the inner base layer and the outer base layer.

Method for fabricating dilution holes in ceramic matrix composite combustor panels

A pre-diffuser fairing for a gas turbine engine is disclosed. In various embodiments, the pre-diffuser fairing includes a first side wall, a first radially inward portion and a first radially outward portion and a second side wall, a second radially inward portion and a second radially outward portion. The first side wall and the second side wall are spaced apart to form a cavity configured to receive a strut.

Thermally isolated combustor pre-diffuser

A combustor panel for use in a gas turbine engine includes a body portion having an outwardly curved edge defining a channel between the body portion and the outwardly curved edge. The outwardly curved edge includes a plurality of slots. The panel further includes a fastening member having a base disposed within the channel and a plurality of fasteners extending from the base and disposed within the slots.

Attachment for high temperature CMC combustor panels

A seal assembly is provided for a gas turbine engine. This seal assembly includes a tadpole seal with a bulb and a tail, where the tail is directed toward a backwall. The seal assembly also includes a faying extension that at least partially extends into the channel and into contact with the bulb. An exhaust duct is also provided for a gas turbine engine. This exhaust duct includes a seal assembly between a first exhaust duct section and a second exhaust duct section. The seal assembly includes a tadpole seal with a bulb and a tail, where the tail is directed upstream.

Large displacement high temperature seal

A brazed end cover assembly for a gas turbine combustor using Au&#x2014;Ni braze is disclosed. The end cover assembly may include an end cover with openings, a flow insert, first and second gaps between the end cover and the flow insert, and first and second braze joints formed at the first and second gaps, wherein the braze materials used comprises Au and Ni. A method of brazing a flow insert into an end cover is also disclosed. The method may include providing an end cover and a flow insert with first and second gaps therebetween; applying a braze material to an outer surface of the flow insert, wherein the braze material comprises Au and Ni; inserting the flow insert into the end cover; heating the assembly to a brazing temperature for some time; and cooling the resulting brazed assembly to room temperature.

Gas turbine fuel nozzle end cover using Au&#x2014;Ni braze and method producing same

An example gas turbine engine includes an engine casing and an engine liner within the engine casing. One of the engine casing or the engine liner includes a first attachment structure. The other of the engine casing or the engine liner defines a track guide. A slideable member is moveable within the track guide between an engaged position and a disengaged position. The slideable member includes a second attachment structure engageable with the first attachment structure to secure the engine liner relative the engine casing when the slideable member is in the engaged position.

Slideable liner anchoring assembly

A nozzle assembly for a turbine engine has a convergent portion for converging fluid flow from a turbine engine core. A divergent portion for diverging fluid flow from the turbine engine core is in fluid communication with the convergent portion. A conduit is in communication with a bypass fluid flow. The conduit has a thrust vectoring port located near the divergent portion.

Nozzle assembly with flow conduits

An exhaust liner assembly for a gas turbine engine contains a unitary liner sheet and an impingement sheet, which contain holes for cooling air to enter chambers that are defined by chemically milled areas in the liner. The chambers are in an isogrid pattern, with the chambers having a polygon shape defined by walls that are left after the liner is milled. The walls intersect at nodes and fasteners are attached to the nodes to attach the impingement sheet to the liner.

Gas turbine exhaust liner with milled air chambers

A turbofan engine uses fan air to cool bounding surfaces of the exhaust duct at all times. A portion of the fan air flow is used for augmentor combustion in the augmentation mode. In the non-augmented mode the flow for combustion is stopped and the cooling air is used to cool the tail cone and exit guide vanes. Infrared radiation is thereby reduced when non-augmented.

Growing community of inventors

Gainesville, FL, United States of America

Gary J Dillard