Rtx Corporation

United Technologies Corporation

Raytheon Technologies Corporation

Hamilton Sundstrand Corporation

Zhongtao Dai

San Quach

Lance L Smith

Jeffrey Mark Cohen

Kristin Kopp-Vaughan

Gregory Boardman

Catalin G Fotache

Justin M Locke

Timothy S Snyder

Steven D Porter

Stephen Karl Kramer

Ram Ranjan

Donald J Hautman

Robert H Dold

Wookyung Kim

Randolph J Smith

Baris A Sen

James B Hoke

Andrzej Ernest Kuczek

Matthew Robert Pearson

Peter A T Cocks

Lexia Kironn

Russell B Hanson

Dustin Wayne Davis

Dave J Hyland

Randal G McKinney

Richard Sterling Tuthill

Kathryn L Kirsch

Kevin E Green

Jeremy Styborski

Corneil S Paauwe

Won-Wook Kim

Caroline Karanian

Jeffrey M Cohen

Adam Takashi Holley

Eva Wong

Lauryn M Curtis

Richard S Tuthill

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a fuel injector nozzle extending axially along an axis to a nozzle tip. The fuel injector nozzle includes an inner fuel passage and an outer fuel passage. The inner fuel passage extends axially within the fuel injector nozzle to an inner passage outlet at the nozzle tip. The inner passage outlet is formed by an inner divergent surface. The inner divergent surface is angularly offset from the axis by a first acute angle. The outer fuel passage extends axially within the fuel injector nozzle to an annular outer passage outlet at the nozzle tip. The annular outer passage outlet is formed by an outer divergent surface. The outer divergent surface is angularly offset from the axis by a second acute angle that is greater than the first acute angle.

Turbine engine fuel injector assembly with annular fuel outlet

An assembly is provided for a turbine engine. This assembly includes a turbine vane array and a cooling system. The turbine vane array includes an inner platform, an outer platform and a plurality of turbine vanes extending between and connected to the inner platform and the outer platform. The turbine vanes include a first turbine vane, and the first turbine vane includes a first passage and a second passage. The cooling system is configured to direct a first fluid into the first passage and a second fluid into the second passage. The first fluid includes air and steam during a first mode. The second fluid includes the air without the steam during the first mode.

Steam cooling turbine stator vane array

A fuel injector assembly for a gas turbine engine includes a swirler and a fuel nozzle. The swirler has an outer wall having a SOW inner wall surface, an inner wall having a SIW inner wall surface and a SIW outer wall surface, an outer passage, and an inner passage. The SIW inner wall surface includes first and second sections. The first section extends between a first airflow inlet and the second section, and the second section extends between the first section and an inner wall distal end. The first section tapers radially inward, and the second section extends parallel the center axis. The outer wall circumscribes the inner wall and extends axially along the center axis to a distal outer wall end, and the distal end wall is axially recessed within the swirler from the distal outer wall end. The fuel nozzle projects into the inner passage.

High shear swirler for gas turbine engine

A fuel nozzle for a gas turbine engine combustor includes a fuel nozzle assembly including an inflow tube disposed along and a nozzle axis, the inflow tube defining an inner air passage and a liquid swirler concentrically disposed about the inflow tube. The liquid swirler includes a liquid swirler inner wall, a liquid swirler outer wall having a liquid swirler outer wall end portion at a downstream-most position and angled radially inward toward the nozzle axis, and an annular liquid passage defined therebetween. The fuel nozzle assembly further includes a radial air swirler (RAS) concentrically disposed about the liquid swirler outer wall, the RAS including an RAS inner wall, an RAS outer wall having an end cap at a downstream-most position, and an annular gas passage defined therebetween. The end cap has a radiused inner surface and a contoured outer surface. The fuel nozzle assembly further includes a guide swirler disposed concentrically about the RAS outer wall, the guide swirler comprising an annular air passage angled radially inward toward the nozzle axis.

Fuel nozzle for hydrogen-based fuel operation

A combustor for a rotating detonation engine includes a radially outer wall extending along an axis (A); a radially inner wall extending along the axis (A), wherein the radially inner wall is positioned within the radially outer wall to define an annular detonation chamber having an inlet for fuel and oxidant and an outlet; a first passage for feeding at least one of the fuel and the oxidant along a first passage axis (a) to the inlet; a second passage for feeding at least one of the fuel and the oxidant along a second passage axis (a) to the inlet, wherein the second passage axis is arranged at an angle (α) relative to the first passage axis whereby mixing of flow from the first passage and the second passage is induced.

Turbulence generator mixer for rotating detonation engine

A fuel nozzle for a gas turbine engine combustor includes a fuel nozzle assembly including an inflow tube disposed along and a nozzle axis, the inflow tube defining an inner air passage and a liquid swirler concentrically disposed about the inflow tube, the liquid swirler including a liquid swirler inner wall having a liquid swirler inner wall end portion angled radially outward from the nozzle axis, a liquid swirler outer wall having a liquid swirler outer wall end portion angled radially outward from the nozzle axis, and an annular liquid passage defined therebetween. The fuel nozzle assembly further includes a radial air swirler (RAS) concentrically disposed about the liquid swirler outer wall, the RAS including an RAS inner wall having an RAS inner wall end portion angled radially inward toward the nozzle axis, an RAS outer wall having an end cap at a downstream-most position, and an annular gas passage defined therebetween. The end cap includes a radiused inner surface and a contoured outer surface, and the radiused inner surface is parallel to the RAS inner wall end portion.

An assembly is provided for a turbine engine. This turbine engine assembly includes a fuel injector assembly, and the fuel injector assembly includes an inner air swirler and a fuel swirler. The inner air swirler is configured to swirl inner air in a direction about an axis to provide inner swirled air. The fuel injector assembly is configured to inject the inner swirled air as an inner air flow along an inner air flow trajectory parallel with the axis. The fuel swirler is configured to swirl fuel in the direction about the axis to provide swirled fuel. The fuel injector assembly is configured to inject the swirled fuel as an annular fuel flow along a fuel flow trajectory parallel with the axis. The annular fuel flow is adjacent and circumscribes the inner air flow.

Fuel injector assembly for gas turbine engine

A fuel nozzle for a gas turbine engine combustor includes a fuel nozzle assembly including an inflow tube disposed along and a nozzle axis, the inflow tube defining an inner air passage, and a liquid swirler concentrically disposed about the inflow tube, the liquid swirler including a liquid swirler inner wall, liquid swirler outer wall having a liquid swirler outer wall end portion angled radially inward toward the nozzle axis, and an annular liquid passage defined therebetween. The fuel nozzle assembly further includes a radial air swirler (RAS) concentrically disposed about the liquid swirler outer wall, the RAS including an RAS inner wall having an RAS inner wall end portion angled radially inward toward the nozzle axis such that it is parallel to the liquid swirler outer wall end portion, an RAS outer wall having an end cap at a downstream-most position, and an annular gas passage defined therebetween. The end cap includes a radiused inner surface and an outer surface.

An assembly is provided for a turbine engine. This assembly includes a housing, a combustor and a fuel injector assembly. The housing includes a case and a diffuser plenum radially within the case. The case extends axially along and circumferentially about a centerline. The combustor is disposed within the diffuser plenum. The combustor includes a bulkhead, a hood, a combustion chamber and a hood cavity. The bulkhead is axially between the combustion chamber and the hood cavity. The hood is between the hood cavity and the diffuser plenum. The fuel injector assembly projects radially into the diffuser plenum from the case. The fuel injector assembly includes a fuel nozzle and a steam nozzle. The fuel nozzle is configured to inject fuel into the combustion chamber. The steam nozzle is configured to inject steam into the hood cavity.

Injecting steam into hood cavity of turbine engine combustor

A ram air fan inlet assembly for cabin air compressor (CAC) motor cooling flow enhancement includes a gas path defined by a ram air duct and a fan section, a CAC motor cooling return duct having an outlet provided through a wall of the ram air duct, and a centerbody body disposed in the ram air duct. The fan section is disposed immediately downstream and abutting the ram air duct. The ram air duct and fan section share a common axis. The centerbody is disposed about the common axis and configured to reduce of volume of the gas flow path in the ram air duct. The centerbody and the outlet axially overlap.

Centerbody insertion for improved CAC motor cooling

An assembly is provided for a turbine engine. This assembly includes a housing, a combustor and a steam injector. The housing includes an air plenum. The combustor is disposed within the air plenum. The combustor includes a combustor wall and a combustion chamber. The combustor wall is disposed between the combustion chamber and the air plenum. The combustor wall includes a quench aperture that extends through the combustor wall from the air plenum to the combustion chamber. The steam injector projects partially into or through the quench aperture.

Introducing steam with quench air into turbine engine combustor

An assembly is provided for a turbine engine. This assembly includes a housing, a combustor and a steam system. The housing includes an air plenum. The combustor is disposed within the air plenum. The combustor includes a combustion chamber and a combustor wall between the combustion chamber and the air plenum. The steam system includes a steam injector arranged within the air plenum next to the combustor wall. The steam system is configured to inject steam out of the steam injector and into the air plenum to impinge against the combustor wall.

Steam cooling turbine engine combustor wall

An assembly is provided for a turbine engine. This assembly includes a fuel injector assembly, and the fuel injector assembly includes a fuel passage, an air passage and a steam passage. The fuel injector assembly is configured to direct fuel out of the fuel passage along an axis into a volume as a fuel flow. The fuel injector assembly is configured to direct air out of the air passage along the axis into the volume as an air flow, where the air flow circumscribes the fuel flow. The fuel injector assembly is configured to direct steam out of the steam passage along the axis into the volume as a steam flow, where the steam flow circumscribes the fuel flow and provides a radial buffer between the fuel flow and the air flow.

Fuel injector assembly for gas turbine engine with fuel, air and steam injection

A turbine rotor includes a base and a plurality of blades. A central nose is radially inward of the blades and defines an axis of rotation. A plurality of cooling manifolds is disposed within the turbine rotor and includes impingement cooling jets extending through a rear surface of the turbine rotor. An internal cooling manifold extends radially inward of the impingement cooling jets and extends between the base and the rear surface of the turbine rotor. A central nose cooling manifold extends into the central nose and is fluidically connected to the internal cooling manifold. A base cooling manifold is fluidically connected to the central nose manifold and extends radially outward from the central nose cooling manifold. A blade cooling manifold is fluidically connected to the base cooling manifold and extends within the blade. Trailing edge jets extend from the blade cooling manifold and through the trailing edge of blades.

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Glastonbury, CT, United States of America

Zhongtao Dai