United Technologies Corporation

Rtx Corporation

Raytheon Technologies Corporation

Florida Turbine Technologies, Inc.

Jose R Paulino

Lawrence A Binek

Paul M Lutjen

Timothy M Davis

Sean R Jackson

Ken Francis Blaney

Mark John Rogers

Brandon W Spangler

Christopher W Strock

Dmitriy A Romanov

Charles H Warner

Neil L Tatman

Tracy A Propheter-Hinckley

Daniel L Gysling

Thomas E Clark

Timothy S Snyder

JinQuan Xu

Michael J Maloney

Steven Wayne Burd

Conway Chuong

Jonathan Jeffery Eastwood

William M Barker

Terence P Tyler

Kurt R Heinemann

Jeremy Drake

Adam Lee Hart

Brian Levy

Luis Miguel Ayalde

Richard K Hayford

Bruce L Morin

Edwin Otero

Ross Wilson

Joey Wong

Carson A Roy Thill

Brian Duguay

Daniel S Rogers

Mark David Ring

Scot Adams Webb

Christopher J Peters

Brian Richard Craig

Craig R McGarrah

Ramons Andris Reba

Anthony B Swift

Stephen A Morford

Anthony Van

Edward R Bareiss

Jason David Liles

Steven D Jenkel

Jaimie Schweitzer

Jeffrey M Wittman

Paul S Bean

Ramons A Reba

Esref Yaylagan

Steven R Chabot

Paul J Burgess

Patrick Scheelk

Chester D Blackman, Jr

Nicolas Bueno

Matthew S Dushek

Veronika Reynolds

Mark Rogers

Jinquan Xu

Terence P TYLERJr

Jr Terence P Tyler

An assembly is provided for a turbine engine. This assembly includes an engine structure, and the engine structure includes a plenum, a reverse flow combustor, a nozzle structure and a cooling circuit. The reverse flow combustor is disposed in the plenum and includes a combustion chamber. The nozzle structure is arranged at an outlet from the combustion chamber. The nozzle structure includes a first platform, a second platform and a plurality of vanes arranged circumferentially about an axis. The vanes extend across the flowpath from the first platform to the second platform. The cooling circuit extends in the first platform and between a circuit inlet into the cooling circuit and a circuit outlet from the cooling circuit. The circuit inlet is fluidly coupled with and disposed along the plenum. The circuit outlet is fluidly coupled with and disposed along the flowpath.

Cooling nozzle vanes of a turbine engine

An additively manufactured vane cluster has a platform, a shroud, and airfoils joining the platform to the shroud. The platform has openings, each opening between a respective two of the airfoils and forming accommodating differential thermal expansion of a leading end of the platform relative to a trailing end of the platform.

Additively manufactured turbine vane cluster

An aircraft propulsion system includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with fuel, and ignited to generate a gas flow that is expanded through a turbine section. A coolant is stored in a coolant chamber and is distributed to a location within the core flow path of the engine through a coolant flow regulator during engine operation.

Turbine engine with auxiliary coolant injection

An assembly is provided that includes a regulator manifold and a regulator element. The regulator manifold includes an inlet passage, a first outlet passage and a second outlet passage. The inlet passage is configured to receive bleed gas from a core flowpath. The regulator element is within the regulator manifold and configured to pivot to a first position, a second position and an intermediate position between the first position and the second position. The regulator element is configured to fluidly couple the inlet passage with the first outlet passage in the first position. The regulator element is configured to fluidly couple the inlet passage with the second outlet passage in the second position. The regulator element is configured to fluidly decouple the inlet passage from the first outlet passage and the second outlet passage in the intermediate position.

Aerial vehicle fluid control system with multi-way flow regulator

A method of manufacturing is provided. During this method, a body is formed using an additive manufacturing process. The body includes a shaft, a bladed rotor and a support structure. The shaft projects axially along an axis out from the bladed rotor. The support structure projects radially out from the shaft and axially to the bladed rotor. The support structure includes a plurality of channels arranged circumferentially about the axis. Each of the channels projects radially into the support structure towards the axis and to a respective channel side. Each of the channels projects axially into the support structure towards the bladed rotor and to a respective channel end.

Support structure for forming turbine engine rotating structure

An accessible debris separator for a gas turbine engine is provided. The accessible debris separator including a chamber formed by a entrance wall, an exit wall, an inner wall, and an outer wall; a plurality of inlet openings in the entrance wall; a plurality of outlet openings in the exit wall; and a component within the chamber, the component forcing cooling air with debris particulates entering the chamber via an inlet opening of the plurality of inlet openings to take a circuitous path thereby separating the debris particulates from the cooling air prior to the cooling air exiting the chamber via an outlet opening of the plurality of outlet openings.

Accessible debris separator for high pressure turbine outside diameter fed static components

An assembly is provided for a turbine engine. This assembly includes a nozzle structure and a combustor wall. The nozzle structure includes a first platform, a second platform and a plurality of nozzle vanes arranged circumferentially about an axis. The nozzle vanes extends radially between and are connected to the first platform and the second platform. The combustor wall includes a plurality of apertures. An upstream portion of the combustor wall is radially between and borders a plenum and a combustion chamber. A downstream portion of the combustor wall is radially between and borders the plenum and a gap. The downstream portion of the combustor wall axially overlaps the nozzle structure with the gap formed by and extending between the combustor wall and the first platform. The apertures extends through the downstream portion of the combustor wall and are aligned with the nozzle vanes.

An assembly is provided for an aerial vehicle. This assembly includes an airframe and a fluid circuit. The airframe includes a body and an airfoil projecting out from the body. The airfoil includes a first surface and a first aperture in the first surface. The fluid circuit is configured to bleed gas from a gas turbine engine mounted to the airframe to provide control gas. The fluid circuit is configured to selectively direct the control gas to the first aperture.

Aerial vehicle fluid control system integrated with gas turbine engine

An assembly is provided for a gas turbine engine. This assembly includes a compressor rotor, a turbine rotor and a cooling circuit. The compressor rotor includes a gas path surface. The turbine rotor is rotatable with the compressor rotor about a rotational axis. The cooling circuit includes an inlet in the gas path surface. The cooling circuit extends from the inlet, through the compressor rotor and into the turbine rotor.

Compressor-turbine rotating assembly with integral cooling circuit(s)

An assembly is provided for an engine. This engine assembly includes an engine structure and a fuel injector. The engine structure includes an injector receptacle. The injector receptacle extends longitudinally through the engine structure along a centerline. The fuel injector is received by the injector receptacle. The fuel injector includes a fuel nozzle and a splash plate. The fuel nozzle is configured to direct fuel out of the fuel injector to impinge against the splash plate.

Fuel injector with splash plate for an engine

An assembly is provided for an engine. This engine assembly includes an engine structure and a fuel injector. The engine structure includes an injector aperture and a fuel supply passage. The injector aperture extends longitudinally through the engine structure along a centerline. The fuel supply passage extends laterally within the engine structure to the injector aperture. The fuel injector is mated with the injector aperture. The fuel injector includes a nozzle passage and a nozzle orifice. The nozzle passage extends longitudinally along the centerline within the fuel injector to the nozzle orifice. The nozzle passage is fluidly coupled with the fuel supply passage.

Modular injector bolt for an engine

A replaceable rotor blade tip clearance measurement device for a gas turbine engine, includes a threaded section along an axis and an integral abradable tip with an internal lattice geometry that extends from the threaded section along the axis.

Replaceable rotor blade tip clearance measurement device for a gas turbine engine

A gas turbine engine is provided that includes an engine core and a bypass duct. The engine core includes a compressor section, a combustor section, a turbine section and a core flowpath. The compressor section includes a radial flow compressor rotor. The core flowpath extends through the compressor section, the combustor section and the turbine section from a core inlet to a core exhaust. The bypass duct includes a bypass flowpath that extends outside of the engine core from a bypass inlet to a bypass exhaust. The bypass inlet is disposed along the compressor section and fluidly coupled with core flowpath.

Gas turbine engine with integral bypass duct

An engine component is configured with a component fluid passage and a receptacle. The component fluid passage extends within the engine component to the receptacle. The receptacle extends through the engine component between a receptacle first end and a receptacle second end. A fluid diverter is configured with a diverter fluid passage and a port. The fluid diverter extends between a diverter first end and a diverter second end. The diverter fluid passage extends partially into the fluid diverter from the diverter first end. The fluid diverter is mated with the receptacle. The diverter first end is disposed at the receptacle first end. The diverter plugs a portion of the receptacle at the diverter second end. The port fluidly couples the component fluid passage to the diverter fluid passage. Fluid is directed through the component fluid passage into the diverter fluid passage to remove debris from the engine component.

Removing debris from an engine component

A brush seal is provided that includes a top plate, a back plate, and a bristle pack. The bristle pack is secured at a joint between the top plate and the back plate. The bristle pack includes a first bristle set extending from the joint, a second bristle set extending from the joint, and a sliding backing plate. The sliding backing plate includes a sliding portion and a support portion. The sliding portion is disposed contiguous with the second bristle set. The support portion has an inner face and a support face. The inner face is in contact with a distal end of the second bristle set. The support face is configured to support at least a portion of the first bristle set. The sliding backing plate is configured to slide relative to the second bristle set.

Brush seal with sliding backing plate

Growing community of inventors

Saco, ME, United States of America

Jose R Paulino