United Technologies Corporation

Raytheon Technologies Corporation

University of Connecticut

Jeffery A Lovett

Lance L Smith

Meredith Bright Colket, Iii

Robert X Gao

Derk S Philippona

Zhaoyan Fan

Torence P Brogan

Jorge I Farah

Patrick Magari

Sean P Zamora

Shawn M McMahon

Jeffrey Mark Cohen

May L Corn

Scott A Liljenberg

Nathan L Messersmith

David Kwoka

Christopher A Eckett

Donald J Hautman

Andrzej Banaszuk

Benjamin Bellows

Darin A Knaus

Javier Nebero Johnson

Eric Beach

Daniel J Micka

Caleb N Cross

Scott David Phillips

Frederick C Padget

John W Mordosky

An assembly is provided that includes a slider seal having a washer and a tubular puck. The washer includes an inner washer surface and an outer washer surface. The inner washer surface extends around an axis of the slider seal and has a non-circular cross-sectional geometry. The inner washer surface forms a washer bore axially through the washer. The outer washer surface extends around the axis and has a cross-sectional geometry with a shape that is different than a shape of the non-circular cross-sectional geometry. The tubular puck projects axially through the washer bore and includes an outer puck surface. The outer puck surface extends around the axis. The outer puck surface is sealingly engaged with and configured to slide axially along the inner washer surface.

Slider seal with non-circular puck geometry

A combustor or augmentor of a gas turbine engine is provided. The combustor or augmentor includes a wall defining apertures and an interior having an inlet, an outlet and a mixing region between the inlet and the outlet and fuel injectors. The fuel injectors are respectively arrayed along the wall at corresponding apertures to inject fuel into the mixing region. Each fuel injector includes a fuel injector body defining an injection outlet through which fuel exits the fuel injector body toward the mixing region and a pintle. The pintle includes a first end, a second end and a pintle body extending between the first and second ends. At least one of the first and second ends is attachable to the fuel injector body to position the pintle body between the injection outlet and the mixing region.

Enhancement for fuel spray breakup

A fuel injection system for a gas turbine engine includes a fuel delivery conduit, a nozzle block with a nozzle aperture, and a cavity block with a cavity. The nozzle aperture has a first cross sectional area, and injects fuel received from the fuel delivery conduit into the cavity. The cavity has a second cross sectional area that is greater than the first cross sectional area.

Fuel delivery system with a cavity coupled fuel injector

A fuel injection system for a gas turbine engine includes a vane in an airflow path within the gas turbine engine, the vane includes an air channel with an outlet in communication with the airflow path; and a fuel nozzle within the vane operable to inject fuel into the air channel to at least partially premix and prevaporize the fuel with a secondary airflow from within the vane in the air channel prior to entry into the airflow path through the outlet. A method of injecting fuel within a gas turbine engine includes at least partially premixing and prevaporizing fuel with a secondary airflow from within a vane in an air channel within the vane, the vane within an airflow path of the gas turbine engine.

Carbureted fuel injection system for a gas turbine engine

A variable area exhaust mixer is provided for a gas turbine engine. The variable area exhaust mixer includes an outer wall with a multiple of doors. Each of the multiple of doors is operable to control a passage entrance into at least one of a multiple of circumferentially arrayed vanes with a respective strut flow passage which essentially alters its bypass ratio during flight to match requirements.

Variable area exhaust mixer for a gas turbine engine

A gaspath component includes a flowpath body. A cooling plenum is disposed within the flowpath body. The cooling plenum includes a first region configured to receive a cooling flow and a second region configured to expel the cooling flow from the flowpath body. A metering obstruction is positioned between the first region and the second region and is configured to meter a flow of coolant through the cooling plenum.

Cooling system for a gaspath component of a gas powered turbine

A fuel injection system for a gas turbine engine includes a fuel nozzle with a fuel injection aperture to inject a fuel jet and a multiple of airflow passages in the fuel nozzle to communicate a multiple of air streams to interact with the fuel jet.

Cavity swirl fuel injector for an augmentor section of a gas turbine engine

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

A method for operating a sensor, including simultaneously exciting a first set of electrodes and sensing an output of each electrode of a second set of electrodes, storing output data corresponding to the output of each electrode of the second set of electrodes in a memory storage device, shifting at least one electrode from the first set of electrodes to the second set of electrodes and at least one electrode from the second set of electrodes to the first set of electrodes, and repeating the simultaneously exciting and sensing, the storing, and the shifting until an output data has been stored for each possible pair of electrodes in the first and second set of electrodes.

Multiple-excitation multiple-receiving (MEMR) capacitance tomography

An air-blast fuel nozzle assembly includes a housing having an inner surface defining an interior chamber around a central axis. The inner surface terminates in an exit aperture. An air swirler pneumatically communicates with the interior chamber and has vanes operative to impart a swirling motion to air passing across the vanes and into the interior chamber. A fuel injection assembly includes a nozzle portion extending along the central axis and having a plurality of outlets circumferentially-arranged around the central axis that are directed into the interior chamber toward the inner surface of the housing. A shield extends radially outwardly from the nozzle portion upstream of the plurality of outlets. The shield extends between a base at the nozzle section and a free tip end such that the shield extends partially across the interior chamber toward the inner surface.

Air-blast fuel-injector with shield-cone upstream of fuel orifices

A gas turbine engine augmenter has a gas flowpath. A number of vanes extend into the gas flowpath. A number of augmenter fuel conduits have outlets along at least some of the vanes. At least one burner discharge outlet is along at least one of the vanes for discharging a pilot gas.

Augmentor pilot

A turbine engine augmentor has a centerbody within a gas flowpath. A flameholder is positioned in the flowpath outboard of the centerbody. A burner within the centerbody has an outlet for expelling combustion products of a first pilot fuel. A pilot fuel conduit has an outlet positioned to introduce a supplemental pilot fuel to the expelled combustion products.

Augmentor

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.

Growing community of inventors

Tolland, CT, United States of America

Jeffery A Lovett