General Electric Company

Parker-hannifin Corporation

Alfred Albert Mancini

Michael Anthony Benjamin

Duane Douglas Thomsen

Nayan Vinodbhai Patel

Hukam Chand Mongia

James Neil Cooper

Marie Ann McMasters

Steven Joseph Lohmueller

Bangalore Aswatha Nagaraj

Lawrence Bernard Kool

Michael Louis Vermeersch

William Joseph Myers, Jr

Brandon Wayne Miller

Daniel Alan Niergarth

John Frederick Ackerman

William Randolph Stowell

Allen Michael Danis

Ethan Patrick O'Connor

Rex Jay Harvey

Kevin Richard Leamy

Robert Thane Mains

Shui-chi Li

Shih-Yang Hsieh

Peter Laing

Thomas Vander Ng

George Chia-Chun Hsiao

Thomas George Holland

Barry Walford Savel

Michael Peter Wrubel

Rameshkumar Muthuvel Chandrasekaran

Christopher Edward Wolfe

Jan Christopher Schilling

Clayton Stuart Cooper

Kwanwoo Kim

Minesh Ashok Shah

Leonardo Cesar Kammer

Jeffrey Bernard Fortin

David Louis Burrus

Aaron Jay Knobloch

Peter W Mueller

Raymond Floyd Martell

John A Kastl

David Walter Parry

Chukwueloka Obiora Umeh

Randy Joseph Tobe

William Joseph Myers Jr

William J Myers

Marie Ann Mcmasters

William Joseph Myers

Shui-Chi Li

Steven J Lohmueller

A hydrocarbon fluid containment article having a wall with a surface that is wetted by hydrocarbon fluid. The surface includes an anti-coking coating. The anti-coking coating includes a copper salt, a silver salt, or a combination thereof. A gas turbine engine component including a wall having a first surface and an anti-coking coating on the first surface of the wall that is wetted by hydrocarbon fluid. The anti-coking coating including a copper salt, a silver salt, or a combination thereof that prevents the formation of gum or coke on a surface thereon. Methods for reducing the deposition of thermal decomposition products on a wall of an article are also provided.

Coated article for hot hydrocarbon fluid and method of preventing fuel thermal degradation deposits

A fuel nozzle valve includes a fuel nozzle valve liner having a channel with an opening for allowing fuel to flow therethrough and a seat. A plunger has a stud and a base substantially perpendicular to the stud, the plunger being configured to move relative to the fuel nozzle valve liner to seal or to open the opening of the fuel nozzle valve. The fuel nozzle valve further includes a metal resilient member configured to contact the base of the plunger and the seat of the fuel nozzle valve liner to seal the opening of the fuel nozzle valve when the plunger is moved to seal the fuel nozzle valve.

Fuel nozzle valve seals for high temperature

A component configured to be in contact with a hydrocarbon fluid and a method of preparing a contact surface of the component. The component may include a wall having the contact surface configured to be in contact with the hydrocarbon fluid. The contact surface is formed from a metal comprising a metal M, where M is selected from the group consisting of nickel (Ni), palladium (Pd), and platinum (Pt). A metal-ligand complex comprising phosphorus (P) is on the contact surface. The method of preparing a contact surface of the component may include treating the contact surface with a metal-ligand complex precursor comprising a phosphorus (P) ligand.

Surfaces for contacting a hydrocarbon fluid and methods for preparing the same

A fuel oxygen reduction unit for an engine is provided. The fuel oxygen reduction unit includes an inlet fuel line; a stripping gas source; a contactor selectively in fluid communication with the stripping gas source, the inlet fuel line, or both to form a fuel/gas mixture; and a separator that receives the fuel/gas mixture, the separator configured to separate the fuel/gas mixture into an outlet stripping gas flow and an outlet fuel flow; wherein a flow of stripping gas passes through the fuel oxygen reduction unit a single time.

Fuel oxygen reduction unit for prescribed operating conditions

In one exemplary embodiment of the present disclosure, a method of operating a fuel system for an aeronautical gas turbine engine is provided. The method includes: providing a flow of fuel to a fuel nozzle of the aeronautical gas turbine engine during a wind down condition; operating a fuel oxygen reduction unit to reduce an oxygen content of the flow of fuel provided to the fuel nozzle of the aeronautical gas turbine engine during the wind down condition; and ceasing providing the flow of fuel to the fuel nozzle of the aeronautical gas turbine engine, the fuel nozzle comprising a volume of fuel after ceasing providing the flow of fuel to the fuel nozzle; wherein operating the fuel oxygen reduction unit comprises operating the fuel oxygen reduction unit to reduce an oxygen content of the volume of fuel in the fuel nozzle to less than 20 parts per million.

Fuel oxygen reduction unit

A gas turbine engine includes a combustion section, the combustion section including a plurality of fuel nozzles. A fuel delivery system for the gas turbine engine includes a feed tube and a fuel manifold fluidly connected to the feed tube for receiving fuel from the feed tube. The fuel delivery system also includes a pigtail fuel line fluidly connected to the fuel manifold and configured to fluidly connect to a fuel nozzle of the plurality of fuel nozzles when the fuel delivery system is installed in the gas turbine engine. In order to reduce an amount of hydraulic instability of a fuel flow through the fuel delivery system, at least one of the fuel manifold or the pigtail fuel line includes a means for damping a hydraulic instability within the fuel delivery system.

Fuel delivery system for a gas turbine engine

A fuel nozzle for a gas turbine engine includes an outer body extending generally along a centerline axis and defining a plurality of openings in an exterior surface. The fuel nozzle additionally includes a main injection ring disposed at least partially inside the outer body, the main injection ring including a fuel post extending into or through one of the plurality of openings of the outer body. The fuel post defines a spray well and a main fuel orifice, the spray well defining a bottom surface, a side wall, and a taper in the bottom surface extending from the main fuel orifice towards the side wall.

Fuel nozzle for a gas turbine engine

The present disclosure is directed to a fuel nozzle assembly for a gas turbine engine. The fuel nozzle assembly includes a centerbody extended along a nozzle centerline axis and generally concentric thereto and an outer sleeve surrounding the centerbody and extended along the nozzle centerline axis and generally concentric thereto. The centerbody defines an outer wall extended at least partially along the nozzle centerline axis in which the centerbody defines a first fuel passage therewithin and one or more first fuel exit openings through the outer wall. Each first fuel exit opening is discrete from another along the outer wall. The outer sleeve and centerbody together define a first air passage therebetween. The first fuel passage and the first fuel exit opening are in fluid communication with the first air passage. The fuel nozzle assembly provides a first flow of fuel through the first fuel passage and first exit opening and a first flow of air through the first air passage, the first flow of fuel defines a jet in crossflow mixing with the first flow of air.

Jet in cross flow fuel nozzle for a gas turbine engine

A fuel nozzle for a gas turbine engine includes an outer body defining a plurality of openings in an exterior surface. The fuel nozzle also includes a main injection ring disposed at least partially inside the outer body. The main injection ring includes a plurality of fuel posts extending into or through the plurality of openings of the outer body. The plurality of fuel posts include an LP fuel post defining a main fuel orifice, a top surface, and a scarf, the scarf of the LP fuel post extending in the top surface in a first direction relative to the centerline axis away from the main fuel orifice. The plurality of fuel posts also include an HP fuel post defining a main fuel orifice, a top surface, and a scarf, the scarf of the HP fuel post extending in the top surface f in a second direction relative to the centerline axis away from the main fuel orifice, the second direction being at least ninety degrees different than the first direction.

A fuel nozzle is provided for a gas turbine engine, and can include a pilot fuel injector having an axially-elongated, inner pilot centerbody wall and an outer pilot centerbody wall, with the axially-elongated, inner pilot centerbody wall extending from an upstream end to an annular fuel passage defining the downstream end of the pilot fuel injector. The fuel passage intersects with the inner pilot centerbody wall at a pilot fuel metering orifice. The fuel nozzle also includes a pilot fuel film surface downstream from the annular fuel passage and an annular splitter surrounding the pilot fuel injector. The annular splitter comprises, in axial sequence: an upstream section, a splitter throat having a diameter that is larger than a downstream diameter defined by the pilot fuel film surface, and a downstream diverging surface having an average diverging angle of about 24&#xb0; to about 40&#xb0; in relation to a centerline axis.

Prefilming air blast (PAB) pilot having annular splitter surrounding a pilot fuel injector

In one aspect, a fuel supply system may include a fuel injector having a primary and a secondary pilot fuel nozzle in fluid communication with a primary and a secondary fuel circuit, respectively, and a main fuel nozzle in fluid communication with a main fuel circuit. The fuel injector may also define a by-pass fuel circuit connected between the primary circuit and the secondary circuit and/or the main circuit. The system may also include a primary fuel manifold configured to be fluidly connected to the primary pilot fuel nozzle via the primary fuel circuit. Moreover, the system may include a by-pass valve provided in operative association with the by-pass fuel circuit. The by-pass valve may be configured to be opened such that a portion of the fuel flowing through the primary circuit from the primary fuel manifold is directed to the secondary circuit and/or the main circuit.

Fuel supply system for a gas turbine engine

A pilot fuel injector is provided for a fuel nozzle of a gas turbine engine. The pilot fuel injector can include an axially-elongated, inner pilot centerbody wall extending from an upstream end to a downstream end, with the axially-elongated, inner pilot centerbody wall having a diverging-converging orientation with respect to a centerline axis to define a hollow tube having an upstream diameter, a throat, and a downstream diameter such that the throat has an inner diameter that is less than both of the upstream diameter and the downstream diameter. The pilot fuel injector also includes a center air circuit positioned at the upstream end, and an annular fuel passage defining the downstream end and intersecting with the centerbody wall at a pilot fuel metering orifice. A pilot fuel film surface is downstream from the annular fuel passage.

Prefilming air blast (PAB) pilot for low emissions combustors

A fuel nozzle for a gas turbine engine is disclosed, the fuel nozzle comprising at least one unitary component made using a rapid manufacturing process. In one aspect, the rapid manufacturing process is a laser sintering process. Unitary components disclosed include a conduit, swirler, distributor, venturi and a centerbody.

Fuel nozzle

Growing community of inventors

Cincinnati, OH, United States of America

Alfred Albert Mancini