General Electric Company

Other

Nayan Vinodbhai Patel

Duane Douglas Thomsen

Michael Anthony Benjamin

Alfred Albert Mancini

Chinh Tran

Kevin Richard Graziano

Michael Scott McCambridge

Eric John Kress

Brendon Matthew Leeker

Daniel J Kirtley

Chad Holden Sutton

Adam Robert Kahn

Kevin Vandevoorde

James A Russo

Kwanwoo Kim

Craig Alan Gonyou

Anquan Wang

Michael John McCarren

Shih-Yang Hsieh

Krishnakumar Venkatesan

Owen James Sullivan Rickey

Neeraj Kumar Mishra

Harris Daniel Abramson

Robert Andrew Stowers

Yuxin Zhang

Shanwu Wang

Anne Dord

Anil Raju

Ying Huang

Dhanashegaran Shanmugam

A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.

Gas turbine combustor fuel nozzle assembly and combustor liner having dilution holes in arrangements

A method of treatment is disclosed, comprising administering a composition of Cyclodextrin and reduced, nanonized L-Glutathione to a patient in need of treatment, wherein the L-Glutathione molecule is non-acetylated, non-Esterified, and non-fatty acid attached.

Method for stabilization and delivery of therapeutic molecules

Combustor fuel nozzle assembly

A method and system for cleaning a fuel nozzle during engine operation is provided. Operations include operating the compressor section to provide the flow of oxidizer at a first oxidizer flow condition to the combustion chamber, wherein the first oxidizer flow condition comprises an environmental parameter; operating the fuel system at a first fuel flow condition to produce a fuel-oxidizer ratio at the combustion chamber; comparing the environmental parameter to a first environmental parameter threshold; and transitioning the fuel system to a second fuel flow condition corresponding to a cleaning condition at the fuel nozzle if the environmental parameter is equal to or greater than the first environmental threshold.

System and method for fuel nozzle cleaning during engine operation

A dome-deflector structure for a combustor of a gas turbine includes a dome portion and a deflector portion, the dome portion and the deflector portion being connected together to form a dome-deflector cavity therebetween. The dome portion includes a plurality of dome-side cooling airflow passages therethrough arranged in a plurality of groups of dome-side cooling airflow passages, each group of dome-side cooling airflow passages being arranged to provide a flow of air therethrough in a respective group swirl direction, and adjacent groups of the dome-side cooling airflow passages providing the flow of air in a different group swirl direction with respect to one another.

Dome structure providing a dome-deflector cavity with counter-swirled airflow

A System for Aerodynamic Premixer for Reduced Emissions comprising a premixer is generally cylindrical in form and defined by the relationship in physical space between a first ring, a second ring, and a plurality of radial vanes. The first and second rings are found to be generally equidistant, one from the other, at all points along their facing surfaces. Radial vanes connect the first ring to the second ring and thereby form the premixer.

System for aerodynamically enhanced premixer for reduced emissions

A combustor assembly for a heat engine is generally provided. The combustor assembly defines a fuel nozzle centerline and a radial direction extended from the nozzle centerline. The combustor assembly includes a fuel nozzle disposed at least partially concentric to the nozzle centerline. The fuel nozzle defines a fuel injection opening. A deflector assembly is defined around the nozzle centerline extended therethrough. The deflector assembly includes a deflector wall extended at least partially along the radial direction. The deflector assembly includes a conical portion defined around the nozzle centerline. The conical portion defines a fuel nozzle opening. A plurality of openings is defined through the conical portion radially adjacent to the fuel injection opening at the fuel nozzle.

Combustor assembly for a heat engine

A method and system for fuel nozzle cleaning during engine operation is provided. The steps or operations include operating the compressor section to provide the flow of oxidizer to the combustion chamber, operating the fuel system at a first fuel flow condition, in which the first fuel flow condition provides a fuel-oxidizer ratio at the combustion chamber, operating the fuel system at a second fuel flow condition, in which the second fuel flow condition provides the fuel-oxidizer ratio at the combustion chamber equal at the first fuel flow condition and the second fuel flow condition, and operating the fuel system at a third fuel flow condition after operating the fuel system at the second fuel flow condition.

Method and system for fuel nozzle cleaning during engine operation

A fuel nozzle for a combustor assembly of a heat engine is generally provided. The fuel nozzle defines a fuel nozzle centerline therethrough and a radial direction extended from the nozzle centerline. The fuel nozzle includes a first wall extended along the radial direction. The first wall defines a first cooling passage and a second cooling passage each extended therethrough. The first cooling passage is defined at a first acute angle relative to the nozzle centerline. The second cooling passage is defined at a second acute angle 90 degrees or less relative to the first acute angle.

Fuel nozzle cooling structure

A fuel nozzle apparatus for a gas turbine engine includes: a first pilot fuel injector disposed on a centerline axis of the fuel nozzle which defines a direction of air flow through the fuel nozzle, the first pilot fuel injector being of a pressure atomizing type; an annular second pilot fuel injector at least partially surrounding the first pilot fuel injector, the second pilot fuel injector being of an air blast type and having a fuel outlet disposed axially downstream and radially outboard of the first pilot fuel injector; an annular venturi surrounding the first and second pilot fuel injectors, the venturi including a throat of minimum diameter; an array of inner swirl vanes extending between the first pilot fuel injector and the second pilot fuel injector; and an array of outer swirl vanes extending between the second pilot fuel injector and the venturi.

Hybrid air blast fuel nozzle

Aerodynamically enhanced premixer with purge slots for reduced emissions

Growing community of inventors

Liberty Township, OH, United States of America

Nayan Vinodbhai Patel