United Technologies Corporation

Raytheon Technologies Corporation

Barry C Schlein

Timothy S Snyder

Thomas J Madden

Jeffrey D Melman

Aaron S Hu

John B McVey

Theodore G Fox

Thomas J Rosfjord

Albert Veninger

Alexander Vranos

Richard Roberts

W Barry Wagner

Donald T Lemon

David H Rummel

Christine Blanchard

A fuel nozzle is provided for a combustor of a gas turbine engine. The fuel nozzle includes an outer air swirler along an axis. The outer air swirler defines an outer annular air passage. An inner air swirler along the axis defines an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler. An annular liquid passage is defined between the inner air swirler and an air inflow tube. A tube is within a housing to define an annular gas passage around the tube. The tube is operable to communicate a liquid into the annular liquid passage and the annular gas passage is operable to communicate a gas into the annular fuel gas passage.

Dual fuel nozzle with concentric fuel passages for a gas turbine engine

A premix liquid fuel nozzle has longitudinal air entrance slots (24) into a cylindrical chamber (20). A centerbody (42) produces an axially increasing flow area toward the chamber outlet (32). Liquid fuel is atomized in a specified location (58) adjacent the conical centerbody (42). This area has a high axial shear velocity producing thorough vaporization and uniform mixing before combustion.

Tangential entry fuel nozzle

A fuel injector 28 utilizing air, a liquid fluid and a gaseous fluid is disclosed. Various construction details are developed to enhance mixing and reduce carbon monoxide emissions for a given level of nitrous oxide emissions. In one detailed embodiment, the fuel nozzle 28 has two radially spaced passages 68, 104 for air having swirlers 86, 114, a liquid fluid passage 57 for water therebetween and a gaseous fluid fuel passage 118 which injects fuel into one of the air passages.

Fuel injector and method of operating the fuel injector

A fuel injector 28 for gaseous and liquid fuel is disclosed. Various construction details are developed to enhance mixing and reduce nitrogen oxide emissions in a compact design. In one embodiment of the invention, the fuel nozzle 28 includes two radially spaced passages 68, 104 for air having swirlers 86, 112 and a liquid fuel passage 57 disposed between the air passages and a gaseous fuel passage 116 outwardly of the outermost air passage. In one detailed embodiment, a center body 76 is disposed in the inner air chamber to promote re-ciruclation of the hot gases.

Dual fuel injector

A two-stage premix combustor in which the primary flow flameholder and secondary flow flameholders are axially separated and each is arranged for optimum emissions control, with the fuel injected, atomized and at least partially vaporized external to the burning zone.

Two-stage premixed combustor

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Wethersfield, CT, United States of America

Barry C Schlein