Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Jacob William Hardes

Timothy A Fox

Walter Ray Laster

Juan Enrique Portillo Bilbao

Scott M Martin

Robert H Bartley

Mario Gaviria

A gas turbine engine has a converging duct that has combustion products flow at low mach speeds through a first portion and a high mach speeds through a second portion. The converging duct has two types of cooling schemes formed. One type of cooling scheme is beneficial for the low mach speed combustion product flow and one type of cooling scheme is beneficial for the high mach speed combustion product flow. The two cooling schemes are blended together in order increase the efficiency of the cooling of the converging duct.

Converging duct with elongated and hexagonal cooling features

A cooling system for a fuel system in a turbine engine that is usable to cool a fuel nozzle is disclosed. The cooling system may include one or more cooling system housings positioned around the fuel nozzle, such that the cooling system housing forms a cooling chamber defined at least partially by an inner surface of the cooling system housing and an outer surface of the fuel nozzle. The fuel nozzle may extend into a combustor chamber formed at least in part by a combustor housing. The fuel nozzle may include one or more fuel exhaust orifices with an opening in an outer surface of the fuel nozzle and configured to exhaust fluids unrestricted by the housing forming the cooling system cooling chamber. The cooling system may provide cooling fluids to cool the fuel nozzle within the cooling system cooling chamber regardless of whether the fuel nozzle is in use.

Cooling system for fuel nozzles within combustor in a turbine engine

A secondary fuel stage () of a combustor of a gas turbine engine. The combustor has a main combustion zone () upstream of the secondary fuel stage to ignite working gas The secondary fuel stage includes a nozzle () with dual outlets () oriented with a circumferential component to inject an air-fuel mixture () into the combustor. The nozzle is effective to entrain the air-fuel mixture with the working gas () such that a peak temperature () of the working gas at a location downstream of the secondary fuel stage is less than a peak temperature () of working gas if the air-fuel mixture were injected into the combustor with a single outlet nozzle ().

Dual outlet nozzle for a secondary fuel stage of a combustor of a gas turbine engine

A fuel injector for injecting fuels having a different energy density in a gas turbine is provided. A first fuel supply channel () and a second fuel supply channel () may be coaxially arranged in a fuel delivery structure (). A first set of vanesincludes a radial passage () in fluid communication with the first channel () to receive a first fuel. Passage () branches into passages () each having an aperture () to inject the first fuel without jet in cross-flow injection. A second set of vanes () includes a radial passage () in fluid communication with the second channel () to receive a second fuel. Passage () branches into passages () each having an aperture () arranged to inject the second fuel also without jet in cross-flow injection. This arrangement may be effective to reduce flashback that otherwise may be encountered in fuels having a relatively high flame speed.

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Charlotte, NC, United States of America

Jacob William Hardes