CN-122014420-A - Turbine engine with fuel nozzle

Abstract

A turbine engine may burn fuel to drive a turbine that drives the engine. The fuel nozzle may supply fuel for combustion or ignition of the fuel. The fuel nozzle may include a centerbody defining a first fuel passage terminating at a first orifice. An annular first wall circumferentially surrounds and is spaced apart from the central body to define a first airflow passage therebetween. A set of first swirler vanes are circumferentially spaced about the centerbody and disposed within the first gas flow passage. The fuel nozzles may supply a mixture of fuel and air for combustion.

Inventors

• Katie Kayan sampas
• Pradip Nike
• CLAYTON S. COOPER
• Xibutosh Pal
• Michael T. Baccaro
• Steven.C.Weese
• Michael. A. Benjamin
• Andrew J. Wickham

Assignees

• 通用电气公司

Dates

Publication Date

20260512

Application Date

20250928

Priority Date

20241004

Claims (10)

1. 1. A turbine engine, comprising: a compressor section, a combustor section, and a turbine section in a serial flow arrangement, wherein the combustor section includes a fuel nozzle defining a longitudinal axis and a radial axis orthogonal to the longitudinal axis, the fuel nozzle comprising: A central body defining a first fuel passage extending axially therethrough, the first fuel passage terminating in a first orifice, An annular first wall circumferentially surrounding and spaced apart from the central body to define a first air flow passage therebetween, an A set of first swirler vanes circumferentially spaced about the central body and disposed within the first airflow passage, each first swirler vane extending radially outwardly from the central body toward the annular first wall, at least one first swirler vane defining a respective second fuel passage extending axially therethrough and terminating in a respective second orifice, and Wherein the first orifices are configured to inject a first fuel stream toward a combustion zone and the respective second orifices are configured to inject a respective second fuel stream toward the combustion zone.
2. 2. The turbine engine of claim 1, wherein the set of first swirler vanes imparts a tangential swirl to a first airflow in the first airflow passage.
3. 3. The turbine engine of claim 1, wherein the respective second aperture is disposed downstream of the first aperture.
4. 4. The turbine engine of claim 1, wherein the respective second orifices are configured to inject the respective second fuel streams tangential to the longitudinal axis.
5. 5. The turbine engine of claim 4, wherein the annular first wall and the at least one first swirler vane cooperatively define a respective third fuel passage extending radially therethrough, the respective third fuel passage being in fluid communication with the respective second fuel passage.
6. 6. The turbine engine of claim 5, wherein the third fuel passage is configured to deliver a third fuel flow radially therethrough toward the respective second fuel passage.
7. 7. The turbine engine of claim 1, further comprising: An annular second wall circumferentially surrounding and spaced from the central body to define an annular second gas flow passage therebetween, the annular second wall defining a respective fourth fuel passage extending axially therethrough and terminating in a respective third orifice configured to inject a fourth fuel flow toward the combustion zone, and A set of second swirler vanes circumferentially spaced about the central body and disposed within the annular second airflow passage, each second swirler vane extending radially outwardly from the annular first wall toward the annular second wall.
8. 8. The turbine engine of claim 7, wherein the set of second swirler vanes imparts a tangential swirl to a second airflow in the second airflow passage.
9. 9. The turbine engine of claim 7, wherein the respective third aperture is disposed downstream of the first aperture.
10. 10. The turbine engine of claim 7, wherein the respective third orifices are configured to inject the respective fourth fuel streams tangential to the longitudinal axis.

Description

Turbine engine with fuel nozzle Technical Field The present subject matter relates generally to engine components and, more particularly, to turbine engines having a combustor section including fuel nozzles. Background An engine, such as a turbine engine, includes a turbine driven by a flow of combustion gases generated by combustion of a combustible fuel within a combustor of the engine. Engines utilize fuel nozzles to inject combustible fuel into a combustor where the combustible fuel is ignited to produce combustion gases. The flow of combustion gases through the engine may rotate a plurality of turbine blades, which in turn rotates a compressor, providing compressed air to the combustor for combustion. Typically, air (e.g., compressed air) and a combustible fuel (e.g., hydrocarbon fuel) are injected into the combustion chamber, and the fuel is then combusted in the presence of the air to produce hot gases. Fuel nozzles are commonly used to inject combustible fuel into a combustor. The fuel nozzle may mix fuel with air to achieve efficient combustion. The hot combustion gases are then sent to a turbine where they are cooled and expanded to produce power. Byproducts of fuel combustion typically include environmentally undesirable byproducts such as nitrogen oxides and nitrogen dioxide (collectively referred to as NO x), carbon monoxide (CO), unburned Hydrocarbons (UHC) (e.g., methane and volatile organic compounds that contribute to the formation of atmospheric ozone), and other oxides including oxides of sulfur (e.g., SO 2 and SO 3). Drawings A full and enabling disclosure of the present disclosure, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which: FIG. 1 is a schematic cross-sectional view of an engine according to an exemplary aspect of the present disclosure. FIG. 2A is a cross-sectional view of a fuel nozzle for use with the engine of FIG. 1, according to an exemplary aspect of the present disclosure. Fig. 2B is an offset cross-sectional view taken along line IIB-IIB of fig. 2A, according to an exemplary aspect of the present disclosure. FIG. 3 is another offset cross-sectional view taken along line IIB-IIB of FIG. 2A, according to another exemplary aspect of the present disclosure. FIG. 4A is a cross-sectional view of a fuel nozzle for use with the engine of FIG. 1, according to yet another exemplary aspect of the present disclosure. Fig. 4B is an offset cross-sectional view taken along line IVB-IVB of fig. 4A, according to an exemplary aspect of the present disclosure. Fig. 4C is an offset cross-sectional view taken along line I-I of fig. 4A, according to another exemplary aspect of the present disclosure. FIG. 5A is a cross-sectional view of a fuel nozzle for use with the engine of FIG. 1 according to yet another exemplary aspect of the present disclosure. Fig. 5B is an offset cross-sectional view taken along line VB-VB of fig. 5A in accordance with an exemplary aspect of the present disclosure. Detailed Description Aspects disclosed herein relate to fuel nozzle architectures located within engine components, and more particularly, to fuel nozzle structures configured for use with increased combustion engine temperatures (such as combustion engine temperatures utilizing hydrogen fuel). Hydrogen fuel can eliminate carbon emissions, but can create challenges related to flame holding due to the higher flame speed. Current burners present a durability risk when using this fuel or other high temperature fuels due to flame holding on the burner components caused by flashback. The fuel nozzles as disclosed herein are particularly suited for use with hydrogen fuel (hereinafter "H2 fuel"). In particular, the fuel nozzle is particularly suitable for supplying a flow of H2 fuel to the combustion chamber. The H2 fuel stream may include gaseous H2 fuel, liquid H2 fuel, or a combination thereof. The H2 fuel stream may also be mixed with other fuels or fluids such as, but not limited to, natural gas, coke oven gas, diesel, jet-a, and the like. The H2 fuel has a higher combustion temperature and speed than conventional fuels (e.g., carbon fuels, petroleum fuels, etc.). In addition, flashback may occur when H2 fuel is used. As used herein, flashback refers to the unexpected flame propagation upon combustion of H2 fuel. The H2 fuel has a high volatility, which means that once the H2 fuel is burned or ignited, the flame generated by igniting the H2 fuel may expand at undesirable locations, in other words, flashback may occur. For example, the flame may expand into a fuel nozzle or igniter. The fuel nozzle as described herein ensures that flashback of the H2 fuel does not occur. If the H2 fuel is overheated, auto-ignition of the H2 fuel may occur. In certain locations of the burner section, auto-ignition of the H2 fuel may be undesirable. The fuel nozzles as described herein are designed to ensure