当前申请(专利权)人地址：
Incorporated in USA - New York, 1 River Road, Schenectady 12345, New York, United States of America
权利要求：
CLAIMS:
i A fuel nozzle assembly for a gas turbine engine, the fuel nozzle assembly comprising:
a centerbody extended along a nozzle centerline axis and generally concentric thereto, the centerbody defining an outer wall extended at least partially along the nozzle centerline axis, wherein the centerbody defines a first fuel passage therewithin and one or more first fuel exit openings through the outer wall, and wherein each first fuel exit opening is discrete from another along the outer wall; and
an outer sleeve surrounding the centerbody and extended along the nozzle centerline axis and generally concentric thereto, the outer sleeve and centerbody together defining a first air passage therebetween, and wherein the first fuel passage and the first fuel exit opening is in fluid communication with the first air passage, and wherein 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 defining a jet in crossflow mixing with the first flow of air.
2. The fuel nozzle assembly of claim 1, wherein the outer wall of the centerbody defines an exit portion converging toward a downstream direction at an angle of approximately 20 degrees to approximately 60 degrees relative to the nozzle centerline axis.
3. The fuel nozzle assembly of claim 2, wherein the first fuel exit opening is defined within the exit portion of the outer wall of the centerbody.
4. The fuel nozzle assembly of either of claim 1 or 2, wherein the exit portion of the outer wall defines a length along the nozzle centerline axis from a downstream end of the centerbody equal to or less than approximately five times a maximum diameter of the first fuel exit opening.
5. The fuel nozzle assembly of any preceding claim, wherein the centerbody further defines a second fuel passage therewithin and a second fuel exit opening, wherein the second fuel exit opening is centered at the nozzle centerline axis.
6. The fuel nozzle assembly of claim 5, wherein the fuel nozzle assembly provides a second flow of fuel through the second fuel passage and second exit opening.
2 The fuel nozzle assembly of claim 2 or any claim dependent thereon, wherein the first fuel passage defines an outlet portion in fluid communication with the first fuel exit opening approximately perpendicular to the exit portion of the outer wall. 8. The fuel nozzle assembly of claim 7, wherein the outlet portion of the first fuel passage defines a length to the first fuel exit opening, and wherein the length of the outlet portion is approximately 2.0 to approximately 3.5 times a maximum diameter of the first fuel exit opening.
9. The fuel nozzle assembly of any preceding claim, wherein the outer sleeve defines a distance along a radial direction from the nozzle centerline axis fluidly segregated from the first flow of fuel from the first fuel exit opening.
10. The fuel nozzle assembly of any preceding claim, wherein a plurality of the first fuel exit openings is disposed in circumferential arrangement around the nozzle centerline axis on the outer wall of the centerbody.
11. A gas turbine engine, the gas turbine engine comprising:
a plurality of fuel nozzle assemblies disposed in circumferential arrangement around a longitudinal centerline of the gas turbine engine, wherein each fuel nozzle comprises:
a centerbody extended along a nozzle centerline axis and generally
concentric thereto, the centerbody defining an outer wall extended at least
partially along the nozzle centerline axis, wherein the centerbody defines a
first fuel passage therewithin and one or more first fuel exit openings through
the outer wall, and wherein each first fuel exit opening is discrete from another
along the outer wall; and
an outer sleeve surrounding the centerbody and extended along the
nozzle centerline axis and generally concentric thereto, the outer sleeve and
centerbody together defining a first air passage therebetween, and wherein the
first fuel passage and the first fuel exit opening is in fluid communication with
the first air passage, wherein 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 defining a jet in crossflow
mixing with the first flow of air.
12. The gas turbine engine of claim 11, wherein the gas turbine engine defines a first fuel nozzle and a second fuel nozzle among the plurality of fuel nozzles, wherein the first fuel nozzle defines a first diameter of the first fuel passage and the first fuel exit opening and the second fuel nozzle defines a second diameter of the first fuel passage and the first fuel exit opening.
13. The gas turbine engine of claim 12, wherein the first fuel nozzle defines a first flow rate of fuel through the first fuel passage and first exit orifice, and wherein the second fuel nozzle defines a second flow rate of fuel through the first fuel passage and the first exit orifice, the first flow rate and the second flow rate providing attenuation of combustion acoustics.
14. The gas turbine engine of any of claims 11 to 13, wherein the outer wall of the centerbody defines an exit portion converging toward a downstream direction at an angle of approximately 20 degrees to approximately 60 degrees relative to the nozzle centerline axis.
15. The gas turbine engine of claim 14, wherein the gas turbine engine defines a first fuel nozzle and a second fuel nozzle among the plurality of fuel nozzles, wherein the first fuel nozzle defines a first angle of the exit portion of the centerbody different from a second angle of the exit portion at the second fuel nozzle.
16. The fuel nozzle assembly of either of claim 14 or 15, wherein the first fuel exit opening is defined within the exit portion of the outer wall of the centerbody.
17. The fuel nozzle assembly of any of claims 14 to 16, wherein the exit portion of the outer wall defines a length along the nozzle centerline axis from a downstream end of the centerbody equal to or less than approximately five times a maximum diameter of the first fuel exit opening.
18. The gas turbine engine of any of claims 14 to 17, wherein the first fuel passage defines an outlet portion in fluid communication with the first fuel exit opening approximately perpendicular to the exit portion of the outer wall.
19. The fuel nozzle assembly of claim 18, wherein the outlet portion of the first fuel passage defines a length to the first fuel exit opening, and wherein the length of the outlet portion is approximately 2.0 to approximately 3.5 times a maximum diameter of the first fuel exit opening.
20. The gas turbine engine of any of claims 11 to 19, wherein the outer sleeve defines a distance along a radial direction from the nozzle centerline axis fluidly segregated from the first flow of fuel from the first fuel exit opening.