Dual-fuel fuel nozzle with liquid fuel tip

Patent metadata

Field	Value
Publication number	US-10697639-B2
Application number	US-201715460398-A
Country	US
Kind code	B2
Filing date	Mar 16, 2017
Priority date	Mar 16, 2017
Publication date	Jun 30, 2020
Grant date	Jun 30, 2020

Abstract

A dual-fuel fuel nozzle includes a centerbody that at least partially defines an air plenum therein. A tip body is disposed at a downstream end of the centerbody. The tip body includes an upstream side that is axially spaced from a downstream side. The downstream side defines a circular slot and a circular recess that is positioned radially inwardly from the circular slot. The circular recess includes a floor and a side wall, The floor defines an insert opening and the side wall defines an annular groove that includes an undercut surface. The tip body further defines a plurality of orifices annularly arranged around the insert opening radially inward from the side wall of the circular recess. Each orifice includes an inlet that is in fluid communication with the air plenum and an outlet that is oriented towards the undercut surface.

First claim

What is claimed is:

1. A dual-fuel fuel nozzle, comprising: a centerbody, wherein the centerbody at least partially defines an air plenum therein;
a tip body disposed at a downstream end of the centerbody, the tip body having an upstream side axially spaced from a downstream side, the downstream side defining a circular slot and a circular recess positioned radially inwardly from the circular slot, the circular recess comprising a first floor and an annular side wall, the first floor defining an insert opening and the side wall defining an annular groove, wherein the annular groove defines an undercut surface, the tip body further defining a plurality of orifices annularly arranged around the insert opening and positioned radially inward from the side wall and upstream of the undercut surface of the circular recess, each of the plurality of the orifices including a first inlet in direct fluid communication with the air plenum and a first outlet defined along the first floor, wherein the first outlet is oriented towards the undercut surface and configured to direct a portion of compressed air from the air plenum to impinge upon the undercut surface of the annular groove, wherein the circular slot of the tip body includes a second floor and a plurality of apertures annularly arranged across the second floor, each aperture of the plurality of apertures extending from a second inlet immediately downstream of the air plenum to a second outlet defined along the second floor, wherein the plurality of apertures are disposed radially outward from the plurality of orifices.

2. The dual-fuel fuel nozzle as in claim 1 , wherein the circular slot of the tip body includes a pair of radially opposing walls, wherein at least one of the radially opposing walls is angled radially inwardly or radially outwardly with respect to an axial centerline of the dual-fuel fuel nozzle.

3. The dual-fuel fuel nozzle as in claim 1 , wherein the circular slot divides the downstream side into a radially outer surface and a radially inner surface, wherein the circular recess is defined within the radially inner surface.

4. The dual-fuel fuel nozzle as in claim 3 , wherein a portion of the radially inner surface diverges radially outwardly aft of the annular groove.

5. The dual-fuel fuel nozzle as in claim 1 , further comprising an atomizer insert removably seated within the insert opening.

6. The dual-fuel fuel nozzle as in claim 1 , further comprising a conduit extending within the centerbody, wherein one end of the conduit is connected to an inlet of the insert opening and a second end of the conduit is fluidly coupled to a fluid supply.

7. The dual-fuel fuel nozzle as in claim 6 , wherein at least a portion of the conduit extends helically within the centerbody upstream from the insert opening of the tip body.

8. The dual-fuel fuel nozzle as in claim 1 , further comprising an outer sleeve that circumferentially surrounds at least a portion of the centerbody and a plurality of turning vanes that extend radially between the centerbody and the outer sleeve.

9. The dual-fuel fuel nozzle as in claim 2 , wherein each turning vane of the plurality of turning vanes includes at least one fuel port in fluid communication with a gas-fuel fuel supply.

10. A combustor, comprising:
an end cover coupled to an outer casing;
a dual-fuel fuel nozzle coupled to the end cover, the dual-fuel fuel nozzle comprising, an outer sleeve, a centerbody extending axially through the outer sleeve wherein the outer sleeve and the centerbody are radially spaced to form a premix passage therebetween and a plurality of turning vanes that extend radially between the centerbody and the outer sleeve within the premix passage;
a tip body disposed at a downstream end of the centerbody, the Up body having an upstream side axially spaced from a downstream side, the downstream side defining a circular slot and a circular recess positioned radially inwardly from the circular slot, the circular recess comprising a first floor and an annular-a side wall, the first floor defining an insert opening and the side wall defining an annular groove, wherein the annular groove defines an undercut surface, the tip body further defining a plurality of orifices annularly arranged around the insert opening and positioned radially inward from the side wall and upstream of the undercut surface of the circular recess, each of the plurality of the orifices including a first inlet in direct fluid communication with an air plenum defined within the centerbody and a first outlet defined along the first floor, wherein the first outlet is oriented towards the undercut surface and configured to direct a portion of compressed air from the air plenum to impinge upon the undercut surface of the annular groove, wherein the circular slot of the tip body includes a second floor and a plurality of apertures annularly arranged across the second floor, each aperture of the plurality of apertures extending from a second inlet immediately downstream of the air plenum to a second outlet defined along the second floor, wherein the plurality of apertures are disposed radially outward from the plurality of orifices.

11. The combustor as in claim 10 , wherein the circular, slot of the tip body includes a pair of radially opposing walls, wherein at least one of the radially opposing walls is angled radially, inwardly or radially outwardly with respect to an axial centerline of the dual-fuel fuel nozzle.

12. The combustor as in claim 10 , wherein the circular slot divides the downstream side of the tip body into a radially outer surface and a radially inner surface, wherein the circular recess is defined within the radially inner surface.

13. The combustor as in claim 12 , wherein a portion of the radially inner surface diverges radially outwardly aft of the annular groove.

14. The combustor as in claim 10 , further comprising an atomizer insert removably seated within the insert opening.

15. The combustor as in claim 10 , further comprising a conduit extending within the centerbody, wherein one end of the conduit is connected to an inlet of the insert opening and a second end of the conduit is fluidly coupled to a fluid supply.

16. The combustor as in claim 15 , wherein at least a portion of the conduit extends helically within the centerbody upstream from the insert opening of the tip body.

17. The combustor as in claim 10 , wherein each turning vane of the plurality of turning vanes includes at least one fuel port in fluid communication with a gas-fuel fuel supply.

Assignees

• Gen Electric
• General Electric Compamy

Inventors

• Johnson Thomas Edward
• Graham Kaitlin Marie
• Myers Geoffrey David

Classifications

• F23R3/28 Primary

  characterised by the fuel supply (burners F23D) · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F02C7/22

  Fuel supply systems · CPC title

• F23R3/343

  Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00) · CPC title

• F23D2900/00015

  Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability · CPC title