Dual-fuel fuel nozzle with air shield

Patent metadata

Field	Value
Publication number	US-10612775-B2
Application number	US-201715626486-A
Country	US
Kind code	B2
Filing date	Jun 19, 2017
Priority date	Jun 19, 2017
Publication date	Apr 7, 2020
Grant date	Apr 7, 2020

Abstract

The present disclosure is directed to a dual-fuel fuel nozzle including a center body having a tube shape and a gas fuel plenum defined within the center body. The fuel nozzle also includes a plurality of turning vanes extending radially outward from the center body. Each turning vane includes at least one fuel port in fluid communication with the gas fuel plenum. A plurality of apertures is disposed through the plurality of turning vanes. The fuel nozzle further includes a ring manifold disposed within the center body downstream of the plurality of turning vanes. Additionally, the fuel nozzle includes a first fuel tube extending helically around a centerline of the center body. Furthermore, the fuel nozzle includes an air shield disposed within the center body and extending circumferentially around the first fuel tube.

First claim

What is claimed is:

1. A dual-fuel fuel nozzle, comprising:
a center body having a tube shape;
a gas fuel plenum defined within the center body;
a plurality of turning vanes extending radially outward from the center body, each turning vane including at least one fuel port in fluid communication with the gas fuel plenum, wherein a plurality of apertures extends through the plurality of turning vanes and the center body;
a ring manifold disposed within the center body downstream of the plurality of turning vanes, the ring manifold extending radially between an inner band and an outer band and axially between a forward side wall and an aft side wall;
a nozzle body connected to an aft end of an outer sleeve, wherein the ring manifold, the outer sleeve and the nozzle body define a fluid chamber;
an inner fuel tube extending axially within the center body, through the ring manifold to the nozzle body, the ring manifold defining a radial gap between the ring manifold and the inner fuel tube, the radial gap extending axially from the forward side wall of the ring manifold to the aft side wall of the ring manifold;
a first fuel tube extending helically around a centerline of the center body, the first fuel tube supplying liquid fuel to at least one radially oriented fuel injector in the ring manifold; and
an air shield disposed within the center body and extending circumferentially around the first fuel tube such that a forward end of the air shield is positioned downstream of the at least one fuel port and upstream the plurality of apertures relative to a direction of flow through the dual-fuel nozzle, the air shield being in fluid communication with the plurality of apertures, the air shield positioned within the outer band such that the air shield directs air through the radial gap to the fluid chamber.

2. The dual-fuel fuel nozzle as in claim 1 , wherein the air shield includes a plurality of ribs extending radially outwardly from an outer surface of the air shield.

3. The dual-fuel fuel nozzle as in claim 2 , wherein circumferentially adjacent ribs of the plurality of ribs form a respective axial flow channel circumferentially therebetween.

4. The dual-fuel fuel nozzle as in claim 1 , wherein the air shield is positioned upstream from the ring manifold.

5. The dual-fuel fuel nozzle as in claim 1 , further comprising a second fuel tube extending helically around the centerline of the center body, the second fuel tube being fluidly coupled to a fuel plenum of the ring manifold, wherein the air shield extends circumferentially around the first fuel tube and the second fuel tube.

6. The dual-fuel fuel nozzle as in claim 5 , wherein the first fuel tube and the second fuel tube are disposed radially inwardly from the gas fuel plenum.

7. The dual-fuel fuel nozzle as in claim 5 , wherein the first fuel tube and the second fuel tube are radially outward of the centerline of the center body.

8. The dual-fuel fuel nozzle as in claim 5 , wherein coils of the first fuel tube and the second fuel tube are wound together with identical spacing and numbers of turns.

9. The dual-fuel fuel nozzle as in claim 1 , wherein the inner fuel tube is in fluid communication with an axially oriented fuel injector of the nozzle body, wherein a portion of the inner fuel tube extends helically about an axial centerline of the center body between the aft side wall of the ring manifold and the nozzle body.

10. The dual-fuel fuel nozzle as in claim 9 , wherein the inner fuel tube is axially unrestrained by the ring manifold.

11. The dual-fuel fuel nozzle as in claim 1 , further comprising a burner tube circumferentially surrounding a portion of the center body, wherein the burner tube and the center body define a premix passage therebetween, wherein the plurality of turning vanes extends radially between the center body and the outer sleeve within the premix passage.

12. The dual-fuel fuel nozzle as in claim 1 , wherein the at least one radially oriented fuel injector comprises a plurality of radially oriented fuel injectors, the plurality of radially oriented fuel injectors are disposed downstream from the plurality of turning vanes.

13. A combustor, comprising:
an end cover;
a plurality of dual-fuel fuel nozzles connected to the end cover and annularly arranged around a centerline of the end cover, each dual-fuel fuel nozzle comprising:
a center body having a tube shape;
a gas fuel plenum defined within the center body;
a plurality of turning vanes extending radially outward from the center body, each turning vane including at least one fuel port in fluid communication with the gas fuel plenum, wherein a plurality of apertures extends through the plurality of turning vanes and the center body;
a ring manifold disposed within the center body downstream of the plurality of turning vanes, the ring manifold extending radially between an inner band and an outer band and axially between a forward side wall and an aft side wall;
a nozzle body connected to an aft end of an outer sleeve, wherein the ring manifold, the outer sleeve and the nozzle body define a fluid chamber;
an inner fuel tube extending axially within the center body, through the ring manifold to the nozzle body, the ring manifold defining a radial gap between the ring manifold and the inner fuel tube, the radial gap extending axially from the forward side wall of the ring manifold to the aft side wall of the ring manifold;
a first fuel tube extending helically around a centerline of the center body, the first fuel tube supplying liquid fuel to at least one radially oriented fuel injector in the ring manifold; and
an air shield disposed within the center body and extending circumferentially around the first fuel tube such that a forward end of the air shield is positioned downstream of the at least one fuel port and upstream the plurality of apertures relative to a direction of flow through the dual-fuel nozzle, the air shield being in fluid communication with the plurality of apertures, the air shield positioned within the outer band such that the air shield directs air through the radial gap to the fluid chamber.

14. The combustor as in claim 13 , wherein the air shield is positioned upstream from the ring manifold.

15. The combustor as in claim 13 , wherein the air shield includes a plurality of protrusions or ribs extending radially outward from an outer surface of the air shield.

16. The combustor as in claim 15 , wherein circumferentially adjacent ribs of the plurality of ribs form a respective axial flow channel circumferentially therebetween.

17. The combustor as in claim 13 , wherein the dual-fuel fuel nozzle further comprises a second fuel tube extending helically around the centerline of the center body, the second fuel tube being fluidly coupled to a fuel plenum of the ring manifold, wherein the air shield extends circumferentially around the first fuel tube and the second fuel tube.

18. The combustor as in claim 17 , wherein the first fuel tube and the second fuel tube are disposed radially inwardly from the gas fuel plenum.

19. The combustor as in claim 17 , wherein the first fuel tube and the second fuel tube are radially outward of the centerline of the center body.

Assignees

• Gen Electric

Inventors

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

Classifications

• F23R2900/00001

  Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses · CPC title

• F23D2900/00008

  Burner assemblies with diffusion and premix modes, i.e. dual mode burners · CPC title

• F23D2209/30

  Purging · 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

• F23R3/286 Primary

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title