Nozzle with multi-tube fuel passageway for gas turbine engines

Patent metadata

Field	Value
Publication number	US-9562692-B2
Application number	US-201414164791-A
Country	US
Kind code	B2
Filing date	Jan 27, 2014
Priority date	Feb 6, 2013
Publication date	Feb 7, 2017
Grant date	Feb 7, 2017

Abstract

A pilot fuel nozzle for a combustor includes an igniter forming a central body extending along a longitudinal center of the nozzle. A nozzle tip includes a plurality of circumferentially spaced fuel passages and a plurality of circumferentially spaced air passages extending to an outer side of the nozzle tip. The central body extends through a center of the nozzle tip for producing a spark to ignite a fuel/air mixture adjacent to the nozzle tip. A plurality of fuel tubes extend along the central body, each of the fuel tubes having an outlet end engaged on the nozzle tip for delivery of fuel from the nozzle tip into a combustion chamber of the combustor An outer sleeve surrounds the fuel tubes and defines an annular space in fluid communication with the air passages of the nozzle tip between the outer sleeve and the central body.

First claim

What is claimed is:

1. A fuel nozzle for operation in a combustor, the fuel nozzle including:
a central body, the central body defining a generally cylindrical shape having an outer diameter;
a nozzle tip located at an end of the central body;
fuel tubes extending along the outer diameter of the central body, each of the fuel tubes having an outlet end engaged on the nozzle tip for delivery of fuel from the nozzle tip into a combustion chamber of the combustor;
an outer sleeve surrounding the fuel tubes and forming an annular space between the outer sleeve and the central body,
wherein the fuel tubes extend longitudinally in the annular space to form respective flows of fuel in the annular space,
the annular space fluidly coupled to receive air that forms a flow of air in the annular space, wherein the annular space forms a common conduit space for the respective flows of fuel and the flow of air,
wherein the fuel tubes are configured in a spiral, extending longitudinally along and circumferentially around the central body, and
wherein the central body is an igniter having a distal end at the nozzle tip for producing a spark to ignite a fuel/air mixture adjacent to the nozzle tip.

2. The fuel nozzle of claim 1 , wherein the fuel tubes are spaced equidistant from each other circumferentially around the central body.

3. The fuel nozzle of claim 2 , wherein three fuel tubes are spaced equidistant from each other.

4. The fuel nozzle of claim 1 , wherein the nozzle tip is a disk-shaped structure having an outer side and an inner side, fuel passages extend from the inner side to the outer side, and each of the fuel tubes includes an outlet end connected to a respective fuel passage.

5. The fuel nozzle of claim 4 , further including:
a source of air supplying the air to the annular space; and
air passages extending through the nozzle tip from an inner end of the air passages at the inner side to the outer side, the inner end of the air passages being open to the annular space for conveying air to the outer side of the nozzle tip.

6. The fuel nozzle of claim 5 , including a support member spanning from the outer sleeve to the central body at a longitudinal location between the source of air and the nozzle tip, the support member engaging the fuel tubes to locate the fuel tubes at a predetermined spacing from each of the outer sleeve and the central body.

7. The fuel nozzle of claim 6 , wherein the support member is an annular ring member including a plurality of perforations for passage of air from the air source to the nozzle tip.

8. The fuel nozzle of claim 1 , wherein the nozzle tip is a circular member that defines a nozzle tip diameter, and the fuel tubes are located within an imaginary circle circumscribed around the fuel tubes and defining a diameter that is no greater than the nozzle tip diameter.

9. The fuel nozzle of claim 1 , including a nozzle base having a fuel plenum receiving fuel from a fuel supply, and an end of each of the fuel tubes opposite from the nozzle tip is connected in fluid communication to the fuel plenum.

10. A pilot fuel nozzle for a combustor for a gas turbine engine, the pilot fuel nozzle including:
an igniter forming a central body extending along a longitudinal center of the pilot fuel nozzle and defining a generally cylindrical shape having an outer diameter;
a disk-shaped pilot fuel nozzle tip having circumferentially spaced fuel passages extending from an inner side to an outer side of the disk-shaped pilot fuel nozzle tip, and air passages which are circumferentially spaced, the air passages extending from the inner side to the outer side of the disk-shaped pilot fuel nozzle tip;
the central body having a distal end extending through a center of the disk-shaped pilot fuel nozzle tip for producing a spark to ignite a fuel/air mixture adjacent to the disk-shaped pilot fuel nozzle tip;
fuel tubes extending along the outer diameter of the central body, each of the fuel tubes having an outlet end engaged on the inner side of the disk-shaped pilot fuel nozzle tip for delivery of fuel from the disk-shaped pilot fuel nozzle tip into a combustion chamber of the combustor; and
an outer sleeve surrounding the fuel tubes and defining an annular space in fluid communication with the air passages of the disk-shaped pilot fuel nozzle tip between the outer sleeve and the central body,
wherein the fuel tubes extend longitudinally in the annular space to form respective flows of fuel in the annular space,
the annular space fluidly coupled to receive air that forms a flow of air in the annular space, wherein the annular space forms a common conduit space for the respective flows of fuel and the flow of air.

11. The pilot fuel nozzle of claim 10 , wherein the disk-shaped pilot fuel nozzle tip is a circular member that defines a pilot fuel nozzle tip diameter, and the fuel tubes are located within an imaginary circle circumscribed around the fuel tubes and defining a diameter that is no greater than the nozzle tip diameter.

12. The pilot fuel nozzle of claim 10 , including a pilot fuel nozzle base having a fuel plenum receiving fuel from a fuel supply, and an end of each of the fuel tubes opposite from the disk-shaped pilot fuel nozzle tip is connected in fluid communication to the fuel plenum.

13. The pilot fuel nozzle of claim 12 , wherein the outer sleeve includes an annular diffusion passage and an annular premix passage surrounding the fuel tubes, the diffusion passage and premix passage conveying respective gas flows from the pilot fuel nozzle base toward the disk-shaped pilot fuel nozzle tip.

14. The pilot fuel nozzle of claim 12 , wherein the central body is supported on the pilot fuel nozzle base.

15. The pilot fuel nozzle of claim 12 , including a support member spanning from the outer sleeve to the central body at a longitudinal location between the pilot fuel nozzle base and the disk-shaped pilot fuel nozzle tip, the support member engaging the fuel tubes to locate the fuel tubes at a predetermined spacing from each of the outer sleeve and the central body.

16. The pilot fuel nozzle of claim 15 , wherein the support member is an annular ring member including a plurality of perforations for passage of air from a location adjacent to the pilot fuel nozzle base to the nozzle tip.

17. The pilot fuel nozzle of claim 16 , including a source of air supplying the air to the annular space via the pilot fuel nozzle base.

18. The pilot fuel nozzle of claim 10 , wherein the fuel tubes are configured in a spiral, extending longitudinally along and circumferentially around the central body.

19. A fuel nozzle for operation in a combustor, the fuel nozzle including:
a central body, the central body defining a generally cylindrical shape having an outer diameter;
a nozzle tip located at an end of the central body;
fuel tubes extending along the outer diameter of the central body, each of the fuel tubes having an outlet end engaged on the nozzle tip for delivery of fuel from the nozzle tip into a combustion chamber of the combustor;
an outer sleeve surrounding the fuel tubes and forming an annular space between the outer sleeve and the central body,
wherein the fuel tubes extend longitudinally in the annular space to form respective flows of fuel in the annular space,
the annular space fluidly coupled to receive air that forms a flow of air in the annular space, wherein the annular space forms a common conduit space for the respective flows of fuel and the flow of air,
wherein the nozzle tip is a disk-shaped stru

Assignees

• Siemens Ag

Inventors

• Williams Steven
• Fox Timothy A
• Schilp Reinhard

Classifications

• F02C7/266

  Electric (sparking plugs H01T) · CPC title

• F23D11/38

  Nozzles; Cleaning devices therefor · CPC title

• F23R3/38

  comprising rotary fuel injection means · CPC title

• F23R3/36

  Supply of different fuels · CPC title

• F23D3/22

  Devices for mixing evaporated fuel with air · CPC title