PREMIXING NOZZLE WITH INTEGRAL LIQUID EVAPORATOR

• US 20160169110A1
• Filed: 11/11/2014
• Published: 06/16/2016
• Est. Priority Date: 11/11/2014
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: MYERS, GEOFFREY DAVID, SHERSHNYOV, BORYS, SUBBOTA, ANDREY, GERASIMOV, ALEXEY YURIEVICH, VYAZEMSKAYA, NATALYA IGOREVNA, VALEEV, ALMAZ
• Granted Patent: US 9,964,043 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F02C 3/30 Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases F02C7/141, F02C7/30, F01D21/00, F01K21/04, F23D11/10 take precedence
• CPC Class Codes: F02C 7/222 Fuel flow conduits, e.g. manifolds
• CPC Class Codes: F02C 9/26 Control of fuel supply F02C9/48 takes precedence; fuel valves F02C7/232
• CPC Class Codes: F02M 25/025 Adding water
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F23D 17/002 gaseous or liquid fuel
• CPC Class Codes: F23D 2900/00015 Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability
• CPC Class Codes: F23L 7/002 Supplying water
• CPC Class Codes: F23R 3/14 by using swirl vanes
• CPC Class Codes: F23R 3/286 having fuel-air premixing devices F23R3/30 takes precedence
• CPC Class Codes: F23R 3/343 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 Class Codes: F23R 3/36 Supply of different fuels
• CPC Class Codes: Y02T 10/12 Improving ICE efficiencies

Abstract

The present application provides a fuel nozzle for a gas turbine engine using a primary fuel and a secondary fuel. The fuel nozzle may include a number of primary fuel injection ports for the primary fuel, a water passage, a number of secondary fuel injection ports, and a secondary fuel evaporator system for atomizing the secondary fuel.

Claims

1. A fuel nozzle for a gas turbine engine using a primary fuel and a secondary fuel, comprising:

a plurality of primary fuel injection ports for the primary fuel;

a water passage;

a plurality of secondary fuel injection ports; and

a secondary fuel evaporator system for atomizing the secondary fuel.

2. The fuel nozzle of claim 1, further comprising a plurality of swirler vanes with the plurality of primary fuel injection ports positioned thereon.

3. The fuel nozzle of claim 2, wherein the plurality of swirler vanes are positioned about a premixing chamber.

4. The fuel nozzle of claim 1, wherein the primary fuel comprises a flow of natural gas.

5. The fuel nozzle of claim 1, wherein the water passage comprises a pilot liquid fuel passage.

6. The fuel nozzle of claim 5, wherein the pilot liquid fuel passage extends to a pilot tip.

7. The fuel nozzle of claim 6, wherein the pilot tip comprises a pilot swirler thereabout.

8. The fuel nozzle of claim 1, further comprising a secondary fuel passage in communication with the plurality of second fuel injectors.

9. The fuel nozzle of claim 8, wherein the secondary fuel comprises a flow of a liquid fuel.

10. The fuel nozzle of claim 1, wherein the secondary fuel evaporator system comprises an atomizer.

11. The fuel nozzle of claim 10, wherein the atomizer comprises an atomizer swirler.

12. The fuel nozzle of claim 11, wherein the atomizer swirler comprises a stem and a flange.

13. The fuel nozzle of claim 11, wherein the atomizer swirler comprises a plurality of slots therein.

14. The fuel nozzle of claim 11, wherein atomizer comprises a jacket with an orifice therein.

15. A method of operating a fuel nozzle for a gas turbine engine on either a primary fuel or a secondary fuel, comprising:

providing a flow of the primary fuel;

providing a flow of the secondary fuel;

flowing the secondary fuel through an atomizer;

atomizing the secondary fuel; and

combusting the atomized secondary fuel.

16. A fuel nozzle for a gas turbine engine using natural gas and/or a liquid fuel, comprising:

a plurality of swirler vanes with a plurality of natural gas injection ports for the natural gas;

a water passage;

a plurality of liquid fuel injection ports; and

a liquid fuel atomizer for atomizing the liquid fuel.

17. The fuel nozzle of claim 16, wherein the atomizer comprises an atomizer swirler.

18. The fuel nozzle of claim 17, wherein the atomizer swirler comprises a flange with a plurality of slots therein.

19. The fuel nozzle of claim 16, wherein atomizer comprises a jacket with an orifice therein.

20. The fuel nozzle of claim 16, wherein the water passage comprises a pilot liquid fuel passage.