Fuel injection device for a gas turbine having streamlined bodies with lobe structure

Patent metadata

Field	Value
Publication number	US-10422283-B2
Application number	US-201615041958-A
Country	US
Kind code	B2
Filing date	Feb 11, 2016
Priority date	Feb 11, 2015
Publication date	Sep 24, 2019
Grant date	Sep 24, 2019

Abstract

A fuel injection device for a gas turbine can include streamlined bodies arranged adjacent to one another in a circumferential direction. Each streamlined body can have a fuel nozzle on its trailing edge. The streamlined bodies can be split into at least a first group of streamlined bodies and a second group of streamlined bodies. All the streamlined bodies in the first group being the same and being different from the streamlined bodies in the second group. The first group of streamlined bodies includes at least two streamlined bodies adjacent to one another. Alternatively, the streamlined bodies are clustered in sets of two adjacent streamlined bodies. As yet another alternative, the streamlined bodies can be arranged such that the fuel injection device has a maximum of four-fold rotational symmetry in the plane perpendicular to the central axis.

First claim

The invention claimed is:

1. A fuel injection device for a gas turbine, comprising:
a plurality of streamlined bodies arranged in a ring adjacent to one another in a circumferential direction relative to a central axis of the fuel injection device, each streamlined body having a trailing edge and at least one streamlined body having a fuel nozzle on the trailing edge;
wherein the plurality of streamlined bodies is split into at least a first group of streamlined bodies and a second group of streamlined bodies; all the streamlined bodies in the first group being the same and being different in lobe structure from the streamlined bodies in the second group, and all the streamlined bodies in the second group being the same;
wherein the streamlined bodies are arranged such that the fuel injection device has a maximum of four-fold rotational symmetry in a plane perpendicular to the central axis.

2. The fuel injection device of claim 1 , wherein
the streamlined bodies of the first group have a right-handed lobe structure, and the streamlined bodies of the second group have a left-handed lobe structure.

3. The fuel injection device of claim 2 , wherein the first group and the second group each have the same number of streamlined bodies.

4. The fuel injection device of claim 2 , wherein the second group comprises: at least two streamlined bodies adjacent to one another in the circumferential direction, or in which all the streamlined bodies are the same radial distance from the central axis.

5. The fuel injection device of claim 2 , in which at least half of the streamlined bodies are opposite a different streamlined body relative to the central axis.

6. The injection device of claim 2 , in which each of the streamlined bodies of the first group has at least one fuel nozzle and each of the streamlined bodies of the second group has at least one fuel nozzle, and the at least one fuel nozzle of the first group has a different size to the at least one fuel nozzle of the second group.

7. A gas turbine comprising: the fuel injection device of claim 2 .

8. The gas turbine of claim 7 , comprising: at least one damper downstream of the fuel injection device arranged to reduce vibrations and/or pulsations caused by circumferential thermoacoustic modes.

9. A method of designing a gas turbine combustor, comprising:
manufacturing a fuel injection device according to claim 2 ;
installing the fuel injection device in a gas turbine; monitoring the gas turbine to ascertain where to add dampers to the gas turbine combustor to reduce vibrations and/or pulsations caused by circumferential thermoacoustic modes; and
adding at least one damper into the gas turbine combustor to reduce vibrations and/or pulsations caused by circumferential thermoacoustic modes.

10. The fuel injection device of claim 1 , in which the first group is split into at least two sectors and the second group is split into at least two sectors, and the sectors a of the first group and sectors b of the second group are arranged in a configuration abab around the ring such that each sector b of the second group is between sectors a of the first group.

11. The fuel injection device of claim 1 , wherein the plurality of streamlined bodies additionally comprises: a third group of streamlined bodies, all the streamlined bodies in the third group being the same and the streamlined bodies of the third group being different in lobe structure from the streamlined bodies in the first group and the streamlined bodies of the third group being different in lobe structure from the streamlined bodies of the second group.

12. The fuel injection device of claim 1 , in which the trailing edges of the first group are arranged into lobes and have a lobe combination, and in which the trailing edges of the second group are arranged into lobes.

13. The fuel injection device of claim 1 , in which the trailing edges of the first group are arranged into lobes and in which the trailing edges of the second group are arranged into lobes, each of the lobes of the first group being one of: a full lobe and a half lobe, each of the lobes of the second group being one of: a full lobe and a half lobe.

14. The fuel injection device of claim 1 , wherein all the streamlined bodies are the same radial distance from the central axis.

15. The fuel injection device of claim 14 , wherein each of the streamlined bodies of the first group has at least one fuel nozzle and each of the streamlined bodies of the second group has at least one fuel nozzle, and the at least one fuel nozzle of the first group has a different size to the at least one fuel nozzle of the second group.

16. The fuel injection device of claim 15 , in which the first group is split into at least two sectors and the second group is split into at least two sectors, and the sectors a of the first group and sectors b of the second group are arranged in a configuration abab around the ring such that each sector b of the second group is between sectors a of the first group.

17. The fuel injection device of claim 14 , wherein the plurality of streamlined bodies additionally comprises: a third group of streamlined bodies, all the streamlined bodies in the third group being the same and the streamlined bodies of the third group being different in lobe structure from the streamlined bodies in the first group and the streamlined bodies of the third group being different in lobe structure from the streamlined bodies of the second group.

18. The fuel injection device of claim 17 , in which the trailing edges of the first group are arranged into lobes and in which the trailing edges of the second group are arranged into lobes.

19. A method of operating a fuel injection device for a gas turbine, the fuel injection device having a plurality of streamlined bodies arranged in a ring adjacent to one another in a circumferential direction relative to a central axis of the fuel injection device, each streamlined body having a trailing edge and at least one streamlined body having a fuel nozzle on the trailing edge; wherein the plurality of streamlined bodies is split into at least a first group of streamlined bodies and a second group of streamlined bodies; all the streamlined bodies in the first group being the same and being different in lobe structure from the streamlined bodies in the second group, and all the streamlined bodies in the second group being the same; wherein the streamlined bodies are arranged such that the fuel injection device has a maximum of four-fold rotational symmetry in a plane perpendicular to the central axis, the method comprising:
injecting fuel through the fuel nozzle.

20. The method of claim 19 , wherein each of the streamlined bodies of the first group has at least one fuel nozzle and each of the streamlined bodies of the second group has at least one fuel nozzle, and wherein the injecting fuel through the fuel nozzle comprises:
injecting fuel at different rates through at least one fuel nozzle of the first group of streamlined bodies and at least one fuel nozzle of the second group of streamlined bodies.

Assignees

• Ansaldo Energia Switzerland AG

Inventors

• Yang Yang
• Noiray Nicolas
• Dusing Michael

Classifications

• F23R3/38 Primary

  comprising rotary fuel injection means · CPC title

• F23R3/20 Primary

  incorporating fuel injection means · CPC title

• F23R2900/00014

  Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators · CPC title

• F23R3/34

  Feeding into different combustion zones · CPC title

• F02C7/222 Primary

  Fuel flow conduits, e.g. manifolds · CPC title