Swirler for a burner of a gas turbine engine, burner of a gas turbine engine and gas turbine engine

Patent metadata

Field	Value
Publication number	US-2017051919-A1
Application number	US-201515305417-A
Country	US
Kind code	A1
Filing date	May 7, 2015
Priority date	May 9, 2014
Publication date	Feb 23, 2017
Grant date	—

Abstract

A swirler for a burner of a gas turbine engine, having a plurality of vanes extending from an outer radius of the swirler to an inner radius of the swirler and a plurality of mixing channels between the vanes to channel air from a radially outer end of the mixing channel, located essentially at an outer radius of the swirler, to a radially inner end of the mixing channel, located essentially at an inner radius of the swirler, at least one main injector for providing fuel for a main flame of the gas turbine engine, the main injector arranged at and/or in at least one of the mixing channels, and at least one pilot injector for providing fuel for a pilot flame of the gas turbine engine. A burner of a gas turbine engine and a gas turbine engine include the swirler.

First claim

What is claimed is:

1 . A swirler for a burner of a gas turbine engine, the swirler comprising:
a central axis, a base plate having a base plate surface, an annular array of vanes mounted on the base plate and each vane having a first side surface and a second side surface which meet at a trailing edge, wherein the first side surfaces, the second side surfaces the base plate surfaces define a plurality of mixing channels between the vanes to channel air from a radially outer end of the mixing channel to a radially inner end of the mixing channel, wherein at least one vane has a height and the trailing edge is at an inner radius from the central axis, at least one main injector for providing fuel for a main flame, the main injector arranged at and/or in at least one of the mixing channels, and at least one pilot injector for providing fuel for a pilot flame, wherein the at least one pilot injector has an outlet that is arranged within 30% of the height from the base plate surface and between 80% and 150% of the inner radius.

2 . The swirler according to claim 1 ,
wherein the at least one pilot injector is at least partly housed within or through an orifice in any one or more of the vane or base plate.

3 . The swirler according to claim 1 ,
wherein the at least one pilot injector is arranged radially inwardly of the at least one main fuel injector.

4 . The swirler according to claim 1 ,
wherein the at least one pilot injector is arranged at a distance from a center of the swirler of 100% to 120%, of the inner radius of the swirler.

5 . The swirler according to claim 1 ,
wherein the at least one pilot injector is at least partly arranged in a region between an extended plane of the first side surface and an extended plane of the second side surface.

6 . The swirler according to claim 1 ,
wherein the at least one pilot injector is constructed as a fuel injection lance.

7 . The swirler according to claim 6 ,
wherein the fuel injection lance comprises an angled tip.

8 . The swirler according to claim 1 ,
wherein the at least one pilot injector comprises pilot fuel injectors arranged relative to alternate mixing channels or vanes.

9 . The swirler according to claim 8 ,
wherein the at least one main injector comprises main fuel injectors arranged relative to alternate mixing channels.

10 . The swirler according to claim 1 ,
wherein the at least one pilot injector is arranged at and/or extends into the at least one mixing channel between 5% to 10% of the height of the trailing edge.

11 . The swirler according to claim 1 ,
wherein the swirler comprises at least two pilot injectors, the at least two pilot injectors arranged at or near different mixing channels of the swirler.

12 . The swirler according to claim 1 ,
wherein the at least one pilot injector and the at least one main injector are arranged at and/or in different mixing channels of the swirler.

13 . The swirler according to claim 1 ,
wherein the at least one pilot injector and the at least one main injector are arranged at different heights and/or extend into different heights of the respective at least one mixing channel of the swirler and/or cause fuel to penetrate to different heights of the respective at least one mixing channel of the swirler.

14 . A burner of a gas turbine engine, comprising
a swirler and a combustion chamber, wherein the swirler is constructed according to claim 1 .

15 . A gas turbine engine, comprising
at least one burner, wherein the burner is constructed according claim 14 .

16 . The swirler according to claim 6 ,
wherein the at least one pilot injector is constructed as a removable fuel injection lance.

17 . The swirler according to claim 13 ,
wherein the fuel penetrates to different heights of the respective at least one mixing channel of the swirler by regulation of an injection velocity.

Assignees

• Siemens Ag

Inventors

• Dolmansley Timothy

Classifications

• F23D14/24

  at least one of the fluids being submitted to a swirling motion · CPC title

• F23R3/286

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

• F23C7/002

  the air being submitted to a rotary or spinning motion (cyclonic combustion chamber F23C3/006) · CPC title

• F23R3/14 Primary

  by using swirl vanes · 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