Recessed fuel injector positioning

Patent metadata

Field	Value
Publication number	US-9816707-B2
Application number	US-201314647248-A
Country	US
Kind code	B2
Filing date	Nov 11, 2013
Priority date	Dec 11, 2012
Publication date	Nov 14, 2017
Grant date	Nov 14, 2017

Abstract

A combustion chamber for a gas turbine is provided. The combustion chamber has a pilot burner device, a fuel injector and an ignitor unit. The pilot burner device has a pilot body with a pilot surface which is facing an inner volume of the combustion chamber. The fuel injector has a fuel outlet for injecting a fuel into the inner volume. The ignitor unit is adapted for igniting the fuel inside the inner volume, wherein the ignitor unit is arranged at the pilot surface such that fuel which passes the ignitor unit is ignitable. The pilot body includes a recess, wherein the fuel outlet is arranged within the recess.

First claim

The invention claimed is:

1. A combustion chamber for a gas turbine, the combustion chamber comprising
a pilot burner device comprising a pilot body with a pilot surface which is facing an inner volume of the combustion chamber, wherein the pilot burner device further comprises a centre axis,
a fuel injector comprising a fuel outlet for injecting a fuel into the inner volume,
an ignitor unit for igniting the fuel inside the inner volume,
wherein the ignitor unit is arranged at the pilot surface such that fuel which passes the ignitor unit is ignitable,
wherein the pilot body comprises a recess comprising a base area spaced from a section of the pilot surface surrounding the recess and a lateral surface that connects the base area to the pilot surface,
wherein the fuel outlet is arranged within the recess, and wherein the recess is located off-centred from the centre axis, and
an air blast injector for injecting an air blast into the inner volume,
wherein the ignitor unit is located outside of the recess,
wherein the air blast injector comprises an air blast outlet which is arranged in the recess and arranged circumferentially adjacent to the fuel outlet with respect to a circumferential direction of the combustion chamber, and
wherein the air blast injector is configured to direct the air blast in the circumferential direction toward the fuel outlet and then the ignitor unit, which is effective to direct the fuel to the ignitor unit.

2. The combustion chamber according to claim 1 ,
wherein the fuel outlet is arranged at a bottom surface of the recess.

3. The combustion chamber according to claim 1 ,
wherein the fuel outlet is arranged at the lateral surface.

4. The combustion chamber according to claim 1 ,
wherein the lateral surface comprises a curved shape.

5. The combustion chamber according to claim 1 ,
wherein the base area comprises a circular, elliptical or rectangular profile.

6. The combustion chamber according to claim 1 ,
wherein the fuel injector, the ignitor unit and the air blast injector are arranged along the circumferential direction around the centre axis of the pilot burner device.

7. The combustion chamber according to claim 1 ,
wherein the fuel injector comprises a fuel nozzle at the fuel outlet such that the fuel is injectable in an atomized manner.

8. The combustion chamber according to claim 1 ,
wherein the air blast outlet is formed for injecting the air blast with an air blast spray cone.

9. The combustion chamber according to claim 1 ,
wherein the pilot body comprises a first passage which connects the inner volume with an environment of the pilot burner device,
wherein the fuel injector is inserted into the first passage,
wherein the pilot body further comprises a second passage which connects the inner volume with the environment of the pilot burner device,
wherein the air blast injector is inserted into the second passage.

10. The combustion chamber according to claim 8 ,
wherein the pilot body comprises a common passage which connects the inner volume with an environment of the pilot burner device,
wherein the fuel injector and the air blast injector are inserted into the common passage.

11. A method for operating a combustion chamber, the method comprising
injecting a fuel into an inner volume of the combustion chamber by a fuel injector comprising a fuel outlet,
wherein the combustion chamber comprises a pilot burner device comprising a pilot body with a pilot surface which is exposable to a flame in the inner volume of the combustion chamber and a recess comprising a base area spaced from a section of the pilot surface surrounding the recess and a lateral surface that connects the base area to the pilot surface,
igniting the fuel inside the inner volume by an ignitor unit,
wherein the ignitor unit is arranged at the pilot surface such that fuel which passes the ignitor unit is ignitable,
wherein the fuel outlet is formed for directing the fuel in the direction to the ignitor unit,
wherein the fuel outlet is arranged inside the recess,
wherein the ignitor unit is located outside of the recess, and
directing an air blast into the inner volume of the combustion chamber by an air blast injector located in the recess and comprising an air blast outlet arranged at the pilot surface or at the base area and arranged circumferentially adjacent to the fuel outlet with respect to a circumferential direction of the combustion chamber, wherein the air blast injector is configured to direct the air blast in the circumferential direction toward the fuel outlet and then the ignitor unit, which is effective to direct the fuel to the ignitor unit.

12. A combustion chamber for a gas turbine, the combustion chamber comprising
a pilot burner device comprising a pilot body with a pilot surface which is facing an inner volume of the combustion chamber, wherein the pilot burner device further comprises a centre axis,
a fuel injector comprising a fuel outlet for injecting a fuel into the inner volume,
an ignitor unit for igniting the fuel inside the inner volume,
wherein the ignitor unit is arranged at the pilot surface such that fuel which passes the ignitor unit is ignitable,
wherein the pilot body comprises a recess comprising a base area spaced from a section of the pilot surface surrounding the recess and a lateral surface that connects the base area to the pilot surface, wherein the fuel outlet is arranged within the recess, and wherein the recess is located off-centred from the centre axis, and
an air blast injector for injecting an air blast into the inner volume,
wherein the ignitor unit is located in the recess,
wherein the air blast injector comprises an air blast outlet which is arranged outside of the recess and arranged circumferentially adjacent to the fuel outlet with respect to a circumferential direction of the combustion chamber, and wherein the air blast injector is configured to direct the air blast in the circumferential direction toward the fuel outlet and then the ignitor unit, which is effective to direct the fuel to the ignitor unit.

13. The combustion chamber according to claim 12 , further comprising
a further air blast injector for injecting a further air blast into the inner volume, and
wherein the further air blast injector comprises a further air blast outlet which is arranged at the pilot body such that the further air blast is injectable in the direction to the fuel outlet and the ignitor unit for directing the fuel to the ignitor unit.

Assignees

• Siemens Ag

Inventors

• Dolmansley Timothy

Classifications

• F23D11/24

  by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space · CPC title

• F02C7/26

  Starting; Ignition · CPC title

• F23R3/12

  inducing a vortex · CPC title

• F23Q9/00

  Pilot flame igniters · CPC title

• F02C7/266

  Electric (sparking plugs H01T) · CPC title