Combustor burner arrangement

Patent metadata

Field	Value
Publication number	US-10533748-B2
Application number	US-201515305450-A
Country	US
Kind code	B2
Filing date	Apr 30, 2015
Priority date	May 2, 2014
Publication date	Jan 14, 2020
Grant date	Jan 14, 2020

Abstract

A fuel lance for a burner of a combustor has a fuel lance body defining a fuel flow passage and a liquid fuel tip attached thereto and in flow communication with fuel flow passage. The liquid fuel tip has a fuel outlet and an array of air passages having outlets which are arranged outside a blank sector of a circumference around the fuel outlet, the blank sector defined by an angle from 30° to 160°. A burner includes the fuel lance and the igniter and a main air flow passage to direct at least a part of a main air flow over the fuel lance and over the igniter, the blank sector has a centre-line angled between +120° and −120° from a radial line from the axis and passing through the fuel lance. A method includes rotating the fuel lance between a start-up condition and a second condition.

First claim

What is claimed is:

1. A burner for a combustor of a gas turbine, the burner comprising:
a burner longitudinal axis, a pilot burner, and a main burner;
wherein the pilot burner comprises a body;
wherein the body comprises a fuel lance, an igniter, and an end wall, the end wall comprising an end wall surface;
wherein the fuel lance comprises a liquid fuel tip and a fuel lance body, the liquid fuel tip being attached to the fuel lance body, the fuel lance body defining a fuel flow passage and a lance axis, wherein the liquid fuel tip comprises a fuel outlet and an array of air passages comprising air passage outlets arranged about the fuel outlet, wherein liquid fuel flows through the fuel flow passage and the liquid fuel tip and issues from the fuel outlet, wherein the air passage outlets are arranged outside a blank sector of a circumference around the fuel outlet, wherein the blank sector is defined by an angle between and including 30° and 160° about the lance axis, and wherein air from the air passage outlets impinges on the liquid fuel issuing from the fuel outlet and creates an asymmetric pilot vortex of the liquid fuel and air,
wherein the main burner comprises a swirler arrangement comprising an annular array of swirler vanes defining main air flow passages therebetween;
wherein the annular array of swirler vanes are arranged about the burner longitudinal axis, and wherein each main air flow passage is configured to direct a respective portion of a main air flow radially inward toward the burner longitudinal axis on a downstream side of the air passage outlets to form the main air flow,
wherein the air passage outlets and the fuel outlet are located in the end wall,
wherein the igniter is at least partly housed within the end wall and comprises an end face, the end face is located at the end wall surface,
wherein the main air flow passages are arranged to direct at least a part of the main air flow over the fuel lance and then over the igniter, and
wherein the blank sector comprises a center-line and the center-line is angled between +120° and −120° from a radial line from the burner longitudinal axis and passing through the fuel lance.

2. The burner as claimed in claim 1 ,
wherein the main air flow passages are tangentially angled relative to the burner longitudinal axis to create a clockwise swirl direction or an anticlockwise swirl direction of the main air flow, and
wherein the array of air passages is tangentially angled relative to the lance axis to create the clockwise or the anticlockwise swirl direction of the asymmetric pilot vortex.

3. The burner as claimed in claim 2 ,
wherein the main air flow passages and the array of air passages are both tangentially angled in the same direction to create the clockwise swirl direction of the main air flow and the clockwise swirl direction of the asymmetric pilot vortex or to create the anticlockwise swirl direction of the main air flow and the anticlockwise swirl direction of the asymmetric pilot vortex, and
wherein the center-line of the blank sector is angled up to 60° from the radial line.

4. The burner as claimed in claim 3 ,
wherein the center-line of the blank sector is angled up to 20° from the radial line.

5. The burner as claimed in claim 3 ,
wherein the center-line of the blank sector is angled approximately 0° from the radial line.

6. The burner as claimed in claim 2 ,
wherein the main air flow passages and the array of air passages are oppositely tangentially angled so the main air flow and the asymmetric pilot vortex swirl opposite each other, and
wherein the center-line of the blank sector is angled between 0° and 120° from the radial line.

7. The burner as claimed in claim 2 ,
wherein the igniter is positioned downstream of the fuel lance with respect to a direction of the main air flow.

8. The burner as claimed in claim 1 ,
wherein the liquid fuel tip outlet comprises one of a fuel prefilmer, an orifice, or a number of orifices.

9. The burner as claimed in claim 1 , further comprising:
a rotation mechanism arranged to rotate the fuel lance about the lance axis.

10. A method of operating a burner for a combustor of a gas turbine, the burner comprising a burner longitudinal axis, a pilot burner, and a main burner, the pilot burner comprising a body, the body comprising each of an end wall, a fuel lance, and an igniter, the end wall comprising an end wall surface, the fuel lance comprising a fuel lance body and a liquid fuel tip attached to the fuel lance body, the fuel lance body defining a fuel flow passage and a lance axis, the liquid fuel tip comprising a fuel outlet and an array of air passages, the array of air passages comprising air passage outlets arranged about the fuel outlet, wherein liquid fuel flows through the fuel flow passage and the liquid fuel tip and issues from the fuel outlet, the air passage outlets being arranged outside a blank sector of a circumference around the fuel outlet, wherein the blank sector is defined by an angle between and including 30° and 160° about the lance axis, and wherein air from the air passage outlets impinges on the liquid fuel issuing from the fuel outlet and creates an asymmetric pilot vortex of the liquid fuel and air, the burner further comprising a rotation mechanism arranged to rotate the fuel lance about the lance axis, the main burner further comprising a swirler arrangement comprising an annular array of swirler vanes defining main air flow passages therebetween, wherein the annular array of swirler vanes are arranged about the burner longitudinal axis, wherein each main air flow passage is configured to direct a respective portion of a main air flow radially inward toward the burner longitudinal axis on a downstream side of the air passage outlets to form the main air flow, wherein the air passage outlets and the fuel outlet are located in the end wall, wherein the igniter is at least partly housed within the end wall and comprises an end face, the end face is located at the end wall surface, wherein the main air flow passages are arranged to direct at least a part of the main air flow over the fuel lance and then over the igniter;
the method comprising rotating the fuel lance between a start-up condition and a second condition.

11. The method as claimed in claim 10 ,
wherein at the start-up condition the center-line is angled between +120° and −120° from a radial line from the burner longitudinal axis and passing through the fuel lance and
wherein at the second condition the center-line is angled between +240° and 0° from the radial line.

12. The method as claimed in claim 11 ,
wherein the second condition comprises one of weak extinction, part-load or maximum load.

13. The method as claimed in claim 10 ,
wherein the liquid fuel tip outlet comprises one of a fuel prefilmer, an orifice, or a number of orifices.

Assignees

• Siemens Ag

Inventors

• Stevenson Imogen
• Bickerton Ronald
• Dolmansley Timothy

Classifications

• F23R3/04 Primary

  Air inlet arrangements · CPC title

• F23D11/12 Primary

  characterised by the shape or arrangement of the outlets from the nozzle · CPC title

• F02C7/264

  Ignition · CPC title

• F23R2900/00004

  Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits · CPC title

• F23R3/286

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