Premix burner of the multi-cone type for a gas turbine

Patent metadata

Field	Value
Publication number	US-9441837-B2
Application number	US-201313937502-A
Country	US
Kind code	B2
Filing date	Jul 9, 2013
Priority date	Jul 10, 2012
Publication date	Sep 13, 2016
Grant date	Sep 13, 2016

Abstract

The invention relates to a premix burner of the multi-cone type for a gas turbine that includes a plurality of shells which are arranged around a central burner axis and are parts of a virtual, axially extending common cone, which opens in a downstream direction, whereby said parts are displaced perpendicular to said burner axis such that a tangential slot is defined between each pair of adjacent shells. The flame front of such a burner is stabilized by providing a virtual common cone with a cone angle, which varies in axial direction.

First claim

What is claimed is:

1. A premix burner for a gas turbine, said premix burner comprising:
a plurality of shells, which are arranged around a central burner axis of the premix burner and are parts of a virtual, axially extending common cone, which opens in a downstream direction,
wherein said shells are oriented perpendicular to said central burner axis such that a tangential slot is defined between each pair of adjacent shells, and
wherein said virtual common cone has a cone angle which varies in axial direction;
each of the shells having an upstream end and a downstream end, the upstream end being twisted around the central burner axis by a twist angle relative to the downstream end.

2. The premix burner according to claim 1 , wherein the cone angle of the virtual common cone increases in the downstream direction.

3. The premix burner according to claim 1 , comprising cylindrical gas channels attached to the shells, each of the gas channels defining straight inclined paths along which premix gas is passable.

4. The premix burner according to claim 3 , wherein each of the shells have holes through which premix gas from the gas channels is injectable to mix with air entering an interior defined by the shells via the tangential slots.

5. The premix burner according to claim 4 , wherein the twist angle is equal to or larger than 30°.

6. The premix burner according to claim 4 , wherein the twist angle is equal to or larger than 60°.

7. The premix burner according to claim 1 , wherein the shells comprise four shells.

8. The premix burner according to claim 1 , wherein each of the shells is equipped with a premix gas channel extending along an axially oriented edge of the respective shell such that a gas is injectable from said premix gas channel through gas injection holes into a stream of air entering an interior defined by the shells through the tangential slots.

9. The premix burner according to claim 8 , wherein said premix gas channels each have a cylindrical shape.

10. A premix burner for a gas turbine, comprising:
a plurality of shells positioned around a central burner axis of the premix burner, the shells spaced apart from each other to define slots between adjacent shells, each of the slots being defined around the central burner axis;
each of the shells having a downstream end and an upstream end, the upstream end being twisted around the central burner axis relative to the downstream end about a twist angle;
each of the shells being attached to an inclined linear gas channel through which premix gas is passable.

11. The premix burner of claim 10 , wherein the shells define an interior, each of the shells have holes through which the premix gas is injectable into an air stream entering into the interior via the slots.

12. The premix burner of claim 10 , wherein the twist angle is equal to or larger than 30°.

13. The premix burner of claim 10 , wherein the twist angle is equal to or larger than 60°.

14. The premix burner of claim 10 , wherein each of the shells has a bell-type shape.

15. The premix burner of claim 10 , comprising:
a fuel lance positioned adjacent to the shells.

16. The premix burner of claim 15 , wherein the central burner axis passes through the fuel lance.

17. The premix burner of claim 10 , wherein the shells are shaped to define a varying burner swirl number that varies along the central burner axis.

18. The premix burner of claim 10 , wherein the premix burner is configured without a bluff body.

19. The premix burner of claim 10 , wherein the shells define an increasing gradient of swirl strength along the central burner axis.

Assignees

• Alstom Technology Ltd
• General Electric Technology Gmbh

Inventors

• Pasqualotto Ennio
• Genin Franklin Marie
• Hellat Jaan

Classifications

• F23R3/286 Primary

  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

• F23C2900/07002

  Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners · CPC title

• F23D14/46

  Details · CPC title

• F23D14/02 Primary

  Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone · CPC title