Burner for a can combustor

Patent metadata

Field	Value
Publication number	US-10544939-B2
Application number	US-201715446407-A
Country	US
Kind code	B2
Filing date	Mar 1, 2017
Priority date	Oct 23, 2012
Publication date	Jan 28, 2020
Grant date	Jan 28, 2020

Abstract

A burner for a combustion chamber of a gas turbine with a mixing and injection device, which includes a limiting wall that defines a gas-flow channel and at least two streamlined bodies. Each streamlined body extends in a first transverse direction into the gas-flow channel, and has two lateral surfaces that are arranged essentially parallel to the main-flow direction. The lateral surfaces are joined to one another at their upstream and downstream sides to form leading and trailing edges of the body, respectively. At least one of the streamlined bodies includes a mixing structure and at least one fuel nozzle at its trailing edge for introducing at least one fuel essentially parallel to the main-flow direction into the flow channel. At least two of the streamlined bodies have different lengths along the first transverse direction such that they may be used for a can combustor.

First claim

What is claimed is:

1. A method for operating a burner, the burner comprising:
a mixing and injection device which includes:
a limiting wall that defines a gas-flow channel with a longitudinal axis, an inlet area, and downstream of the inlet area in a main-flow direction, an outlet area, wherein the gas-flow channel has a cross-section perpendicular to the main-flow direction, the cross-section being a substantially lensoid or elliptical cross-section; and
at least two streamlined bodies, each extending in a first transverse direction of the burner, from a first region of the limiting wall and perpendicularly to or at an inclination with respect to the main-flow direction into the gas-flow channel, wherein at least two of the at least two streamlined bodies have different lengths along the first transverse direction, wherein at least one streamlined body includes:
two lateral surfaces that are arranged substantially parallel to the main-flow direction with a central plane there between, wherein the two lateral surfaces are joined to one another at upstream sides of the two lateral surfaces to form a leading edge of the at least one streamlined body and are joined at downstream sides of the two lateral surfaces to form a trailing edge of the at least one streamlined body;
the at least one streamlined body extending perpendicularly to the main-flow direction and along the first transverse direction, and having a cross-section perpendicular to the first transverse direction that is shaped as a streamlined profile;
a mixing structure with at least two fuel nozzles located at the trailing edge, wherein the mixing structure is a plurality of lobes located at the trailing edge of the at least one streamlined body, wherein each lobe extends substantially perpendicular to a central plane in a second transverse direction or a third transverse direction, wherein the second and third transverse directions run oppositely to one another, and wherein lobe side walls include straight sections such that a lobed trailing edge is provided which includes the straight sections, wherein the at least two fuel nozzles are tilted to inject at least one fuel and/or a carrier gas at an inclination angle with respect to the main-flow direction ranging from 0° to 60°, the at least two fuel nozzles comprising at least one first fuel nozzle arranged closest to the limiting wall at the trailing edge of the at least one streamlined body, wherein the at least one first fuel nozzle is tilted so as to inject a fuel jet away from the limiting wall,

the method comprising:
determining a number of the at least one fuel nozzle, through which fuel is injected, as a function of a total injected fuel flow.

2. The method according to claim 1 , wherein, below a threshold fuel flow, the method comprises at least one of: injecting fuel only through every second fuel nozzle of a respective streamlined body; or injecting fuel through fuel nozzles of every second streamlined body of the at least two streamlined bodies, wherein the at least two streamlined bodies include three or more streamlined bodies, or injecting fuel through fuel nozzles of every third streamlined body of the at least two streamlined bodies, wherein the at least two streamlined bodies include four or more streamlined bodies.

3. The method according to claim 1 , comprising: combusting the at least one fuel, the at least one fuel being at least one fuel that contains hydrogen.

4. A burner for a combustion chamber of a gas turbine, the burner comprising a mixing and injection device that comprises:
a limiting wall that defines a gas-flow channel with a longitudinal axis, an inlet area, and an outlet area that is downstream from the inlet area in a main-flow direction, the gas-flow channel having a cross-section perpendicular to the main-flow direction, the cross-section being a substantially lensoid or elliptical cross section;
at least two streamlined bodies, each having two lateral surfaces that are arranged substantially parallel to the main-flow direction with a central plane there between, wherein the two lateral surfaces are joined to one another at upstream sides of the two lateral surfaces to form respective leading edges of the at least two streamlined bodies and are joined at downstream sides of the two lateral surfaces to form respective trailing edges edge of the at least two streamlined bodies, the at least one streamlined body extending perpendicularly to the main-flow direction and along a first transverse direction, at least one streamlined body of the at least two streamlined bodies having a cross-section perpendicular to the first transverse direction that is shaped as a streamlined profile, wherein at least two of the at least two streamlined bodies have different lengths along the first transverse direction; and
a mixing structure with at least two fuel nozzles located at the trailing edge, wherein the mixing structure is a plurality of lobes located at the trailing edge of the at least one streamlined body, wherein each lobe extends substantially perpendicularly to the central plane in a second transverse direction or a third transverse direction, wherein the second and third transverse directions run oppositely to one another, and wherein side walls of each lobe include straight sections such that the trailing edge is a lobed trailing edge which includes the straight sections, wherein the at least two fuel nozzles are tilted to inject at least one fuel and/or a carrier gas at an inclination angle with respect to the main-flow direction ranging from 0° to 60°, the at least two fuel nozzles comprising at least one first fuel nozzle arranged closest to the limiting wall at the trailing edge of the at least one streamlined body, wherein the at least one first fuel nozzle is tilted so as to inject a fuel jet away from the limiting wall.

5. The burner of claim 4 , wherein the plurality of lobes are provided as a combination of sectors in a shape of at least one of arcs of circles or sinusoidal curves, wherein the straight sections are asymptotic to the sinusoidal curves or arcs of circles.

6. The burner of claim 4 , wherein a transition of the at least one streamlined body in a downstream direction from a leading edge region to the plurality of lobes is smooth with a surface curvature representing a function with a continuous first derivative.

7. The burner of claim 6 , wherein a transverse displacement of the two lateral surfaces of the at least one streamlined body which forms the plurality of lobes is in a downstream two thirds of an axial length of the at least one streamlined body, the axial length being measured along the main-flow direction.

8. The burner of claim 6 , wherein a transverse displacement of the two lateral surfaces of the at least one streamlined body which forms the plurality of lobes is in a downstream half of an axial length of the at least one streamlined body, the axial length being measured along the main-flow direction.

9. The burner of claim 4 , wherein the lobed trailing edge is provided over an entirety of the length along the first transverse direction of the at least one streamlined body, and wherein the plurality of lobes are sequentially arranged along the trailing edge and alternatingly extend in the second transverse direction and the third transverse direction.

10. The burner of claim 9 , wherein the plurality of lobes include a lobe wave length that ranges from 20 millimeters to 100 millimeters.

11. The burner of claim 9 , wherein the plurality of lobes include a lobe wave length that ranges from 30 millimeters to 60 millimeters.

12. The burner of claim 4 , wherein
the streamlined profile has a width in the se

Assignees

• Ansaldo Energia Switzerland AG

Inventors

• Ciani Andrea
• Wood John Philip
• Pennell Douglas Anthony
• Freitag Ewald
• Benz Urs
• Theuer Andre

Classifications

• F23R3/34

  Feeding into different combustion zones · CPC title

• F23R2900/03341

  Sequential combustion chambers or burners · CPC title

• F23R3/20

  incorporating fuel injection means · CPC title

• F23R3/16 Primary

  with devices inside the flame tube or the combustion chamber to influence the air or gas flow · CPC title

• F02C6/003

  Gas-turbine plants with heaters between turbine stages · CPC title