Inclined fuel injection of fuel into a swirler slot

Patent metadata

Field	Value
Publication number	US-9810433-B2
Application number	US-201214374901-A
Country	US
Kind code	B2
Filing date	Dec 4, 2012
Priority date	Feb 15, 2012
Publication date	Nov 7, 2017
Grant date	Nov 7, 2017

Abstract

A combustor for a gas turbine is provided. The combustor includes a pre-combustion chamber having a center axis and a swirler which is mounted to the pre-combustion chamber. The swirler surrounds the pre-combustion chamber in a circumferential direction with respect to the center axis. The swirler has a bottom surface which forms a part of a slot through which oxidant/fuel mixture is injectable into the pre-combustion chamber, wherein the bottom surface is located in a bottom plane. The swirler further includes a fuel injector which is arranged to the bottom surface such that a fuel is injectable into the slot with a fuel injection direction, wherein a first component of the fuel injection direction is non-parallel to the normal (n) of the bottom plane.

First claim

The invention claimed is:

1. A combustor for a gas turbine, the combustor comprising:
a pre-combustion chamber having a center axis,
a swirler mounted to the pre-combustion chamber,
wherein the swirler surrounds the pre-combustion chamber in a circumferential direction with respect to the centre axis,
wherein the swirler comprises a bottom surface which forms a part of a slot through which an oxidant/fuel mixture is injectable into the pre-combustion chamber,
wherein the bottom surface is located within a bottom plane,
wherein the swirler further comprises a fuel injector which is arranged such that a fuel is injectable into the slot through the bottom surface with a fuel injection direction,
wherein a first component of the fuel injection direction is non-parallel to a normal (n) of the bottom plane,
wherein the fuel injector comprises an injection tube, said injection tube is aligned with respect to the bottom surface such that the fuel is injectable into the slot with the fuel injection direction, and
wherein the fuel injector is arranged such that an injection angle (Θ) between the bottom plane and the fuel injection direction is between 20° and 70°,
wherein the swirler comprises a vane comprising a side wall oriented transverse to the bottom surface and which forms a further part of the slot, wherein the fuel injector is arranged such that a second component of the fuel injection direction is into the slot and toward the side wall.

2. The combustor according to claim 1 , wherein the injection angle (Θ) is between 35° and 55°.

3. The combustor according to claim 1 , wherein the injection tube protrudes from the bottom surface into the slot.

4. The combustor according to claim 1 , wherein the second component of the fuel injection direction is perpendicular to the side wall.

5. The combustor according to claim 1 , wherein the swirler further comprises a further fuel injector, wherein said further fuel injector is arranged in the bottom surface.

6. The combustor according to claim 1 , wherein the bottom surface forms a part of a further slot through which a further oxidant/fuel mixture is injectable into the pre-combustion chamber, wherein the swirler further comprises an another fuel injector which is arranged in the bottom surface such that an another fuel is injectable into the further slot with a further fuel injection direction, and wherein a further first component of the further fuel injection direction is non-parallel to the normal (n) of the bottom plane.

7. The combustor according to claim 1 , further comprising a pilot burner, said pilot burner comprising a burner face, wherein the pilot burner comprises a pilot fuel injector which is arranged in the burner face for injecting a pilot fuel into the pre-combustion chamber.

8. The combustor according to claim 7 , wherein the burner face is located within the bottom plane.

9. The combustor of claim 1 , wherein the fuel injector is configured to ensure the fuel is injected against the side wall of the vane.

10. The combustor of claim 1 , wherein the second component is counter to a direction of a fluid flow through the slot.

11. A method for operating a combustor according to claim 1 , the method comprising injecting the fuel into the slot with the fuel injection direction.

Assignees

• Siemens Ag

Inventors

• Sadasivuni Suresh

Classifications

• 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

• F23D2900/14021

  Premixing burners with swirling or vortices creating means for fuel or air · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• F23C7/004

  using vanes · CPC title

• F23R3/286 Primary

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