Combustion chamber of a gas turbine, gas turbine and method for operating the same

Patent metadata

Field	Value
Publication number	US-12298007-B2
Application number	US-201916601146-A
Country	US
Kind code	B2
Filing date	Oct 14, 2019
Priority date	Oct 18, 2018
Publication date	May 13, 2025
Grant date	May 13, 2025

Abstract

A combustion chamber of a gas turbine combusts a fuel in the presence of combustion air. The combustion chamber is configured as dual-fuel combustion chamber, wherein the combustion chamber, in a gas fuel operating mode, is supplied with a mixture of a gaseous fuel and combustion air via a main swirl body. In a liquid fuel operating mode, the combustion chamber is supplied with a liquid fuel via an atomization apparatus and combustion air via the main swirl body. The atomization apparatus has an atomization lance with an atomization nozzle centrally arranged with respect to a longitudinal center axis of a prechamber of the combustion chamber. The atomization nozzle of the central atomization lance includes a swirl chamber and, downstream of the swirl chamber, a nozzle orifice. The swirl chamber is supplied with the liquid fuel via a radial swirl generator and an axial swirl generator.

First claim

The invention claimed is:

1. A combustion chamber of a gas turbine, for combusting a fuel in the presence of combustion air, the combustion chamber being configured as a dual fuel combustion chamber, comprising:
a main swirl body;
an atomization apparatus arranged entirely upstream of the main swirl body having an atomization lance having an outer cylinder and an inner cylinder that is coaxially arranged with respect to the outer cylinder that comprises an atomization nozzle, the atomization nozzle comprising a swirl chamber and, downstream of the swirl chamber, a nozzle orifice;
a prechamber downstream of the main swirl body, wherein the prechamber diameter is smaller than a main swirl body diameter;
a radial swirl generator arranged in the inner cylinder of the atomization lance;
and an axial swirl generator arranged in the inner cylinder of the atomization lance upstream of the atomization nozzle and the radial swirl generator,
wherein the combustion chamber is configured such that:
in a gas fuel operating mode the combustion chamber is supplied with a mixture of gaseous fuel and the combustion air via the main swirl body, and
in a liquid fuel operating mode the combustion chamber is supplied with liquid fuel via the atomization apparatus and supplied with the combustion air via the main swirl body,

wherein the atomization nozzle is arranged centrally with respect to a longitudinal center axis of the combustion chamber, or arranged on a longitudinal center axis of the prechamber,
wherein the swirl chamber is configured to be supplied with the liquid fuel via the radial swirl generator and the axial swirl generator,
wherein the atomization apparatus comprises multiple atomization nozzles that are arranged in a decentralized manner with respect to the longitudinal center axis of the combustion chamber, or arranged in a decentralized manner with respect to the longitudinal center axis of the prechamber, wherein the decentralized multiple atomization nozzles are inactive during igniting and starting up, and to be switched on once a no-load rotational speed has been reached,
wherein both the central atomization lance and the decentralized multiple atomization nozzles are, in the liquid fuel operating mode, utilized throughout an operating range between no load and full load to supply the liquid fuel to the combustion chamber,
wherein with increasing load starting from the no load, the decentralized multiple atomization nozzles introduce the liquid fuel into the combustion chamber in a continuously increasing quantity,
wherein with the increasing load starting from the no load, the central atomization lance introduces the liquid fuel into the combustion chamber initially at a constant level and then at a level that decreases, but without being deactivated even at the full load,
wherein the central atomization lance comprises a hood-like portion that has a first segment that extends axially from the outer cylinder of the central atomization lance, a second segment that extends radially inward, and an arcuate segment between the first and second segments,
wherein:
the hood like portion defines a chamber arranged downstream of the nozzle orifice of the atomization nozzle of the central atomization lance and upstream of an outlet opening of the central atomization lance,
the outlet opening is defined by the second segment of the hood, and
a second radial swirl generator is arranged in the outer cylinder of the atomization lance upstream of the atomization nozzle that supplies the chamber with the combustion air, so as to bypass the main swirl body via a bypass,
wherein the chamber is supplied with the liquid fuel from the swirl chamber via the nozzle orifice, and
wherein the second radial swirl generator supplies the chamber with the combustion air at full load so as to stabilize the spray cone by the introduction of the combustion air into the chamber by the second radial swirl generator, and
wherein the outlet opening of the central atomization lance and respective outlets of the decentralized multiple atomization nozzles are arranged on a same plane at an upstream end of the combustion chamber and radially within the main swirl body, and
wherein an upstream end of the main swirl body is arranged on the same plane and the downstream end of the main swirl body is entirely upstream end of the prechamber.

2. The combustion chamber according to claim 1 , wherein the radial swirl generator is supplied with the liquid fuel via a first fuel line and the axial swirl generator is supplied with the liquid fuel via a second fuel line.

3. The combustion chamber according to claim 2 , wherein the first fuel line has a first fuel valve and the second fuel line has a second fuel valve.

4. The combustion chamber according to claim 3 , wherein
the atomization nozzle of the central atomization lance provides an atomization cone with a spray angle (β) of greater than 60° and smaller than 100° in a case in which the first fuel valve is open, the second fuel valve is closed and the liquid fuel is supplied to the swirl chamber exclusively via the radial swirl generator, and
the atomization nozzle provides an atomization cone with a spray angle (β) of greater than 40° and smaller than 60° in a case in which the first and second fuel valve are both open and the liquid fuel is supplied to the swirl chamber via the axial and radial swirl generators.

5. The combustion chamber according to claim 4 , wherein the combustion air that can be supplied to the combustion chamber while bypassing the main swirl body via the chamber between the nozzle orifice and the atomization nozzle and the hood-like portion is between 1% and 10% of the combustion air that can be supplied to the combustion chamber via the main swirl body.

6. The combustion chamber according to claim 5 , wherein the decentralized multiple atomization nozzles are positioned on a circular path or pitch circle path extending about the longitudinal center axis of the combustion chamber or about the longitudinal center axis of the prechamber.

7. The combustion chamber according to claim 6 , wherein a center point of the circular path or pitch circle path, on which the decentralized multiple atomization nozzles are positioned, is positioned on the longitudinal center axis of the combustion chamber or on the longitudinal center axis of the prechamber, wherein a radius of the circular path or pitch circle path, on which the decentralized multiple atomization nozzles are positioned, is between 0.4 times and 1.1 times an inner radius of the main swirl body.

8. The combustion chamber according to claim 7 , wherein the decentralized multiple atomization nozzles each provide an atomization cone with a spray angle (ψ) of greater than 25° and smaller than 90°.

9. The combustion chamber according to claim 8 , wherein the decentralized multiple atomization nozzles are configured as self-exciting nozzles providing an oscillating fluid jet.

10. A gas turbine, comprising:
the combustion chamber according to claim 1 , and
a turbine configured to expand an exhaust gas produced during a combustion in the combustion chamber.

11. A method for operating the gas turbine according to claim 10 , comprising:
supplying, in the gas fuel operating mode, to the combustion chamber a mixture of the gaseous fuel and the combustion air via the main swirl body, and
supplying to the combustion chamber, in the liquid fuel operating mode:
the liquid fuel to the combustion chamber via the atomization apparatus, and
the liquid fuel and the combustion air via the main swirl body.

12. The method according to claim 11 , wherein for igniting the gas turbine in t

Assignees

• Man Energy Solutions Se

Inventors

• Cosic Bernhard
• Reiss Frank
• Proebster Roman

Classifications

• F02C7/22

  Fuel supply systems · CPC title

• F02C9/40

  specially adapted to the use of a special fuel or a plurality of fuels · CPC title

• F05D2240/36

  Fuel vaporizer · CPC title

• F23R3/30

  comprising fuel prevapourising devices · CPC title

• F23D11/383

  with swirl means · CPC title