Combustion Chamber Of A Gas Turbine, Gas Turbine And Method For Operating The Same

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.

Claims

1. A combustion chamber (1) of a gas turbine, for combusting a fuel in the presence of combustion air, the combustion chamber (1) being configured as a dual fuel combustion chamber, comprising: a main swirl body (2); an atomization apparatus (3) having an atomization lance (6) that comprises an atomization nozzle (7), the atomization nozzle (7) comprising a swirl chamber (9) and, downstream of the swirl chamber (9), a nozzle orifice (28); a prechamber (5); a radial swirl generator (10); and an axial swirl generator (11), wherein the combustion chamber (1) is configured such that: in a gas fuel operating mode the combustion chamber (1) is supplied with a mixture of gaseous fuel and combustion air via the main swirl body (2), and in a liquid fuel operating mode the combustion chamber (1) is supplied with liquid fuel via the atomization apparatus (3) and supplied with combustion air via the main swirl body (2), wherein the atomization nozzle (7) is arranged centrally with respect to a longitudinal center axis (4) of the combustion chamber (1), or arranged on the longitudinal center axis (4) of the prechamber (5), and wherein the swirl chamber (9) is configured to be supplied with the liquid fuel via the radial swirl generator (10) and the axial swirl generator (11).

2. The combustion chamber according to claim 1, wherein the radial swirl generator (10) is supplied with the liquid fuel via a first fuel line (12) and the axial swirl generator (11) is supplied with the liquid fuel via a second fuel line (13).

3. The combustion chamber according to claim 2, wherein the first fuel line (12) has a first fuel valve (15) and the second fuel line (13) has second fuel valve (14).

4. The combustion chamber according to claim 3, wherein the atomization nozzle (7) of the central atomization lance (6) provides an atomization cone (16) with a spray angle () of greater than 60 and smaller than 100 in a case in which the first fuel valve (15) is open, the second fuel valve (14) is closed and the liquid fuel is supplied to the swirl chamber (9) exclusively via the radial swirl generator (10), and the atomization nozzle (7) provides an atomization cone (16) with a spray angle () of greater than 40 and smaller than 60 in a case in which the first and second fuel valve (14, 15) are both open and the liquid fuel is supplied to the swirl chamber (9) via the axial and radial swirl generators (10, 11).

5. The combustion chamber according to claim 4, wherein the central atomization lance (6) comprises a hood-like portion (18) which, downstream of the nozzle orifice (28) of the atomization nozzle (7) of the central atomization lance (6) and upstream of an outlet opening (21) of the central atomization lance (6), defines a chamber (27) which is supplied with the liquid fuel from the swirl chamber (9) via the nozzle orifice (28) and supplied with the combustion air, via a second radial swirl generator (20), bypassing the main swirl body (2).

6. The combustion chamber according to claim 5, wherein the combustion air flow that can be supplied to the combustion chamber (1) while bypassing the main swirl body (2) via the chamber (27) between the nozzle orifice (28) and the atomization nozzle (7) and the hood-like portion (18) is between 1% and 10% of the combustion air flow that can be supplied to the combustion chamber (1) via the main swirl body (2).

7. The combustion chamber according to claim 6, wherein the atomization apparatus (3) comprises multiple atomization nozzles (8) that are arranged in a decentralized manner with respect to a longitudinal center axis (4) of the combustion chamber (1), or arranged in a decentralized manner with respect to the longitudinal center axis (4) of the prechamber (5).

8. The combustion chamber according to claim 7, wherein the decentralized atomization nozzles (8) are positioned on a circular path or pitch circle path (22) extending about the longitudinal center axis (4) of the combustion chamber (1) or about the longitudinal center axis (4) of the prechamber (5).

9. The combustion chamber according to claim 8, wherein a center point of the circular path or pitch circle path (22), on which the decentralized atomization nozzles (8) are positioned, is positioned on the longitudinal center axis (4) of the combustion chamber (1) or on the longitudinal center axis (4) of the prechamber (5), wherein a radius of the circular path or pitch circle path (22), on which the decentralized atomization nozzles (8) are positioned, is between 0.4 times and 1.1 times an inner radius of the main swirl body (2).

10. The combustion chamber according to claim 9, wherein the decentralized atomization nozzles (8) each provide an atomization cone with a spray angle () of greater than 25 and smaller than 90.

11. The combustion chamber according to claim 10, wherein the decentralized atomization nozzles (8) are configured as self-exciting nozzles providing an oscillating fluid jet.

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

13. A method for operating a gas turbine according to claim 12, comprising: supplying, in the gas fuel operating mode, to the combustion chamber (1) a mixture of the gaseous fuel and the combustion air via the main swirl body (2), and supplying to the combustion chamber (1), in the liquid fuel operating mode: the liquid fuel to the combustion chamber (1) via the atomization apparatus (3), and the liquid fuel and combustion air via the main swirl body (2).

14. The method according to claim 13, wherein in the liquid fuel operating mode both the central atomization lance (6) and the decentralized atomization nozzles (8) are utilized throughout an operating range between no load and full load to supply the liquid fuel to the combustion chamber (1).

15. The method according to claim 14, wherein for igniting the gas turbine in the liquid fuel operating mode the swirl chamber (9) of the central atomization lance (6) is supplied with the liquid fuel exclusively via the radial swirl generator (10) and wherein after the igniting of the gas turbine the swirl chamber (9) of the central atomization lance (6) is additionally supplied with the liquid fuel via the axial swirl generator (10).

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Exemplary embodiments of the invention are explained in more detail by way of the drawings without being restricted to the drawings. In the drawings:

[0025] FIG. 1 is a highly schematic plan view of an atomization apparatus of a combustion chamber according to the invention of a gas turbine according to the invention;

[0026] FIG. 2 shows the cross section II-II of FIG. 1;

[0027] FIG. 3 shows the detail III of FIG. 2; and

[0028] FIG. 4 is a diagram for illustrating a method according to the invention for operating the gas turbine according to the invention.

DETAILED DESCRIPTION OF THE PRESENTLY PREFERRED EMBODIMENTS

[0029] The invention relates to a combustion chamber of a gas turbine, to a gas turbine having a combustion chamber and to a method for operating a gas turbine.

[0030] FIGS. 1 to 3 show different views or details of a combustion chamber 1 of a gas turbine, wherein the combustion chamber is a dual fuel combustion chamber.

[0031] FIG. 1 shows a schematic front view or plan view of the combustion chamber 1 against the flow direction of combustion air and fuel. FIG. 2 shows the cross section along the section line II-II of FIG. 1.

[0032] The combustion chamber 1 comprises a flame tube 23, which defines a primary combustion zone of the combustion chamber 1. In the flow direction upstream of this flame tube 23, the combustion chamber 1 comprises a prechamber 5 which forms a pre-primary combustion zone of the combustion chamber 1. Flame tube 23 and prechamber 5 are arranged concentrically to one another and have a common longitudinal center axis 4.

[0033] The combustion chamber 1 according to the invention is a dual-fuel combustion chamber. In a gas fuel operating mode, a gaseous fuel is combusted in the combustion chamber 1, wherein a mixture of the gaseous fuel and combustion air is supplied via a main swirl body 2 to the combustion chamber 1, namely initially to the prechamber 5 and subsequently to the flame tube 23.

[0034] Here, the main swirl body 2 is embodied as a radial swirl body and produces a defined swirl of the mixture of combustion air and gaseous fuel entering the prechamber 5 of the combustion chamber 1 in the gas fuel operating mode. The mixture of the gaseous fuel and the combustion air is ignited in the gas fuel operating mode with the help of an ignition electrode 17 in order to accelerate the gas turbine from the stationary state in the gas fuel operating mode. The ignition electrode 17 is an electric ignition electrode.

[0035] In the liquid fuel operating mode of the combustion chamber 1, a liquid fuel is combusted in the combustion chamber 1. The liquid fuel is supplied to the combustion chamber 1 with the help of an atomization apparatus 3. Combustion air required for combusting the liquid fuel is supplied to the combustion chamber 1 via the main swirl body 2.

[0036] Both during the combustion of gaseous fuel in the gas fuel operating mode and also during the combustion of liquid fuel in the liquid fuel operating mode exhaust gas is produced. This exhaust gas produced in the combustion chamber 1 can be supplied to a turbine of the gas turbine (not shown) to expand the exhaust gas in the turbine and extract energy in the process that can be utilized, for example, for driving an electric machine.

[0037] The atomization apparatus 3 of the combustion chamber 1 comprises a central atomization lance 6, which is positioned approximately on the longitudinal center axis 4 of the prechamber 5 of the combustion chamber 1 or the longitudinal center axis 4 of the flame tube 23 of the combustion chamber 1. Accordingly, the atomization lance 6, based on this longitudinal center axis 4, is positioned centrally, wherein the central atomization lance 6 comprises an atomization nozzle 7, as can be seen in FIG. 3. By way of the atomization nozzle 7 of the central atomization lance 6, the liquid fuel forming an atomization cone 16 can be injected into the prechamber 5 of the combustion chamber 1. Here, the atomization cone 16 is characterized by a spray angle .

[0038] In the shown, preferred exemplary embodiment, the atomization apparatus 3 not only comprises the central atomization lance 6 but in addition to the central atomization lance 6 multiple atomization nozzles 8 which based on the longitudinal central axis 4 of the combustion chamber 1 or based on the longitudinal center axis 4 of the prechamber 5 are decentralized. The ignition electrode 17 is arranged adjacent to one of the decentralized atomization nozzles 8, as shown in FIGS. 1 and 2.

[0039] By way of these decentralized atomization nozzles 8, the liquid fuel can likewise be injected into the prechamber 5 of the combustion chamber 1, namely again subject to forming an atomization cone 29, which is characterized by an atomization cone

[0040] In the preferred exemplary embodiment, the atomization apparatus 3 accordingly comprises the central atomization lance 6 with the atomization nozzle 7 and multiple decentralized atomization nozzles 8. In the following, the central atomization lance 6 and the decentralized atomization nozzles 8 are discussed.

[0041] FIG. 3 shows the detail III of FIG. 2, i.e., a detail from the central atomization lance 6 in the region of the atomization nozzle 7 of the same. The atomization nozzle 7 of the central atomization lance 6 comprises a swirl chamber 9, and downstream of the swirl chamber 9, a nozzle orifice 28. The swirl chamber 9 of the atomization nozzle 7 of the central atomization lance 6 can be supplied with the liquid fuel on the one hand via radial swirl generator 10, and on the other hand, via an axial swirl generator 11. Emanating from a first fuel line 12, which has a fuel valve 15, the radial swirl generator 10 is supplied with liquid fuel. Independently of this, the axial swirl generator 11 can be supplied with liquid fuel via a second fuel line 13, which has a second fuel valve 14.

[0042] In particular when the first fuel valve 15 is open and the second fuel valve 14 is closed and the liquid fuel is supplied to the swirl chamber 9 of the atomization nozzle 7 of the central atomization lance 6 exclusively via the radial swirl generator 10, the atomization nozzle 7 of the central atomization lance 6 provides an atomization cone of liquid fuel with a spray angle of greater than 60 and smaller than 100, preferentially of greater than 70 and smaller than 90. Such a spray angle is utilized in particular for igniting the liquid fuel in the liquid fuel operating mode via the ignition electrode 17.

[0043] In particular when the first fuel valve 15 and the second fuel valve 14 are both open and the liquid fuel is supplied to the fuel chamber 9 of the atomization nozzle 7 of the decentralized atomization lance 6 both via the axial swirl generator 11 and also via the radial swirl generator 10, the atomization nozzle 7 of the central atomization lance 6 provides an atomization cone 16 of the liquid fuel with a spray angle of greater than 40 and smaller than 60. This atomization angle or spray angle of the atomization nozzle 7 of the central atomization lance 6 is advantageous in particular after the igniting of the fuel for running up the gas turbine to a no-load rotation speed and for a subsequent operation of the gas turbine under load.

[0044] Fuel, which is made available to the swirl chamber 9 of the atomization nozzle of the central atomization lance 6 via the radial swirl generator 10 on the fuel side and if applicable the axial swirl generator 11 on the fuel side can exit the swirl chamber 9 via the nozzle orifice 28.

[0045] The fuel-side, radial swirl generator 10 of the central atomization lance 6 and the fuel-side, axial swirl generator 11 of the central atomization lance 6 are preferentially configured so that during the operation exclusively of the radial swirl generator 10 at a relevant atomization pressure of one bar to 15 bar the flow of liquid fuel is substantially smaller than during the operation of both swirl generators 10 and 11.

[0046] The central atomization lance 6 or the atomization nozzle 7 of the same comprises a hood-like portion 18 which downstream of the nozzle orifice 28 and upstream of an outlet opening 21 of the central atomization lance 6 defines a chamber 27.

[0047] It is this chamber 27 into which the liquid fuel enters from the swirl chamber 9 via the nozzle orifice 28, wherein combustion air can continue to be introduced into this chamber 27 via a radial swirl generator 20 on a combustion air side. The combustion air, which is supplied to the chamber 27 via the radial swirl generator 20 on the combustion air side is conducted past the main swirl chamber 2, namely by way of the bypass line 17 shown in FIG. 2.

[0048] Accordingly, combustion air is conducted via the radial swirl generator 20 for the combustion air, bypassing the main swirl body 2, via the bypass 19 and supplied to the chamber 27 of the central atomization lance 6. By way of the swirling of the combustion air supplied to the chamber 27, a swirl jet is produced which promotes the atomization of the liquid fuel entering the chamber 27 via the nozzle orifice 28. Furthermore, this swirled-up air stream cools the atomization nozzle 7 of the central atomization lance 6. The particular combustion air which is conducted past the main swirl body 2 and via the bypass 19 in the direction of the chamber 27 amounts to between 1% and 10% of the combustion air flow, which can be supplied to the combustion chamber 1 via the main swirl body 2.

[0049] As already explained, the atomization apparatus 3 comprises decentralized atomization nozzles 8 in addition to the central atomization lance 6. The decentralized atomization nozzles 8 are preferentially arranged on a circular path or pitch circle path 22, wherein the center point of this circular path or pitch circle path 22, on which the decentralized atomization nozzles 8 are positioned, is positioned on the longitudinal center axis 4 of the combustion chamber 1, i.e., on the longitudinal center axis 4 of the flame tube 23 or on the longitudinal center axis 4 of the prechamber 5. The radius r.sub.22 of this circular path or pitch circle path 22, on which the decentralized atomization nozzles 8 are positioned, amounts to between 0.4 times and 1.1 times the inner radius r.sub.2 of the main swirl body 2. The decentralized atomization nozzles 8 can also be arranged on multiple preferentially concentric circular paths or on an elliptical path or on a polygon.

[0050] While the atomization nozzle 7, dependent on whether the liquid fuel is exclusively conducted via the radial swirl generator 10 or additionally via the axial swirl generator 11, provides the central atomization lance 6 with a spray angle of more than 60 or less than 100 or a spray angle of more than 40 or less than 60, the decentralized atomization nozzles 8 each provide an atomization cone 29 with an atomization angle or spray angle that is greater than 25 and smaller than 90.

[0051] The decentralized atomization nozzles 8 are preferentially nozzles which are configured as self-exciting nozzles and provide an oscillating fluid jet. In this way, a good premixing of the liquid fuel with the combustion air can be provided. The central atomization nozzles 8, emanating from a fuel line 24 having a fuel valve 30, can be supplied with liquid fuel independently of the atomization nozzle 7 of the central atomization lance 6.

[0052] With the help of the decentralized atomization nozzles 8, which are arranged on the circular path or pitch circle path 22 and are equally distributed preferentially along the circular path or pitch circle path 22, the liquid fuel is introduced into the combustion chamber 1, namely initially into the prechamber 5 forming a homogeneous distribution with the combustion air. At the same time, a part premixing of combustion air and liquid fuel is provided, in particular promoted in that the decentralized atomization nozzles 8 are arranged adjoining the outlet of the main swirl body 2.

[0053] A gas turbine according to the invention comprises a combustion chamber according to the invention and a turbine. In the combustion chamber, fuel is combusted in the presence of combustion air. In the turbine, the generated exhaust gas is expanded in order to extract energy in the process for example for driving an electric machine.

[0054] The invention, furthermore, relates to a method for operating a gas turbine. The gas turbine comprises the combustion chamber 1 according to the invention, which is a dual-fuel combustion chamber.

[0055] In the gas fuel operating mode, the combustion chamber 1 is supplied with a mixture of gaseous fuel and combustion air via the main swirl body 2.

[0056] In the liquid fuel operating mode, the combustion chamber 1 is supplied with liquid fuel via the atomization apparatus 3, combustion air is at least partly conducted via the main swirl body 2 and if required via the bypass 19 past the main swirl body 2 in the direction of the chamber 27 of the central atomization lance 6.

[0057] For igniting the gas turbine in the liquid fuel operating mode and for starting-up the gas turbine in the liquid fuel operating mode from the stationary state, the gas turbine is operated so that the combustion chamber 1 is initially supplied with the liquid fuel in the liquid fuel operating mode exclusively via the central atomization lance 6.

[0058] For igniting the liquid fuel, the liquid fuel is initially exclusively supplied to the atomization nozzle 7 via the radial swirl generator 10 in order to thus provide, via the central atomization lance 6, a spray cone 16 with the spray angle or atomization angle , which for the igniting is greater than 60 and smaller than 100, preferentially greater than 70 and smaller than 90. In this case, the liquid fuel can then be favorably ignited via the ignition electrode 17 so that a flame burning in a stable manner can form. In this case, exclusively the fuel valve 15 is open the fuel valves 14 and 30 are then closed.

[0059] Following the forming of the flame burning in a stable manner, the liquid fuel, for accelerating the gas turbine in the direction of a no-load rotational speed, is additionally supplied with the liquid fuel also via the axial swirl generator 11. In the process, the spray angle of the central atomization lance 6 is then reduced in size to an angle of more than 40 and less than 60. By way of this, a disadvantageous wetting of the walls of prechamber 5 and flame tube 23 of the combustion chamber 1 with liquid fuel can be avoided. The fuel valve 14 is also open then. The fuel valve 30 is still closed.

[0060] Once the no-load rotational speed of the gas turbine has been reached, the introduction of the liquid fuel into the combustion chamber 1 via the decentralized atomization nozzle 8 additionally takes place. In this way, an optimal and effective combustion of the liquid fuel can then be ensured during the operation, namely while reducing exhaust gas emissions, in particular while reducing nitrogen oxide emissions. The fuel valve 30 is then also open.

[0061] By way of the central atomization lance 6 of the atomization apparatus 3, liquid fuel is introduced into a central region of the combustion chamber 1, namely a central region of prechamber 5 and flame tube 23. This is advantageous for a stable combustion. Introducing the liquid fuel via the central atomization lance 6 is typically effected not homogeneously the combustion air, no intensive premixing of liquid fuel and combustion air takes place in the region of the central atomization lance 6. By way of the decentralized atomization nozzles 8, the liquid fuel is homogeneously distributed in the combustion air. Furthermore, a part premixing of liquid fuel and combustion air is achieved through the decentralized atomization nozzles 8. This is advantageous in particular for reducing exhaust gas emissions such as nitrogen oxide emissions.

[0062] FIG. 4 illustrates with curve profiles 25 and 25 a fuel mass flow m.sub.BS of fuel which in the liquid fuel operating mode is introduced into the combustion chamber 1 via the central atomization lance 6 and via the decentralized atomization nozzles 8 as a function of the load P of the gas turbine.

[0063] The curve profile 25 corresponds to the mass flow of fuel which is introduced into the combustion chamber 1 via the central atomization lance 6. The curve profile 26 illustrates mass flow of liquid fuel that in the liquid fuel operating mode is introduced into the combustion chamber 1 via the decentralized atomization nozzles 8.

[0064] At a load P of 0% (no load of the gas turbine) fuel is introduced into the combustion chamber 1 as already explained according to the curve profile 25 both via the central atomization lance 6 as well as according to the curve profile 26 via the decentralized atomization nozzles 8.

[0065] With increasing load starting out from no-load (0%), the fuel quantity introduced into the combustion chamber 1 via the decentralized atomization nozzles 8 according to the curve profile 26 rises continuously and the fuel quantity introduced via the central atomization lance 6 remains initially approximately constant according to the curve profile 25.

[0066] With further increasing load, the fuel quantity introduced into the combustion chamber 1 via the central atomization lance 6 falls according to the curve profile 25. However, the central atomization lance 6 is not deactivated but, on the contrary, liquid fuel is introduced into the combustion chamber 1 via the central atomization lance 6 even at a load of 100% (full load of the gas turbine). By way of this, the exhaust gas emissions can be particularly greatly reduced in the full load mode since the fuel quantity introduced into the combustion chamber 1 via the central atomization lance 6 is reduced to a minimum.

[0067] In this connection it is advantageous that the chamber 27 is supplied with combustion air at full load via the radial swirl generator 20 in order to stabilize, in particular with small liquid fuel quantities, which are supplied via the atomization nozzle 7, the spray cone 16 by way of the combustion air introduced into the chamber 27 via the radial swirl generator 20.

[0068] Because the liquid fuel is also supplied via the central atomization lance 6 even at full load, i.e., over the entire load range of the gas turbine in the liquid fuel operating mode, rapid load changes can be realized. Furthermore, the central atomization lance 6 need not be purged or cleaned, since liquid fuel is continuously introduced into the combustion chamber 1 in the liquid fuel operating mode precisely via the same.

[0069] In particular the quantity of liquid fuel which in the liquid fuel operating mode at full load or near full load is introduced in the combustion chamber 1 via the central atomization lance 6 is around less than 5%, preferentially around 2% of the total quantity of the fuel quantity introduced into the combustion chamber 1. In this way a particularly efficient operation of the gas turbine can be guaranteed at full load, in particular while minimizing exhaust gas emissions such as nitrogen oxide emissions.

[0070] With the present invention it is thus possible in the liquid fuel operating mode on the one hand to ignite a gas turbine in a stable manner while on the other hand the gas turbine, starting out from a rotational speed of zero after the igniting, can be run up to the no-load rotational speed in a stable manner. In addition to this, a robust and stable combustion with low emissions can be realized over the entire operating range of the gas turbine between no load or full load. In particular, nitrogen oxide emissions of less than 100 vppm @15% O.sub.2.

[0071] In the gas fuel operating mode, the fuel valves 14, 15, 30 are all closed. The central atomization lance 6 however can be utilized in order to supply, via the chamber 27 of the same, combustion air past the main swirl body 2 to the combustion chamber 1. The ignition electrode, which in the liquid fuel operating mode serves for igniting the liquid fuel, also serves for igniting the gas in the gas fuel operating mode.

[0072] Thus, while there have been shown and described and pointed out fundamental novel features of the invention as applied to a preferred embodiment thereof, it will be understood that various omissions and substitutions and changes in the form and details of the devices illustrated, and in their operation, may be made by those skilled in the art without departing from the spirit of the invention. For example, it is expressly intended that all combinations of those elements and/or method steps which perform substantially the same function in substantially the same way to achieve the same results are within the scope of the invention. Moreover, it should be recognized that structures and/or elements and/or method steps shown and/or described in connection with any disclosed form or embodiment of the invention may be incorporated in any other disclosed or described or suggested form or embodiment as a general matter of design choice. It is the intention, therefore, to be limited only as indicated by the scope of the claims appended hereto.

REFERENCE LIST

[0073] 1 Combustion chamber [0074] 2 Main swirl body [0075] 3 Atomization apparatus [0076] 4 Longitudinal center axis [0077] 5 Prechamber [0078] 6 Atomization lance [0079] 7 Atomization nozzle [0080] 8 Atomization nozzle [0081] 9 Swirl chamber [0082] 10 Radial swirl generator [0083] 11 Axial swirl generator [0084] 12 Fuel line [0085] 13 Fuel line [0086] 14 Fuel valve [0087] 15 Fuel valve [0088] 16 Atomization cone [0089] 17 Ignition electrode [0090] 18 Hood-like portion [0091] 19 Bypass [0092] 20 Radial swirl generator [0093] 21 Outlet opening [0094] 22 Pitch circle [0095] 23 Flame tube [0096] 24 Fuel line [0097] 25 Curve profile [0098] 26 Curve profile [0099] 27 Chamber [0100] 28 Nozzle orifice [0101] 29 Atomization cone [0102] 30 Fuel valve