NOZZLE DEVICE FOR FEEDING AT LEAST ONE GASEOUS FUEL AND ONE LIQUID FUEL, SET, SUPPLY LINE SYSTEM, AND GAS TURBINE ASSEMBLY

Abstract

A nozzle device for feeding a gaseous fuel and a liquid fuel into a combustion chamber of a gas turbine assembly, includes: a nozzle main body having nozzle openings for injecting the gaseous and/or liquid fuels into the combustion chamber, a liquid fuel line for the fluidic connection between a liquid supply line system and the nozzle openings, and at least one gas fuel line for the fluidic connection between a gas supply line system and the nozzle openings. An optimized operation is achieved in that at least partly the gas fuel line is configured to be correlated with the liquid fuel line, wherein a flow cross section AiH2 of the gas fuel line is proportional to a flow cross section AiK of the liquid fuel line by a factor F, where: AiH2=F*Aik, F being 2.4-3, preferably 2.6-2.8, e.g. 2.7.

Claims

1. A nozzle device for feeding at least one gaseous fuel and one liquid fuel into a combustion chamber of a gas turbine assembly, in particular an engine of an aircraft, comprising a nozzle main body having nozzle openings for injecting the gaseous fuel and/or the liquid fuel into the combustion chamber, and at least one liquid fuel line for the fluidic connection between a liquid supply line system and the nozzle openings, and at least one gas fuel line for the fluidic connection between a gas supply line system and the nozzle openings, characterized in that at least in portions, in at least one correlated portion, the gas fuel line is configured so as to be correlated with the liquid fuel line, wherein a flow cross section AiH2 of the gas fuel line is proportional to a flow cross section AiK of the gas fuel line by a factor F, where:
AiH2=F*Aik, F being between 2.4 and 3, preferably between 2.6 and 2.8, e.g. 2.7.

2. The nozzle device according to claim 1, wherein the correlated portion is disposed at least within a bracket holder of the nozzle device.

3. The nozzle device according to claim 1, wherein the correlated portion extends across a majority of more than 50%, preferably more than 80%, of the length of the gas fuel line and of the liquid fuel line, with the exception of transition regions, for example.

4. The nozzle device according to claim 1, wherein the gas fuel line and/or the liquid fuel line at least in the correlated portion have a circular circumference of the flow cross section AiH2, AiK.

5. The nozzle device according to claim 1, wherein the gas fuel line at least in the correlated portion is disposed so as to be in particular cylindrical and/or coaxial about the liquid fuel line.

6. The nozzle device according to claim 1, wherein the nozzle device is conceived for the operation with hydrogen as the gaseous fuel and a kerosene-based and/or kerosene-related fuel as the liquid fuel.

7. A set comprising at least one gas connector line and at least one liquid connector line for installation in a supply line system having a gas supply line system for guiding a gaseous fuel to at least one nozzle device, and having a liquid supply line system for guiding a liquid fuel to at least one nozzle device, wherein the nozzle device is configured according to claim 1, wherein at least in portions, in at least one correlated portion, the gas connector line is configured so as to be correlated with the liquid connector line, wherein a flow cross section AiH2 of the gas connector line is proportional to a flow cross section AiK of the liquid connector line by a factor F, where:
AiH2=F*Aik, F being between 2.4 and 3, preferably between 2.6 and 2.8, e.g. 2.7.

8. The set comprising at least one gas ring line, having a flow cross section which is in particular circular at least in portions, and at least one liquid ring line, having a flow cross section which is in particular circular at least in portions, for installation in a supply line system having a gas supply line system for guiding a gaseous fuel to at least one nozzle device, and having a liquid supply line system for guiding a liquid fuel to at least one nozzle device, wherein the nozzle device is configured according to claim 1, wherein at least in portions, in at least one correlated portion, the gas ring line is configured so as to be correlated with the liquid ring line, wherein a flow cross section AiH2 of the gas ring line is proportional to a flow cross section AiK of the liquid ring line by a factor F, where:
AiH2=F*Aik, F being between 2.4 and 3, preferably between 2.6 and 2.8, e.g. 2.7.

9. The set according to claim 7, wherein the correlated portion extends across a majority of more than 50%, preferably more than 80%, of the length of the gas connector line and of the liquid connector line and/or of the gas ring line and of the liquid ring line, with the exception of transition regions, for example.

10. The set according to claim 7, wherein the gas connector line and the liquid connector line and/or the gas ring line and the liquid ring line are conceived for the operation with hydrogen as the gaseous fuel and a kerosene-based and/or kerosene-related fuel as the liquid fuel.

11. A supply line system having a gas supply line system for guiding a gaseous fuel to at least one nozzle device, and having a liquid supply line system for guiding a liquid fuel to at least one nozzle device, wherein the nozzle device is configured in particular according to one of the preceding claims, having at least one set comprising at least one gas connector line and at least one liquid connector line according to claim 7.

12. Gas turbine assembly, in particular engine for an aircraft, having at least one nozzle device according to one of claim 1.

Description

[0034] The invention will be explained in more detail hereunder by means of exemplary embodiments with reference to the drawings, in which:

[0035] FIG. 1 shows a nozzle device having a nozzle bracket and a nozzle main body as well as a correlated portion of a gas fuel line and of a liquid fuel line in a longitudinal sectional view;

[0036] FIG. 2 shows an enlarged illustration of part of the nozzle bracket of the nozzle device according to FIG. 1 in the longitudinal sectional view; and

[0037] FIG. 3A, 3B show a supply line system having a gas ring line, a liquid ring line, a gas connector line, and a liquid connector line as well as one nozzle device (FIG. 3A) or four nozzle devices (FIG. 3B) in the longitudinal sectional view or in a frontal view when viewed from the direction of a combustion chamber.

[0038] FIG. 1 in a longitudinal sectional illustration shows a nozzle device 1 for alternatively and/or simultaneously feeding gaseous fuel and/or liquid fuel into a combustion chamber of a gas turbine assembly, in particular of the engine of an aircraft.

[0039] The nozzle device 1 is conceived for the operation with hydrogen as the gaseous fuel, and a kerosene-based and/or a kerosene-related fuel (e.g. Jet A-1, diesel, or a synthetic substitute fuel (SAFsustainable aviation fuel)) as the liquid fuel. The fuels may be used alternatively or simultaneously.

[0040] The nozzle device 1 has a nozzle main body lb by way of which gaseous and/or liquid fuel is injected into the combustion chamber by means of nozzle openings 12 during operation. The nozzle openings 12 are in particular configured differently for gaseous fuel and liquid fuel.

[0041] Furthermore, the nozzle device 1 has a nozzle bracket la which is aligned along a longitudinal axis L. An enlarged illustration of part of the nozzle bracket 1 a is shown in FIG. 2.

[0042] Disposed within the nozzle bracket 1 a are a gas fuel line 2 for the fluidic connection between a gas supply line system 7 (cf. FIGS. 3A, B), and a liquid fuel line 4 for the fluidic connection between a liquid supply line system 6 (cf. FIGS. 3A, B), and the nozzle openings 12.

[0043] The gas fuel line 2 and the liquid fuel line 4 are configured to collectively direct the respective fuel (gaseous and liquid) for the operation of a respective nozzle device 1 to the nozzle main body 1b, by way of a respective manifold assembly (for gaseous and for liquid fuel). During operation, the respective fuels are directed to the corresponding nozzle openings 12 by means of the manifold assemblies.

[0044] The gas fuel line 2 and the liquid fuel line 4 are in particular configured so as to be cylindrical, having a circular circumference, and extend along the longitudinal axis L, being symmetrical to the latter. The gas fuel line 2 at least axially extends largely in a cylindrical manner about the liquid fuel line 4 and coaxially with the longitudinal axis L, while forming a symmetrical annular gap. A wall 5 of the liquid fuel line 4 has a wall thickness d. The gas fuel line 2 is delimited by a wall 3.

[0045] The liquid fuel line 4, lying inside, at least largely has a flow cross section having a circular diameter DiK (internal diameter of the wall 5). The gas fuel line 2, disposed cylindrically about the liquid fuel line 4, at least largely has an annular flow cross section having a circular diameter DiH2 (internal diameter of the wall 3).

[0046] For an optimized operation with gaseous fuels as well as liquid fuels, the gas fuel line 2 and the liquid fuel line 4 are conceived so as to mutually correlate in a correlated portion 4. A flow cross section AiH2 of the gas fuel line 2 here is proportional to a flow cross section AiK of the liquid fuel line by a factor F, where:

AiH2=F*AiK, F being between 2.4 and 3, preferably between 2.6 and 2.8, e.g. 2.7.

[0047] It has been demonstrated that, as a result of the basic design, similar flow properties can advantageously be achieved in the operation for hydrogen as the gaseous fuel and the kerosene-based, or kerosene-related fuel at typical operational conditions of an aircraft (in operation on the ground and/or in flight). This offers advantages, e.g. in terms of the control system and/or feedback control system of the engine.

[0048] The correlated portion 13 relates to the same axial position in terms of the gas fuel line 2 and of the liquid fuel line 4, i.e. the flow cross sections AiK, AiH2 or diameters DiK, DiH2 at a specific axial position, or in a specific axial portion, are mutually proportional by the factor F. The correlated portion 13 extends across a majority of more than 50%, preferably more than 80%, of the length of the gas fuel line 2 and of the liquid fuel line 4, for example with only the exception of transition regions in which the mutual disposal of the fuel lines 2, 4 and/or the profile of at least (or in particular only) one fuel line changes (e.g. in terms of the flow cross section and/or the curvature).

[0049] In the example shown in FIG. 1, the following correlation for the diameter DiH2 of the gas fuel line 2 is derived from the given diameter DiK of the liquid fuel line 4:

AiK=0.25(DiK).sup.2 (circular area of the flow cross section of the liquid fuel line),

AiH2=0.25(DiH2).sup.20.25(DiK+2d).sup.2 (circular area of the flow cross section of the gas fuel line 2)

DiH2={square root over (4(AiH2+0.25(DiK+2d).sup.2)/)}

where AiH2=F*AiK , where F=2.7 or 2.6 to 2.8.

[0050] Exemplary values are:

DiK=6 mm

AiK=28.27 mm.sup.2

AiH2=2.7*AiK=76.34 mm.sup.2

d=0.5 mm

DiH2=12.09 mm

[0051] FIG. 3A and FIG. 3B show a supply line system 14 and a nozzle device 1, which is disposed on the supply line system 14, in the cross section (FIG. 3A) as well as a frontal view (viewed from the direction of a combustion chamber) onto the supply line system 14, four nozzle devices 1 being disposed on the latter by way of example (FIG. 3B).

[0052] The supply line system 14 comprises a gas supply line system 6 for guiding the gaseous fuel to the nozzle devices 1. Furthermore, the supply line system 14 comprises a liquid supply line system 7 for guiding the liquid fuel to the nozzle devices 1. The nozzle devices 1 each have in particular the correlated portion 13.

[0053] The gas supply line system 6 comprises a gas ring line 60 and exactly one gas connector line 8 per nozzle device 1. The liquid supply line system 7 comprises a liquid ring line 70 and exactly one liquid connector line 9 per nozzle device 1.

[0054] The gas ring line 60 and the liquid ring line 70 are configured so as to be annular in order to be disposed on a combustion chamber so as to externally run radially about the latter (not shown in FIG. 3A and FIG. 3B). The gas ring line 60 has a circular flow cross section AiH2 having a diameter DiH2. The liquid ring line 70 has a circular flow cross section AiK having a diameter DiK

[0055] The gas connector line 8 and the liquid connector line 9 each are in particular of a flexible configuration. The gas connector line 8 in terms of its basic shape has a circular flow cross section AiH2 having a diameter DiH2. The liquid connector line 9 in terms of its basic shape has a circular flow cross section AiK having a diameter DiK

[0056] The nozzle devices 1 are in each case suitably connected to the supply line system 14 by way of connecting elements 10 and/or 11.

[0057] For an optimized operation with gaseous fuels as well as liquid fuels, the gas line portions and the liquid line portions in the supply line system 14 comprising the ring lines 60, 70 and the connector lines 8, 9 are conceived so as to mutually correlate in at least one correlated portion 15, wherein the flow cross section of the gas line portion AiH2 is in each case proportional to the flow cross section of the liquid line portion AiK by the factor F, where:

AiH2=F*Aik, F being between 2.4 and 3, preferably between 2.6 and 2.8, e.g. 2.7.

[0058] Consequently, the following applies to respective circular flow cross sections of the correlated gas line portions and liquid line portions:

DiH2=1.643*DiK, where F=2.7, or

DiH2=1.612 to 1.673*DiK for F=2.6 to 2.8.

[0059] The correlation relates in particular to line portions of identical function (line portions of the same type), for example between the ring lines 60, 70, and/or between the connector lines 8, 9, and/or respective flow cross sections of identical shape, e.g. circular flow cross sections.

[0060] The correlated portions 15 each occupy a majority of the line length, for instance an extent of more than 50%, preferably more than 80%, for example with the exception only of transition regions in which the mutual disposal of the line portions 2, 4 and/or the profile of at least (or only) one line portion of the same type changes (e.g. in terms of the flow cross section and/or the curvature).

[0061] In the operation of the engine with gaseous fuels or with liquid fuels, flow conditions of the same type are advantageously obtained across the majority of the line profile of the supplying line system 14 and of the nozzle device 1 in particular when the nozzle devices 1 are also configured with the correlated portions 13, as a result of which the operation can be optimized in particular with a view to the control system and/or feedback control system.

List of Reference Signs

[0062] 1 Nozzle device [0063] 1a Nozzle bracket [0064] 1b Nozzle main body [0065] 2 Gas fuel line [0066] 3 Wall [0067] 4 Liquid fuel line [0068] 5 Wall [0069] 6 Gas supply line system [0070] 60 Gas ring line [0071] 7 Liquid supply line system [0072] 70 Liquid ring line [0073] 8 Gas connector line [0074] 9 Liquid connector line [0075] 10 Connecting means [0076] 11 Connecting means [0077] 12 Nozzle opening [0078] 13 Correlated portion [0079] 14 Supply line system [0080] 15 Correlated portion [0081] DiH2 Diameter [0082] DiK Diameter [0083] d Wall thickness [0084] L Longitudinal axis