Piloting assembly, nozzle device, method of manufacture, and gas turbine assembly

Abstract

The invention relates to a piloting arrangement (23) for use in a nozzle device (100) of a gas turbine arrangement, in particular of an aircraft engine, comprising: - a cavity (12) extending on a longitudinal axis (L) for conveying fuel, the largest flow cross-section of which is larger than the largest flow cross-section of a piloting line (130) of a pilot fuel nozzle (13); and - the pilot fuel nozzle (13) adjoining the cavity (12) downstream, with the piloting line (130) and a pilot fuel outlet (131) arranged at the downstream end of the piloting line (130), wherein the cavity (12) is arranged in a central body (8) arranged on the longitudinal axis (L); and wherein at least one swirl element (90) is arranged circumferentially around the central body (8), wherein the central body (8) and the at least one swirl element (90) form a swirl arrangement (9). form.Manufacturing advantages are achieved by the fact that the pilot assembly (23) is composed of two components, wherein a first component (21) comprises the at least one twisting element (90) and the central body (8) and a second component (22) comprises the pilot fuel nozzle (13) (Fig. 3).

Description

[0001] The invention relates to a piloting arrangement for use in a nozzle device of a gas turbine arrangement, in particular of an aircraft engine, according to the preamble of claim 1. The invention further relates to a nozzle device, a method for manufacturing it and a gas turbine arrangement.

[0002] To ensure stable combustion processes in an aircraft engine across the widest possible operating range, fuel nozzles often incorporate a pilot stage. The pilot stage delivers a smaller quantity of fuel than the main stage. This allows the combustion process in the pilot stage to operate within a stable range, thus stabilizing the combustion process in the main stage.

[0003] A pilot arrangement of the type mentioned above, which enables very compact training, is described in DE 10 2022 208 337 A1.

[0004] Pilot arrangements in comparatively large-dimensioned nozzle devices are specified in US 10 072 845 B2 and EP 1 445 540 A1.

[0005] US patent 2014 / 0291418 A1 shows a nozzle device with two air channels for operation with two air streams ("2-stream fuel nozzle"), without piloting.

[0006] The present invention is based on the objective of providing a piloting arrangement optimized with regard to manufacturing aspects, as well as a method for manufacturing the piloting arrangement and a gas turbine arrangement.

[0007] The problem is solved with respect to the pilot arrangement by the features of claim 1. With respect to the nozzle device, the problem is solved with the features of claim 11, with respect to the method with the features of claim 12, and with respect to the gas turbine arrangement with the features of claim 15.

[0008] The piloting arrangement is provided that the piloting arrangement is composed of two components, in particular joined together, wherein a first component comprises the at least one twisting element and (at least largely) the central body and a second component comprises the pilot fuel nozzle.

[0009] The separation between the two components is essentially formed in one or two planes orthogonal to the longitudinal axis, in particular at (exclusively) one or (exclusively) two axial positions.

[0010] The cavity preferably has a significantly larger flow cross-section than the flow cross-section of the pilot line. For example, the largest flow cross-section of the cavity is at least a factor of 3, preferably a factor between 5 and 10, or at least a factor of 10 larger than the largest flow cross-section in a pipe element of the pilot line, upstream of the pilot fuel outlet.

[0011] It is particularly advantageous that the first component is designed as a continuous, integral (one-piece) component. High manufacturing accuracy can be achieved if the first component is manufactured, in particular, by milling, drilling, and / or turning processes.

[0012] For the most compact design possible, the first component preferably has at least one pilot fuel feed for supplying fuel into the cavity. This pilot fuel feed is guided through the swirl element to direct pilot fuel radially inwards from a circumferential wall of an inner air channel into the cavity. The flow cross-section of the pilot fuel feed is at least as large as the flow cross-section of the pilot line (upstream of the pilot fuel outlet). Swirl elements with a pilot fuel feed are preferably thicker (in the direction of rotation) than those without a pilot fuel feed.

[0013] An advantageous swirl imprint on an airflow is achieved when the first component has at least five and at most eight swirl elements. With five swirl elements, preferably at least one or exactly one has a pilot fuel feed. With eight swirl elements, preferably four of them have a pilot fuel feed.

[0014] Preferably, the second component comprises a sleeve, particularly a ceramic one, arranged circumferentially around the pilot line. The sleeve is, for example, made of or comprises Al₂O₃. Preferably, the sleeve is arranged coaxially to the pilot line in a particularly cylindrical interior of a lance and extends from the axial position of the upstream end of the lance (from the downstream end of the central body) to a downstream axial stop in a downstream end region of the lance (in particular a downstream quarter, fifth, or sixth of the lance) upstream of the pilot fuel outlet. The ceramic sleeve acts as a heat shield, particularly in place of a gas chamber, wherein the sleeve is arranged as precisely as possible between a surrounding wall of the lance and the pilot line.

[0015] Preferably, the second component comprises a separating element, particularly a sealing element, arranged between the upstream end of the sleeve and the cavity. The separating element is preferably designed as a collar and / or ring and / or funnel, preferably made of the same material as the pilot line (especially a nickel-based alloy or stainless steel), and is positioned between the cavity and the sleeve in the assembled state. The separating element can be attached to the pilot line as a separate component or manufactured integrally with the pilot line. The separating element serves as a mechanical barrier between the cavity and the sleeve, as well as for axially fixing the sleeve. The pilot line can project upstream through the separating element into the cavity.

[0016] Preferably, the second component comprises a lance extending along the longitudinal axis, which accommodates the pilot line and / or the sleeve and / or the separating element. The lance with the pilot line has an axial length such that the fuel outlet is positioned at least in a downstream third or quarter, preferably at least substantially at an outlet, of an inner air duct of the nozzle device. The lance is particularly largely hollow-cylindrical and preferably has, apart from a tapered downstream end section, a constant height, and in particular a constant outer diameter. The lance connects, for example, to a downstream taper of the central body. The lance preferably has, for example, a cylindrical interior extending along the longitudinal axis for accommodating the individual parts mounted on or in the lance.The individual components arranged within the lance are preferably aligned coaxially with each other. The individual elements can be attached to or within the lance, for example, at the tip by soldering. Preferably, upstream of the lance, a portion of the central body with a conically shaped section of the cavity serving as a transition between the cavity and the pilot line is arranged on the second component.

[0017] Advantageous fuel injection can be achieved if the pilot line narrows towards a pilot fuel outlet by means of a constriction.

[0018] In a manufacturing-optimized design variant, the constriction is formed by means of a pipe element, which is arranged in and / or (immediately adjoining, the pipe element) downstream of a pipe element of the pilot line and has a smaller flow cross-section than the pipe element. The pilot line then comprises the pipe element and, at its downstream end, the pipe element, or is formed from these two elements. It is also possible that the constriction is integrally manufactured on the pipe element, whereby the pilot line is formed (exclusively) by means of the pipe element.

[0019] In a flow-optimized design, the flow cross-section(s) of the pilot line and / or the at least one pilot fuel supply is / are round.

[0020] The nozzle device according to the invention has a piloting arrangement according to one of the preceding embodiments and an inner air channel arranged on a longitudinal axis of the nozzle device, within which the piloting arrangement is arranged coaxially to the inner air channel.

[0021] The procedure for producing a pilot setup trained according to one of the preceding training variants comprises the following steps: a. Providing a first component with at least one twisting element and a central body, and a second component with a pilot fuel nozzle; b. Attaching the two components to each other by joining, e.g. soldering or welding.

[0022] An advantageous manufacturing procedure is to produce the first component by means of milling, drilling and / or turning processes, in particular integrally (in one piece).

[0023] Preferably, the second component is pre-assembled to provide it, wherein For example, a pipe element comprising a pilot line is attached coaxially to the pipe element as the downstream end of the pilot line, in particular by soldering; a sleeve is inserted from an upstream end of a lance into an elongated interior of the lance; the pipe element with the separating element and, if applicable, the pipe element is inserted into the sleeve and fixed at the tip of the lance, e.g. by soldering.

[0024] The invention will now be explained in more detail using exemplary embodiments and with reference to the drawings. The drawings show: Fig. 1A, 1B, 1C a nozzle device with a swirl arrangement according to the prior art in longitudinal section ( Fig. 1A ), an internal air duct of the nozzle device in longitudinal section ( Fig. 1B ) as well as a partial sectional view of the twist arrangement along a section line A ( Fig. 1C ), Fig. 2A, 2B the inner air duct of a nozzle device with a piloting arrangement according to the prior art in longitudinal section ( Fig. 2A ) as well as a partial sectional view of the piloting setup along a section line B ( Fig. 2B ), Fig. 3 the inner air duct of a nozzle device with a piloting arrangement according to the invention in longitudinal section, Fig. 4 steps of a manufacturing process with individual parts of a second component of the piloting arrangement in longitudinal section, and Fig. 5 the inner air duct of a nozzle device in a further embodiment of the piloting arrangement in longitudinal section.

[0025] Fig. 1A Figure 1 shows a nozzle device 100 in longitudinal section with three air channels 5, 7 ("3-flow fuel nozzle"), as known from the prior art. Such nozzle devices 100 are used in particular in aircraft engines. Fig. 1B shows an inner air duct 7 of the nozzle device 100 with built-in central body 8 in longitudinal section. Fig. 1C shows a partial section of the inner air duct 7 along section line A.

[0026] The in Fig. 1A bis Fig. 1C The nozzle device 100 shown is specifically designed for operation with a liquid fuel (kerosene-based or related to kerosene).

[0027] The nozzle assembly 100 has a fuel supply line 1, which is in flow communication with a fuel ring reservoir 2 of the nozzle assembly 100 during operation. Downstream of the fuel ring reservoir 2, a fuel ring line 3 is arranged, by means of which a fuel injector 4 of the nozzle assembly 100 is supplied with fuel during operation. The fuel is injected into a combustion chamber (not shown here) by means of the fuel injector 4.

[0028] The fuel injector 4 is radially surrounded by two circumferential air channels 5, a radially outer air channel and a radially central air channel. Swirl elements 6 are arranged within each of the air channels 5.

[0029] The nozzle device 100 has an inner air channel 7 located centrally on a longitudinal axis L, which is bounded by a, in particular cylindrical, channel 70. At its downstream end, the inner air channel 7 has an outlet 71 for connection to the combustion chamber. An inner diameter D in a downstream section and / or at the outlet 71 can be, for example, 7 mm to 15 mm.

[0030] Between the inner air duct 7 and the fuel ring line 3 and / or the fuel injector 4 there is an air chamber 10 for thermal shielding (i.e. as a heat shield) of these fuel-carrying lines.

[0031] Within the inner air duct 7, a swirl arrangement 9 is arranged, which has a central body 8 on its longitudinal axis L. Around the central body 8, swirl elements 90 of the swirl arrangement 9 are arranged to generate a swirl flow within the inner air duct 7 during operation. These elements extend radially-tangentially from the central body 8 to the wall 70. An example thickness d of the swirl elements 90 is 0.8 mm to 1.5 mm. The swirl elements 90 and the central body 8 are manufactured as separate components, which are joined together, for example, before installation of the nozzle assembly 100.

[0032] In operation with the nozzle device 100 according to Fig. 1A bis Fig. 1C Stability problems can arise, such as lean combustion. Piloting can be used for stabilization, but this is difficult to implement, especially with small nozzle devices (100 mm) due to limited installation space.

[0033] Fig. 2A shows in a longitudinal section of the inner air duct 7 as well as Fig. 2B in a partial section along the section line B a piloting arrangement 23, which, due to its compact design, can easily be incorporated into nozzle devices of 100 smaller dimensions, such as in Fig. 1A This setup can be shown and implemented. It is known from DE 10 2022 208 337 A1.

[0034] The pilot arrangement 23 has a cavity 12 located centrally on the longitudinal axis L and extending along the longitudinal axis L. The cavity 12 serves in particular as a calming chamber for the fuel flow.

[0035] Furthermore, the piloting arrangement 23 comprises a pilot fuel nozzle 13, which includes a piloting line 130 extending axially along the longitudinal axis L and a fuel outlet 131 located at the downstream end of the piloting line 130. The pilot fuel nozzle 13 is located directly downstream of the cavity 12 and is in flow communication with it, and is supplied with fuel from the cavity 12 during operation. The largest and smallest flow cross-sections of the piloting line 130 are smaller than the largest and smallest flow cross-sections of the cavity 12. For example, the largest flow cross-section of the piloting line 130 is smaller by at least a factor of 3, preferably by a factor between 5 and 10, or at least by a factor of 10, than the largest flow cross-section of the cavity 12.

[0036] The pilot arrangement 23 includes, by way of example, several pilot fuel feeds 11 for supplying fuel, in particular liquid fuel (kerosene-based or kerosene-related), into the cavity 12. For a particularly compact design, the pilot fuel feeds 11 are guided radially outwards, i.e., starting from the wall 70 of the inner air duct 7, to the cavity 12 by the swirl elements 90. For this purpose, a corresponding distribution line for supplying the pilot fuel feeds 11 with fuel is preferably arranged in the wall 70 (not shown here).

[0037] For thermal shielding of the cavity 12 and the pilot line 130, a gas-filled hollow chamber 14 is arranged as a heat shield around the pilot line 130 and the cavity 12 within the central body 8.

[0038] The in Fig. 2A und Fig. 2B The known pilot assembly 23 shown is integrated into the swirl assembly 9 for a particularly compact design. The cavity 12 is arranged in the central body 8 of the swirl assembly 9, specifically symmetrically about the longitudinal axis L. The swirl elements 90 are arranged radially around the central body 8, encompassing the cavity 12. The pilot assembly 23, with the swirl elements 90 and the central body 8 encompassing the cavity 12, is formed with the pilot fuel nozzle 13 as a single, integral (one-piece) component.

[0039] Fig. 3 Figure 1 shows a longitudinal section of the inner air duct 7, a further development according to the invention of the piloting arrangement 23 known from DE 10 2022 208 337 A1, which is optimized in particular with regard to manufacturing aspects.

[0040] A lance 16 is arranged at the downstream end of the central body 8, extending coaxially to the inner air duct 7 and the cavity 12 along the longitudinal axis L. The pilot fuel outlet 131 is located in the downstream third of the inner air duct 7 near the outlet 71 (or, preferably, at the level of the outlet 71, not shown here) by means of the lance 16. The lance 16 is, in particular, largely hollow and cylindrical and preferably has a constant height, especially a constant outer diameter, apart from a tapered downstream end section. The lance 16 connects to a downstream taper of the central body 8. At least a large part of the pilot line 130 runs inside the lance 16. By means of the lance 16, the heat release zone during pilot combustion can be arranged downstream, axially spaced from the cavity 12.

[0041] The flow cross-sections of the pilot line 130 and / or the pilot fuel feeds 11 are preferably round.

[0042] How Fig. 3 As shown, the pilot arrangement 23 is composed of, in particular, two components, a first component 21 and a second component 22. The two components 21, 22 are joined together, for example, by soldering or welding.

[0043] A separation T between components 21 and 22, at which they are joined, runs essentially perpendicular to the longitudinal axis L, exemplified at two axial positions for ease of assembly. For example, an upstream end of the second component 22 is designed as a circumferential collar 161, acting as an axial stop during assembly. The outer wall of the first component 21 continues at the separation T onto the second component 22 to ensure a continuous wall profile. The inner wall, which defines the cavity 12, terminates on the first component 21 further upstream than the outer wall of the first component 21, with the outer wall ending at a stop on the side of the collar 161.

[0044] Downstream of the separation T, the inner wall of the cavity 12 within the second component 22 is, for example, conically shaped to form the transition to the pilot line 130.

[0045] The first component 21 comprises the swirl elements 90 with at least one, preferably between one and four, pilot fuel supply(s) 11, and at least a large part of the central body 8, including at least a large part of the cavity 12. The first component 21 is located entirely in the upstream half of the inner air duct 7. A part of the second component 22 also extends, for example, into the upstream half of the inner air duct 7.

[0046] Preferably, between five and eight swirl elements 90 are provided, wherein (with five swirl elements 90) one of the pilot fuel feeds 11 extends radially inwards into the cavity 12 in one or (particularly with eight) up to four swirl elements 90. The swirl elements 90 that include one of the pilot fuel feeds 11 are each thicker than those without a pilot fuel feed 11.

[0047] The first component 21 is designed as a single, integral (one-piece) component and is manufactured, for example, by milling, drilling, and / or turning processes. The cavity 12 is essentially, except for a downstream end section, designed, for example, as a hollow cylinder. A maximum height of the cavity 12 (for example, one diameter) corresponds, for example, to 1 / 4 to 3 / 4 of the (smallest) diameter D of the inner air duct 7.

[0048] The second component 22 comprises the pilot fuel nozzle 13 with the lance 16 and the piloting line 130. A downstream end section of the cavity 12 can also be arranged in the second component 22.

[0049] The second component 22 is in particular composed of several individual parts which are pre-assembled to form the second component 22. The individual parts are arranged on the lance 16, preferably largely inserted into a cylindrical interior 160 of the lance 16.

[0050] The second component 22 comprises a sleeve 17 arranged around the pilot line 130 in the interior space 160. The sleeve 17 is designed in particular as a ceramic element 170, i.e., made of ceramic material (for example, Al₂O₃), and acts as a heat shield for thermally shielding the pilot line 130, in particular in place of a gas space around the pilot line 130. The sleeve 17 also ensures that the pilot line 130 is positioned stably and reliably.

[0051] Furthermore, the second component 22 has a separating element 18 arranged between the upstream end of the sleeve 17 and the cavity 12. The separating element 18 is in the form of a collar and / or ring and / or funnel, preferably made of the same material as the pilot line (in particular a nickel-based alloy or stainless steel), and is positioned between the cavity 12 and the sleeve 17 when assembled. The separating element 18 preferably rests as closely as possible (on the outside) against the inner walls of the cavity 12 and / or the lance 16 and (on the inside) against the wall of the pilot line 130, or is connected to the wall of the pilot line 130. In this way, the separating element 18 acts as an upstream axial stop for the ceramic sleeve 17 to prevent the sleeve 17, containing in particular ceramic material, from entering the fuel path.The pilot line 130 can extend upstream through the separating element 18 into the cavity 12 (cf. . Fig. 5 ).

[0052] Furthermore, the second component 22 can include a pipe element 200, which comprises or forms a downstream constriction 20 of the pilot line 130 leading to the pilot fuel outlet 131. The pilot fuel outlet 131 is then located at the downstream end of the pipe element 200. The upstream section of the pilot line 130 is formed by means of a line element 132, which in this case has an exemplary constant flow cross-section. The pipe element 200 is located at the downstream end of the line element 132 and has a smaller flow cross-section than the line element 132, and may be at least partially inserted into the line element 132. The exact axial position of the pilot fuel outlet 131 can be determined by means of the overhang of the pipe element 200.

[0053] Alternatively, it is possible that the constriction 20 with the pilot fuel outlet 131 is arranged at the downstream end of the line element 132 and is integrally manufactured on it.

[0054] Fig. 4 shows steps of a manufacturing process for the pilot assembly 23 with the pre-assembly of the second component 22 from several individual parts. In a first step in Fig. 4 In step i) shown, the pipe element 200 is inserted coaxially to the downstream end of the conductor element 132 and preferably attached to it, in particular soldered.

[0055] The separating element 18 is or will be arranged at the upstream end of the conductor element 132, e.g. attached to it (subsequently) or manufactured integrally with the conductor element 132, here by way of example such that the upstream end of the separating element 18 is essentially flush with the upstream end of the conductor element 132.

[0056] In step ii) (which can also be carried out parallel to or before step i), the sleeve 17 is inserted upstream into the interior 160 of the lance 16 until the sleeve 17 abuts a cross-sectional constriction of the interior 160 on the downstream side. The sleeve 17 has, in particular, an outer diameter such that it is both positively engaged with the interior 160 and easily displaceable.

[0057] In step iii), the conduit element 132 pre-assembled in step i) with the pipe element 200 and the separating element 18 is inserted into the sleeve 17 located inside the lance 16 until the separating element 18 axially abuts the upstream end of the sleeve 17.

[0058] In step iv) the conductor element 132 and / or the pipe element 200 are fixed to the tip of the lance 16, for example by soldering.

[0059] The second component 22, pre-assembled in this way, is now attached to the first component 21 by means of soldering or welding, whereby the in Fig. 3 The pilot setup shown, 23, is formed.

[0060] Fig. 5 Figure 1 shows the inner air duct 7 of the nozzle device 100 with a further variant of the piloting arrangement 23 in longitudinal section. The line element 132 with the piloting line 13 projects upstream beyond the separating element 18 into the cavity 12 and / or axially into the first component 21.

[0061] The pilot arrangement 23 can be advantageously manufactured with a particularly compact design for use in small-dimensioned nozzle devices, for example in so-called 3-stream fuel nozzles. Bezugszeichenliste

[0062] 100 Nozzle assembly 1 Fuel supply line 2 Fuel ring reservoir 3 Fuel ring line 4 Fuel injector 5 Outer and middle air duct 6 Swirl element 7 Inner air duct 70 Wall 71 Outlet 8 Central body 9 Swirl arrangement 90 Swirl element 10 Air chamber 11 Pilot fuel supply 12 Cavity 13 Pilot fuel nozzle 130 Piloting line 131 Pilot fuel outlet 132 Line element 16 Lance 160 Interior 161 Collar 17 Sleeve 170 Ceramic element 18 Separating element 19 Soldering 20 Constriction 200 Pipe element 21 First component 22 Second component 23 Piloting arrangement D Diameter d Thickness T Separation

Claims

1. Piloting arrangement (23) for use in a nozzle device (100) of a gas turbine arrangement, in particular of an aircraft engine, comprising: - a cavity (12) extending on a longitudinal axis (L) for conveying fuel, the largest flow cross-section of which is larger than the largest flow cross-section of a piloting line (130) of a pilot fuel nozzle (13); and - the pilot fuel nozzle (13) adjoining the cavity (12) downstream, with the piloting line (130) and a pilot fuel outlet (131) arranged at the downstream end of the piloting line (130), wherein the cavity (12) is arranged in a central body (8) arranged on the longitudinal axis (L); and wherein at least one swirl element (90) is arranged circumferentially around the central body (8), wherein the central body (8) and the at least one swirl element (90) form a swirl arrangement (9). characterized by thatthe piloting arrangement (23) is composed of two components, wherein a first component (21) comprises the at least one twisting element (90) and the central body (8) and a second component (22) comprises the pilot fuel nozzle (13).

2. Pilot arrangement (23) according to claim 1, characterized by that the first component (21) is designed as a connected, integral component.

3. Pilot arrangement (23) according to claim , characterized by that the first component (21) has at least one pilot fuel supply (11) for supplying fuel into the cavity (12), wherein the at least one pilot fuel supply (11) is guided through the at least one swirl element (90) for directing pilot fuel from a circumferential wall (70) of an inner air channel (7) radially inwards into the cavity (12).

4. Pilot arrangement (23) according to claim 3, characterized by thatthe first component (21) has at least five, at most eight twisting elements (90).

5. Pilot arrangement (23) according to one of the preceding claims, characterized by that the second component (22) comprises a sleeve (17) arranged around the pilot line (130), in particular a ceramic sleeve.

6. Pilot arrangement (23) according to claim 5, characterized by that the second component (22) has a separating element (18) arranged between the upstream end of the sleeve (17) and the cavity (12), in particular a sealing element.

7. Pilot arrangement (23) according to one of the preceding claims, characterized by thatthe second component (22) comprises a lance (16) extending on the longitudinal axis (L) which accommodates the piloting line (130) and / or the sleeve (17) and / or the separating element (18), wherein the lance (16) with the piloting line (130) has such an axial length that the fuel outlet (131) is positioned at least in a downstream third or quarter, preferably at least substantially at an outlet (71), of an inner air duct (7) of the nozzle device (100).

8. Pilot arrangement (23) according to one of the preceding claims, characterized by that The pilot line (130) narrows towards a pilot fuel outlet (131) by means of a constriction (20).

9. Pilot arrangement (23) according to claim 8, characterized by thatthe constriction (20) is formed by means of a pipe element (200) which is arranged in and / or downstream of a line element (132) of the pilot line (130) and has a smaller flow cross-section than the line element (132).

10. Pilot arrangement (23) according to one of the preceding claims, characterized by that the flow cross-section(s) of the pilot line (130) and / or of at least one pilot fuel supply (11) is / are round.

11. Nozzle device (100) with a piloting arrangement (23) according to one of the preceding claims and with an inner air channel (7) arranged on a longitudinal axis (L) of the nozzle device (100), within which the piloting arrangement (23) is arranged coaxially to the inner air channel (7).

12. Method for manufacturing a piloting arrangement (23) configured according to one of the preceding claims, comprising the steps: c. providing a first component (21) with at least one twisting element (90) and a central body (8), and a second component (22) with a pilot fuel nozzle; d. attaching the two components (21, 22) to each other by joining, e.g. soldering or welding.

13. Method according to claim 12, characterized by that to provide the first component (21) which is manufactured by means of milling, drilling and / or turning processes, in particular integral.

14. Method according to claim 12 or 13, characterized by thatTo provide the second component (22), it is pre-assembled, wherein - for example, a pipe element (200) comprising a pilot line (130) is attached coaxially to the pipe element (132) as the downstream end of the pilot line (130), in particular by soldering; - a sleeve (17) is inserted from an upstream end of a lance (16) into an elongated interior (160) of the same; - the pipe element (132) with a separating element (18) and, if applicable, the pipe element (200) is inserted into the sleeve (17) and is fixed at the tip of the lance (16), e.g. by soldering (19).

15. Gas turbine arrangement, in particular for an aircraft, comprising a combustion chamber arrangement comprising at least a nozzle device (100) according to claim 11 and a turbine arrangement.

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