NOZZLE ASSEMBLY WITH NOZZLE HEAD HAVING GUIDE ELEMENT

Abstract

The proposed solution relates to a nozzle assembly for a combustion chamber of an engine, having at least one nozzle, which includes a nozzle head that extends along a nozzle longitudinal axis and has at least one nozzle exit opening for injecting fuel into a combustion space of the combustion chamber, and at least one air-guiding duct, by way of which a swirl-affected air flow can be created in the direction of the combustion space along an outer lateral surface of the nozzle head.

At least one guide element which protrudes on the outer lateral surface of the nozzle head is in a flow path for the air flow of the at least one air-guiding duct and is configured to guide at least a part of the air flow radially inwards in relation to the nozzle longitudinal axis into a central injection region downstream of the nozzle exit opening.

Claims

1. Nozzle assembly for a combustion chamber of an engine, having at least one nozzle, which comprises a nozzle head that extends along a nozzle longitudinal axis and has at least one nozzle exit opening for injecting fuel into a combustion space of the combustion chamber, and at least one air-guiding duct, by way of which a swirl-affected air flow can be created in the direction of the combustion space along an outer lateral surface of the nozzle head, wherein at least one guide element which protrudes on the outer lateral surface of the nozzle head is provided, which guide element is in a flow path for the air flow of the at least one air-guiding duct and is configured to guide at least a part of the air flow radially inwards in relation to the nozzle longitudinal axis into a central injection region downstream of the nozzle exit opening.

2. Nozzle assembly according to claim 1, wherein the guide element is configured to deflect a part of the air flow of the air-guiding duct radially inwards on the lateral surface of the nozzle head and, in the process, to slow it down in the circumferential direction, with the result that less rotational energy is inherent to this part of the air flow and thus this part is less swirl-affected than other parts of the air flow conducted out of the air-guiding duct in the direction of the combustion space.

3. Nozzle assembly according to claim 1, wherein the guide element has an elongate form.

4. Nozzle assembly according to claim 1, wherein the guide element extends along the outer lateral surface of the nozzle head by way of a minimum length, which corresponds to at least half of the length, measured along the nozzle longitudinal axis, of the nozzle head.

5. Nozzle assembly according to claim 1, wherein the guide element is in the form of a fin or rib.

6. Nozzle assembly according to claim 1, wherein multiple guide elements are provided on the outer lateral surface along a circumferential direction about the nozzle longitudinal axis.

7. Nozzle assembly according to claim 6, wherein the multiple guide elements are provided on the outer lateral surface evenly distributed along the circumferential direction.

8. Nozzle assembly according to claim 6, wherein each guide element of the multiple guide elements extends along the outer lateral surface in a plane of extent which is parallel to the nozzle longitudinal axis.

9. Nozzle assembly according to claim 6, wherein each guide element of the multiple guide elements extends along the outer lateral surface in a plane of extent which is inclined in relation to the nozzle longitudinal axis.

10. Nozzle assembly according to claim 9, wherein an angle of attack at which a respective plane of extent is inclined in relation to the nozzle longitudinal axis is in the range of 1° to 70°.

11. Nozzle assembly according to claim 1, wherein the nozzle head has a conical or frustoconical form.

12. Engine having at least one nozzle assembly according to claim 1.

Description

[0024] In the figures:

[0025] FIG. 1 shows a perspective view, in partial section, of an embodiment variant of a proposed nozzle assembly as seen from the combustion space;

[0026] FIG. 2 shows a sectional illustration of the nozzle assembly of FIG. 1;

[0027] FIG. 3A shows a nozzle assembly, during operation of a combustion chamber of the engine, having a nozzle head on which no guide elements according to the proposed solution are provided, with depiction of a backflow of hot gas in the direction of the nozzle head;

[0028] FIG. 3B shows, in a view corresponding to FIG. 3A, the resulting hot flow in the case of a nozzle assembly according to the proposed solution;

[0029] FIG. 4 shows an individual view, in perspective, of a nozzle of the embodiment variant of FIGS. 1, 2 and 3B;

[0030] FIG. 5 shows, in a view corresponding to FIG. 4, a nozzle of a further embodiment variant, in which guide elements are provided slanted on the nozzle head and thus obliquely in relation to the injection direction;

[0031] FIG. 6A shows an engine in which an embodiment variant of a proposed nozzle assembly is used;

[0032] FIG. 6B shows an enlarged scale of a detail of the combustion chamber of the engine of FIG. 6A.

[0033] FIG. 6A depicts, schematically and in a sectional illustration, a (turbofan) engine T in which the individual engine components are arranged one behind the other along an axis of rotation or central axis M, and the engine T is in the form of a turbofan engine. At an inlet or intake E of the engine T, air is drawn in along an inlet direction by means of a fan F. This fan F, which is arranged in a fan casing FC, is driven by means of a rotor shaft S which is set in rotation by a turbine TT of the engine T. The turbine TT here adjoins a compressor V, which has, for example, a low-pressure compressor 11 and a high-pressure compressor 12, and optionally also a medium-pressure compressor. On the one hand, the fan F conducts air in a primary air flow F1 to the compressor V, and, on the other hand, to generate thrust, in a secondary air flow F2 to a secondary flow duct or bypass duct B. The bypass duct B here runs around a core engine comprising the compressor V and the turbine TT and comprising a primary flow duct for the air supplied to the core engine by the fan F.

[0034] The air conveyed into the primary flow duct by means of the compressor V enters a combustion chamber assembly BK of the core engine, in which the drive energy for driving the turbine TT is generated. For this purpose, the turbine TT has a high-pressure turbine 13, a medium-pressure turbine 14 and a low-pressure turbine 15. Here, the energy released during the combustion is used by the turbine TT to drive the rotor shaft S and thus the fan F in order to generate the required thrust by means of the air conveyed into the bypass duct B. Both the air from the bypass duct B and the exhaust gases from the primary flow duct of the core engine flow out via an outlet A at the end of the engine T. Here, the outlet A commonly has a thrust nozzle with a centrally arranged exit cone C.

[0035] FIG. 6B shows a longitudinal section through the combustion chamber assembly BK of the engine T. This shows in particular an (annular) combustion chamber 3 of the engine T. A nozzle assembly is provided for the injection of fuel or an air-fuel mixture into a combustion space 30 of the combustion chamber 3. Said nozzle assembly comprises a combustion chamber ring R on which multiple nozzles 2 are arranged at a combustion chamber head 31 of the combustion chamber along a circular line around the centre axis M. One or more combustor seals 4 with mounting openings at which nozzle heads of the respective nozzles 2 are held are provided on the combustion chamber ring R, with the result that fuel can be injected into the combustion chamber 3 thereby. Here, each nozzle 2 comprises a flange by way of which a nozzle 2 is screwed to an outer casing G of the combustion chamber 3.

[0036] FIG. 1 depicts, on an enlarged scale, the structure of an embodiment variant of a proposed nozzle assembly with a nozzle 2, on the nozzle head 21 of which multiple guide elements 22 that protrude in a fin-like or rib-like manner and are intended for influencing a swirled air flow are provided. Here, the nozzle 2 of FIG. 1 is in the form of the atomizer nozzle, in order to inject fuel into the combustion space 30 of the combustion chamber 3 of FIGS. 6A and 6B. Thus, the atomized fuel is introduced into the combustion space 30 at relatively high speed at a nozzle exit opening 210 of the nozzle head 21. In this respect, the nozzle head 21 adjoins a nozzle main body 20 of the nozzle 2 along a nozzle longitudinal axis DM.

[0037] Air-guiding ducts 50 and 51 are provided radially further to the outside in relation to the nozzle longitudinal axis DM on the nozzle assembly 2 illustrated. Air flows in towards the combustion space 30 by way of these air-guiding ducts 50 and 51. In the process, the (combustion) air introduced into the combustion space 30 by way of the air-guiding ducts 50 and 51 is selectively swirled in order to radially delineate, downstream of the nozzle exit opening 210, an injection cone 2A, visible in the sectional illustration of FIG. 2, for the injected fuel by means of an eddy current 5A and to provide a recirculation zone Z downstream of the nozzle head 21, which recirculation zone, when the fuel-air mixture is being combusted, is advantageous for the stability of the resulting flame. Here, a first air-guiding duct 50 lies between the nozzle head 21 and a second air-guiding duct 51 which is radially further to the outside. In this respect, in the present case the first air-guiding duct 50 ends in the region of the nozzle head 21 of the nozzle 2, with the result that a part of the air flow coming from the first air-guiding duct 50 is guided along an outer lateral surface 212 of the nozzle head 21, which tapers towards the nozzle end (and is frustoconical here).

[0038] In the present case, the swirl-affected air flow is applied to the nozzle head 21 from the first air-guiding duct 50 at an angle of substantially 90° in relation to the nozzle longitudinal axis DM. A part of the air flow from the first air-guiding duct 50 thus impinges on the lateral surface 212 of the nozzle head 21 in a radially inward direction at an angle of substantially 90° and is thus deflected at this lateral surface 212 and guided along it in the direction of the nozzle exit opening. This deflected part of the air flow then flows into the combustion space 30 substantially free of swirl. The non-deflected part of the air flow continues to be swirl-affected, with the result that a radially inner air flow flows into the combustion space 30 in a manner free of swirl and a radially outer air flow flows into the combustion space in a swirl-affected manner.

[0039] In the case of nozzle assemblies customary to date, under certain circumstances it can be observed that, on account of the swirl-affected air flows from the air-guiding ducts 50 and 51, a backflow RS of hot gas arises in the direction of the nozzle end, and here in particular as far as the nozzle head 21 of the nozzle 2. This backflow RS is therefore in particular aligned opposite to an injection direction ER for the atomized fuel, which is parallel to the nozzle longitudinal axis DM and along which the fuel is injected into the combustion space 30. As depicted in particular with reference to the illustration of FIG. 3A, as a result of the backflow RS it is possible in particular that hot gases and combustion products reach the nozzle head 21 and thus lead to undesirable heating of the nozzle head 21 at the nozzle end. In the extreme case, this heating can even lead to destruction of the nozzle head 21.

[0040] As part of the proposed solution, in the embodiment variant of the nozzle assembly of FIGS. 1 and 2, in this regard an improvement is achieved in that a multiplicity of guide elements 22 evenly distributed over the circumference is provided on the outer lateral surface 212 of the nozzle head 21. Here, these guide elements 22 respectively protrude on the lateral surface 212 in a fin-like or rib-like manner and have an elongate form and run in the direction of the nozzle end. Each guide element 22 is in the flow path of the air flow coming from the first air-guiding duct 50. Thus, at these guide elements 22, at least a part of the air flow coming from the first air-guiding duct 50 is guided along a lateral surface of the respective guide element 22 and thus selectively deflected in the direction of a central injection region EB which is directly downstream of the nozzle exit opening 210. The guide elements 22 on the nozzle head 21 thus lead to a straightened partial air flow in the direction of the central nozzle longitudinal axis DM behind the nozzle head 21. This partial air flow is aligned in the injection direction ER substantially free of swirl and thus effectively counteracts a backflow RS and in particular prevents the triggering of a backflow RS by way of which hot gases are conducted as far as the nozzle head 21.

[0041] This is also depicted in more detail in the illustration of FIG. 3B, which is based on experimental data. In the recirculation zone Z directly downstream of the nozzle 2 designed according to FIGS. 1 and 2, hot combustion gases no longer come back as far as the nozzle head 21.

[0042] The arrangement of the multiplicity of guide elements 22 on the lateral surface 212 of the frustoconical nozzle head 21 is depicted once again in FIG. 4, in which the nozzle 2 is illustrated on its own in a perspective view. Here, the nozzle head 21 adjoins the nozzle main body 20, which is connected to a nozzle stem 23 of the nozzle 2, along the nozzle longitudinal axis DM. The nozzle stem 23 establishes the connection to a fuel supply on the engine side and is secured to the flange via which the nozzle 2 is fixed to the outer casing G of the combustion chamber 3. In the case of the nozzle 2 of FIG. 4, the individual guide elements 22 each run in a straight line and extend over the majority of the length, measured along the nozzle longitudinal axis DM, of the nozzle head 21, here at least over ⅔ of the length of the nozzle head 21. Owing to the conical tapering of the nozzle head 21 towards the nozzle end, and thus the corresponding profile of the outer lateral surface 212, the individual protruding guide elements 22 follow the profile of the lateral surface 212 and each extend at an inclination in relation to the nozzle longitudinal axis DM. Each guide element 22, which in the present case has a rectangular cross section, here consequently extends in a virtual plane of extent parallel to the nozzle longitudinal axis DM.

[0043] By contrast, although the guide elements 22 of one embodiment variant of the nozzle 2 are spaced apart equidistantly from one another, like in the embodiment variant of FIG. 4, as per FIG. 5 they are slanted. Here, consequently, although each guide element 22 still runs in a straight line protruding on the outer lateral surface 212, they are inclined in the circumferential direction. The guide elements 22 of the nozzle 2 of FIG. 5 are therefore oblique in relation to the injection direction ER and have an inclination both in relation to the nozzle longitudinal axis DM and in the circumferential direction. For example, each guide element 22 runs on the outer lateral surface 212 at an angle of attack a in the range of 10° to 40°.

[0044] It is self-evident that the proposed solution is not limited to the exemplary embodiments described above, and various modifications and improvements can be made without departing from the concepts described here. Any of the features may be used separately or in combination with any other features, unless they are mutually exclusive, and the disclosure extends to and includes all combinations and subcombinations of one or more features which are described here.

LIST OF REFERENCE SIGNS

[0045] 11 Low-pressure compressor [0046] 12 High-pressure compressor [0047] 13 High-pressure turbine [0048] 14 Medium-pressure turbine [0049] 15 Low-pressure turbine [0050] 2 Nozzle [0051] 20 Nozzle main body [0052] 21 Nozzle head [0053] 210 Nozzle exit opening [0054] 212 Lateral surface [0055] 22 Guide element [0056] 23 Nozzle stem [0057] 2A Injection cone [0058] 3 Combustion chamber [0059] 30 Combustion space [0060] 31 Combustion chamber head [0061] 4 Combustor seal [0062] 50, 51 Air-guiding duct for creating radially external air eddy currents [0063] 5A Eddy current [0064] A Outlet [0065] B Bypass duct [0066] BK Combustion chamber assembly [0067] C Outlet cone [0068] DM Nozzle longitudinal axis [0069] E Inlet/Intake [0070] EB Injection region [0071] ER Injection direction [0072] F Fan [0073] F1, F2 Fluid flow [0074] FC Fan casing [0075] G Outer casing [0076] M Centre axis/Axis of rotation [0077] R Combustion chamber ring [0078] RS Backflow [0079] S Rotor shaft [0080] T (Turbofan) engine [0081] TT Turbine [0082] V Compressor [0083] Z Recirculation zone [0084] α Angle of attack