Injection device with injector with rich-lean combustion for combustion chamber

Abstract

The invention relates to a gaseous fuel injection device (10) of longitudinal axis (X) intended to be mounted on the bottom (94) of a combustion chamber (90) of a turbomachine, this injection device (10) comprising at least one flange (20) and at least one injector (30) extending from upstream to downstream along a main axis (R), these flanges (20) being located on either side of at least one injector (30). The injector (30) comprises a body (40) and a head (50) located downstream of the body (40), the fuel being suitable for direct injection into the space (45) between the body (40) and the head (50) through injection holes (60) located in the body (40) and the head (50), the body (40) being connected to at least one flange (20) by bars (70) extending in a first transverse direction (Y) perpendicular to the main axis (R). Figure 2

Description

Title of the invention: Injection device with injector with rich-lean combustion for combustion chamber

[0001] The invention relates to the field of combustion chambers of aircraft turbomachinery powered by a gaseous fuel such as dihydrogen and air. These aircraft include winged aircraft for civil or military aviation, helicopters, VTOLs, drones, APUs, turbojets, and turboprops.

[0002] In the case where the turbomachine is a twin-spool, twin-flow aircraft turbomachine extending along a longitudinal axis, the upstream compressor compresses the air that has entered the turbomachine from the upstream end. This air is admitted into the combustion chamber of the downstream turbomachine. The hot gases from this combustion are then expanded in a downstream turbine, causing this turbine to rotate. The rotation of this turbine drives the rotor of the turbomachine on which this turbine is mounted. The rotor, in turn, drives the rotation of the compressor and the fan blades located upstream of the turbomachine. The rotation of the fan blades, along with the high-speed ejection of the gases exiting the combustion chamber, contributes to the propulsion of the turbomachine.

[0003] The combustion chamber is annular and includes a plurality of injection devices which are distributed circumferentially on the bottom of the combustion chamber and which inject the fuel into the combustion chamber.

[0004] Thus, a gaseous fuel injection device with longitudinal axis X intended to be mounted in a turbomachine combustion chamber is known, this injection device comprising at least one flange and at least one injector extending from upstream to downstream along a main axis R.

[0005] During operation of the turbomachine, difficulties may sometimes be encountered in the gaseous fuel injection device, including flame instability downstream of the injectors in the operating range of the turbomachine, flame sticking at the downstream end of the injectors, and the phenomenon of "flashback" (flame returning upstream).

[0006] Furthermore, for environmental reasons, efforts are being made to use gaseous fuels other than kerosene (which is not gaseous), which emit fewer polluting carbon dioxide gases such as NOx, particulate matter, and fumes. One such less polluting fuel is dihydrogen. However, using dihydrogen as a fuel exacerbates the above-mentioned drawbacks, especially the risk of flashback and combustion instabilities because the flame speed is approximately ten times higher. hydrogen burns faster than kerosene. A higher flame temperature for hydrogen also increases NOx production. Description of the invention

[0007] The present invention aims to remedy these drawbacks.

[0008] The invention aims to provide an injection device that delivers more stable combustion across the entire combustion range, i.e., flame stability across the operating range of the turbomachine, and with a reduction or elimination of the flashback phenomenon. This injection device must also produce as little NOx as possible.

[0009] This goal is achieved thanks to the fact that the injector comprises a body and a head located downstream of the body along the main axis R such that a space exists between the body and the head, the gaseous fuel being able to be injected directly into the space through injection holes located in the body and / or in the head, the body being connected to at least one flange by bars which are located in the airflow which passes through the injection device.

[0010] Thanks to these arrangements, a rich combustion region with a low oxygen content (compared to stoichiometric conditions) is created in the space between the body and the nozzle, thereby reducing the combustion flame temperature and NOx production. Immediately downstream of this space, a lean combustion region with a high oxygen content is obtained, which also reduces the combustion flame temperature and NOx production. Furthermore, the presence of bars in the airflow through the injection device allows control of the air content in the space between the body and the nozzle and in the lean combustion region. This improves the gas-fuel mixture and helps prevent flame sticking to the injectors, stabilizes the flame, and avoids flame flashback phenomena, particularly when the fuel is hydrogen.

[0011] For example, the injection device further includes a separator which connects the body and the head and which separates the space into two cavities.

[0012] For example, the separator has gaseous fuel injection holes.

[0013] For example, the injection device comprises at least two flanges and at least one injector extending in a plane defined by the principal axis R which is parallel to the longitudinal axis X and a second transverse direction Z perpendicular to the first transverse direction Y and to the principal axis R, each of the at least two flanges extending in a plane parallel to this plane and the at least one injector being located between two adjacent flanges.

[0014] For example, the injection device comprises at least two coaxial annular flanges with longitudinal axis X, such that at least one injector is located between two adjacent flanges, and is annular and coaxial with these flanges, the principal axis R is parallel to the longitudinal axis X, the first transverse direction Y being radial and a second transverse direction Z perpendicular to the first transverse direction Y and to the principal axis R being circumferential.

[0015] For example, the injection device includes at least one helical flange with longitudinal axis X, such that at least one injector is helical and extends over at least a part of its helical length between two radially adjacent portions of at least one flange and is coaxial with at least one flange, the principal axis R is parallel to the longitudinal axis X, the first transverse direction Y being radial and a second transverse direction Z perpendicular to the first transverse direction Y and to the principal axis R being circumferential.

[0016] For example, the injection device includes at least two radial injectors, each extending in a radial plane with respect to the main axis R, which is parallel to the longitudinal axis X, and includes at least two flanges, each of said planes extending along a second radial transverse direction Z perpendicular to the first circumferential transverse direction Y and to the main axis R, each of the at least two flanges being radial and located between two adjacent injectors.

[0017] For example, the injection device includes at least two radial injectors, each extending in a radial plane with respect to the main axis R, which is radial and perpendicular to the longitudinal axis X, and includes at least two flanges, each of the planes extending along a second transverse direction Z parallel to the longitudinal axis X and perpendicular to the first transverse direction Y, which is circumferential, each of the at least two flanges being radial and located between two of the adjacent injectors.

[0018] The invention also relates to a combustion chamber comprising a plurality of injection devices according to the invention, distributed along the bottom of this chamber.

[0019] The invention also relates to a turbomachine comprising a combustion chamber according to the invention.

[0020] The invention will be better understood and its advantages will become more apparent upon reading the following detailed description of embodiments shown by way of non-limiting examples. The description refers to the accompanying drawings in which:

[0021] [Fig-1] Fig. 1 is a longitudinal cross-sectional view of a combustion chamber of a turbomachine carrying an injection device according to the invention.

[0022] [Fig.2] Fig.2 is a perspective view of an injector of an injection device according to the invention.

[0023] [Fig.3] The [Fig.3] is a side view of the injector of the [Fig.2].

[0024] [Fig.4] Fig.4 is a perspective view of a variant of an injector of an injection device according to the invention

[0025] [Fig.5] The [Fig.5] is a side view of the injector of the [Fig.4].

[0026] [Fig.6] Fig.6 is a front view along the longitudinal axis X of a device injection according to a first embodiment of the invention.

[0027] [Fig.7] The [Fig.7] is a front view along the longitudinal axis X of an injection device according to a second embodiment of the invention.

[0028] [Fig.8] The [Fig.8] is a front view along the longitudinal axis X of an injection device according to a third embodiment of the invention.

[0029] [Fig.9] The [Fig.9] is a front view along the longitudinal axis X of an injection device according to a fourth embodiment of the invention.

[0030] [Fig. 10] The [Fig. 10] is a cross-sectional view along line XX of a part of the injection device of the [Fig.9].

[0031] [Fig. 11] The [Fig. 11] is a front view along the longitudinal axis X of an injection device according to a fifth embodiment of the invention.

[0032] [Fig. 12] The [Fig. 12] is a cross-sectional view along line XILXII of part of the injection device of the [Fig.11]. Detailed description of the invention

[0033] In the description below, the terms "internal" and "inner" refer to an element oriented towards a reference axis or located closer to that axis. The terms "external" and "outer" refer to an element oriented in the opposite direction to that reference axis or located further from that axis. The terms "upstream" and "downstream" are relative to the direction of air and gas flow during the operation of the turbomachine, i.e., from left to right in [Fig. 1]. The term "radial" refers to a position or direction in a transverse plane perpendicular to the reference axis and passing through that reference axis.

[0034] Consider a turbomachine with longitudinal axis A, which is its axis of rotation. This turbomachine comprises a compressor, a combustion chamber 90, and a turbine. The combustion chamber 90 is located in a section of the turbomachine downstream of the compressor and upstream of the turbine. Air compressed by the compressor enters the combustion chamber 90, and fuel is injected into this combustion chamber 90 where it is burned with this compressed air. The hot gases generated by this combustion are ejected at high speed into the turbine.

[0035] As shown in [Fig. 1], the combustion chamber 90 is annular and is mounted between an inner shell 91 and an outer shell 92, which are cylindrical and coaxial with longitudinal axis A. These two shells (91, 92) define an annular space that is open upstream to a diffuser 93 which communicates with the compressor (not shown). The combustion chamber 90 is delimited by an upstream bottom wall 94, an inner shell 95 and an outer shell 96 coaxial with longitudinal axis A, and is open downstream to the turbine. The shells (95, 96) are assembled and fixed to the casings (93, 94) by flanges. The bottom wall 94 is substantially transverse to the axis of gas flow in the combustion chamber 90 and is provided with a plurality of circular openings 97. A shroud 98 located upstream of these openings 97 guides the air from the diffuser 93 to these openings 97. For each opening 97, the fuel is supplied by a pipe 99 to an injection device 10 which atomizes this fuel into the airflow to form a mixture.This mixture enters the combustion chamber 90 along a longitudinal axis X, which is the central axis of the injection device 10 and the direction of gas flow from the injection device 10. The longitudinal axis X passes through the center of the injection device 10. The longitudinal axis X is defined relative to the injection device 10 and is therefore of constant orientation. The injection device 10 is delimited by a wall 11. For example, this wall is cylindrical with a circular cross-section, as shown in the figures. The principal axis X of the injection device 10 is parallel, or not parallel, to the longitudinal axis A.

[0036] For each injector 30 (see below), a principal axis R is defined which gives the direction of air inlet at the upstream edge of the injector 30 and which is the axis along which this injector 30 extends from upstream to downstream. The principal axis R also gives the direction of gas (e.g., hydrogen) flow in an injector 30. The principal axis R is generally parallel to the longitudinal axis X (first, second, third, and fourth embodiments below); however, in the radial embodiment of the injection device 10 (fifth embodiment below), the principal axes R of the injectors are perpendicular to the longitudinal axis X. A first transverse direction Y (first transverse axis Z) is defined, perpendicular to the principal axis R, and a second transverse direction Z (second transverse axis Z) is defined, perpendicular to the first transverse direction Y and to the principal axis R.The thickness of an injector 30 is along the first transverse direction Y. A transverse plane is defined which is perpendicular to the principal axis R, and which therefore extends along the first transverse direction Y and the second transverse direction Z. The transverse directions (Y, Z) are defined at a given point of an injector 30. The transverse directions (Y, Z) are therefore either of constant orientation if the injector(s) 30 extend in parallel planes (first embodiment below), or of variable orientation if the injector(s) 30 are curved or are arranged radially (second, third, fourth and fifth embodiments below).

[0037] The injection device 10 comprises at least one flange 20 and at least one injector 30 extending from upstream to downstream along the main axis R (main direction R). The flange(s) 20 extend along the longitudinal axis R, or alternatively, extend along an axis distinct from the longitudinal axis R. The injector 30, or in certain embodiments each of the injectors 30, is surrounded by one or two adjacent flanges 20. Thus, two adjacent flanges 20 define a space in which an injector 30 is located, and the quantity of air passing around the injector 30 can be regulated by increasing or decreasing the distance between these two adjacent flanges 20.Depending on the geometry of the flanges 20, this space is for example rectangular in section (first embodiment below), annular in section (second embodiment below), helical in section (third embodiment below) or triangular in section (fourth and fifth embodiments below).

[0038] Each injector 30 has a body 40 and a head 50 located downstream of the body 40 along the principal direction R. The body 40 and the head 50 are separated by a gap 45 extending along the first transverse direction Y and the second transverse direction Z. The body 40 has an upstream edge 41 and a downstream edge 42. The upstream edge 41 is, for example, rounded. The head 50 has an upstream edge 51 and a downstream edge 52. The gap 45 therefore extends between the downstream edge 42 and the upstream edge 51. The downstream ends of the downstream edge 52 can be located at the same level, upstream, or downstream along the longitudinal direction X with respect to the downstream edge of a flange 20 that is adjacent to this injector 30.

[0039] For example, the injection device 10 comprises two flanges 20 and an injector 30 located between these two flanges 20. This injection device 10 is illustrated in [Fig. 2] in a perspective view. The principal axis R coincides with the longitudinal axis X. For clarity, the upper flange 20 is shown with a dashed line and is transparent.

[0040] The gaseous fuel is injected directly into the space 45 through injection holes 60 located in the body 40 and / or in the head 50. The downstream edge 42 and the upstream edge 51 have a plurality of these injection holes 60. The gaseous fuel exits on the one hand from the injection holes 60 of the downstream edge 42 and flows downstream, and on the other hand exits from the upstream edge 51 and flows upstream. These gaseous fuel flows are schematically represented by bold arrows labeled F on [Fig.3], which is a side view (in the (R,Y) plane) of the injector 30. These flows cause a vortex circulation of the gaseous fuel in space 45. This circulation allows for a mixing of air and fuel with a rich combustion since there is a surplus of fuel in space 45 and since the air passing through the injection device 10 tends not to enter space 45.Thus, we have a lower flame temperature and we reduce NOx production during this time. combustion. Advantageously, the injection holes 60 of the downstream edge 42 and the injection holes 60 of the upstream edge 51 are not opposite each other, which increases the turbulence in the space 45.

[0041] Since combustion in space 45 is rich, some of the fuel is not consumed and exits space 45 to circulate in the areas between the injector 30 and the flange(s) 20 located above and below the injector 30. In these areas, the fuel is rapidly cooled and mixes with the air flowing through the injection device 10 in the main direction R (this air is indicated by the white arrows labeled A). This mixture burns leanly downstream of the downstream edge 52 of the head 50 and the downstream edge of the flanges 20. This results in a lower flame temperature and reduces NOx production during this combustion.

[0042] The injection device 10 includes bars 70 that connect the body 40 to the flange 20 adjacent to the body 40. Where a flange 20 is located above and below (along the first transverse axis Y) the injector 30, bars 70 connect the body 40 to each of these flanges 20. The bars 70 are positioned along the second transverse direction Z. Thus, the bars 70 are located in the airflow that passes through the injection device 10. By varying the distances between the bars 70, this airflow is modified to optimize the rich and lean combustion described above. This reduces NOx production during these combustion processes. For example, the bars 70 extend along the first transverse direction Y perpendicular to the main axis R. Alternatively, at least one of the bars 70 is inclined with respect to the first transverse direction Y. The bars 70 are arranged periodically or irregularly.Furthermore, modifying the cross-section of the 70 bars also optimizes these combustion processes. For example, this cross-section is chosen from the group consisting of rectangular, triangular, and circular cross-sections.

[0043] The degree of combustion optimization achieved by the positioning and geometry of the bars 70 depends on numerous factors, including the operating regime of the turbomachine and the type of fuel used, and it is not possible to deduce these parameters of the bars 70 from their general characteristics. Nevertheless, tests carried out by the inventors have shown that the shape and characteristics of the bars 70 influence the drag and recirculation zones downstream of these bars 70. Thus, thicker bars 70 have a greater influence on the flow downstream of these bars 70.

[0044] Alternatively, the injection device 10 further comprises a separator 80 which connects the body 40 and the head 50 and separates the space 45 into a first cavity 451 and a second cavity 452. The first cavity 451 is located above the separator 80 and the second cavity 452 is located below the separator 80 in the first direction Transverse Y. The separator 80 extends along the second transverse direction Z along the downstream edge 42 of the body 40 and the upstream edge 51 of the head 50. This injection device 10 is shown in [Fig. 4] in a perspective view. This injection device 10 is identical to the device shown in [Fig. 2] except for the addition of the separator 80. [Fig. 5] is a side view (in the (R,Y) plane) of the injector 30 of this injection device 10. Each cavity (451, 452) is bordered by the downstream edge 42 of the body 40, the upstream edge 51 of the head 50, and the separator 80. Injection holes 60 located on the downstream edge 42 and on the upstream edge 51 open into each cavity (451, 452). Fuel vortices therefore occur in each cavity (451, 452). For example, separator 80 is continuous and has a rectangular cross-section in the (R, Y) plane, as illustrated in [Fig. 4]. Alternatively, separator 80 is segmented into disjoint segments.Alternatively, separator 80 has an oblong or circular cross-section in the (R, Y) plane. For example, separator 80 has raised features.

[0045] Advantageously, the separator 80 further has gaseous fuel injection holes 60, some of which open into the upper cavity 451 and others into the lower cavity 452. The turbulence in these cavities (451, 452) is therefore increased. This situation is shown in Figures 4 and 5.

[0046] As illustrated in Figures 2 to 5, the head 50 of an injector 30 is continuous (i.e., is a single piece) along the second transverse direction Z. Alternatively, the head 50 is divided into sections (each section forming a micro-injector) which are distributed along the second transverse direction. Thus, when the injection device 10 comprises several injectors 30, the set of heads 50 forms an array. For example, the heads 50 are miniaturized to form an array of micro-injectors, each head 50 forming a micro-injector having one or more injection holes 60.

[0047] A first embodiment of the invention is described below in which the injectors 30 each extend in a distinct plane.

[0048] The injection device 10 comprises a plurality of flanges 20 that are substantially flat and parallel to each other, and at least one injector 30, each injector 30 being located between two adjacent flanges 20. The flanges 20 and the injectors 30 each extend in a plane along the longitudinal directions X and Z. The bars 70 are perpendicular to the injectors 30 and extend along the first transverse direction Y. The first transverse direction Y is therefore perpendicular to the flanges 20 and the injectors 30. The first transverse direction Y and the second transverse direction Z are constant. The principal direction R is the same as the longitudinal direction X. This configuration is shown in [Fig. 6] in the case of four flanges 20 and three injectors 30.

[0049] A second embodiment of the invention is described below in which the injectors 30 are annular.

[0050] The injection device 10 comprises a plurality of coaxial annular flanges 20 with longitudinal axis X and a plurality of coaxial annular injectors 30 with the flanges 20, each injector 30 being located between two adjacent flanges 20 except for the most central injector 30 and the injector 30 furthest from the longitudinal axis X. The injectors 30 are curved. The principal direction R coincides with the longitudinal direction X. In this configuration, the first transverse direction Y is radial and the second transverse direction Z is circumferential. Thus, the direction of the first transverse direction Y and the direction of the second transverse direction Z vary as one moves along an injector 30 around the longitudinal axis X. The bars 70 are perpendicular to the injectors 30 and extend radially, each with a different orientation. This configuration is shown in [Fig.7] in the case of three flanges 20 and two injectors 30. Alternatively, an additional flange 20 may be located at the center of the most central injector 30 and an additional flange 20 may surround the injector 30 furthest from the longitudinal axis X, such that each injector 30 is located between two adjacent flanges 20.

[0051] A third embodiment of the invention is described below in which the injectors 30 are helical.

[0052] The injection device 10 comprises at least one helical flange 20 with longitudinal axis X and at least one helical injector 30 which is coaxial with this flange 20 and which extends over at least a portion of, for example over its entire helical length between two radially adjacent portions of the flange 20. The injectors 30 are curved. The principal direction R coincides with the longitudinal direction X. In this configuration, the first transverse direction Y is radial and the second transverse direction Z is circumferential. Thus, the direction of the first transverse direction Y and the direction of the second transverse direction Z vary as one moves along an injector 30 around the longitudinal axis X. The bars 70 are perpendicular to the injectors 30 and extend radially, each with a different orientation. This configuration is shown in [Fig.8] in the case of a flange 20 and an injector 30. .

[0053] A fourth embodiment of the invention is described below in which the injectors 30 are radial and the air inlet in an injector is longitudinal.

[0054] The injection device 10 comprises a plurality of radial injectors 30, each extending in a plane (R, Z) passing through the longitudinal axis X, and a plurality of radial flanges 20, each extending in a plane also passing through the longitudinal axis X, each injector 30 being located between two flanges 20 adjacent. The bars 70 are perpendicular to the injectors 30 and curved, extending circumferentially around the longitudinal axis X, each with a different radius. Air enters the injection device 10 along the longitudinal direction X. The principal direction R coincides with the longitudinal direction X. In this configuration, the first transverse direction Y is circumferential and the second transverse direction Z is radial. Thus, the direction of the first transverse direction Y and the direction of the second transverse direction Z vary with the position of the injector 30 around the longitudinal axis X. This configuration is shown in [Fig. 9] for four flanges 20 and four injectors 30.

[0055] Figure 10 is a cross-sectional view in the radial plane (R, Z) of a portion of the device injection device 10 which shows an injector 30. Air and gas flow through the injection device 10 in the longitudinal direction X and exit in the longitudinal direction X.

[0056] A fifth embodiment of the invention is described below in which the injectors 30 are radial and the air inlet in an injector is radial.

[0057] The injection device 10 comprises a plurality of radial injectors 30, each extending in a plane (R, Z) passing through the longitudinal axis X, and a plurality of radial flanges 20, each extending in a plane also passing through the longitudinal axis X, each injector 30 being located between two adjacent flanges 20. The bars 70 are perpendicular to the injectors 30 and curved, extending circumferentially around the longitudinal axis X to form rings of the same radius. Unlike the fourth embodiment, air enters the injection device 10 in a radial direction, which is the direction R. The principal direction R is perpendicular to the longitudinal direction X. In this configuration, the first transverse direction Y is circumferential and the second transverse direction Z is longitudinal.Thus, the direction of the first transverse direction Y and the direction of the main axis R vary with the position of the injector 30 around the longitudinal axis X. This configuration is represented in [Fig. 1 1] in the case of four flanges 20 and four injectors 30. The flanges 20 may have a curved cross-section, for example in the shape of a blade, in order to optimize the air circulation between a flange 20 and an injector 30.

[0058] Figure 12 is a cross-sectional view in the radial plane (R, Z) of a portion of the device Injection device 10 showing an injector 30. Air and gas enter the injection device 10 in a radial direction R towards the inside. Air and gas exit the injection device 10 through the center of this injection device 10 in the longitudinal direction X.

[0059] The invention also relates to a combustion chamber comprising a plurality of injection devices 10 as described above. These devices injection points are distributed along the bottom 94 of this chamber 90. For example, this chamber is annular.

[0060] The invention also relates to a turbomachine comprising a combustion chamber 90 according to the invention.

Claims

Demands

1. A gaseous fuel injection device (10) with a longitudinal axis (X) for mounting in a turbomachine combustion chamber (90), said injection device (10) comprising at least one flange (20) and at least one injector (30) extending upstream to downstream along a principal axis (R), said at least one injector (30) being characterized in that it comprises a body (40) and a head (50) located downstream of said body (40) along said principal axis (R) such that a space (45) exists between said body (40) and said head (50), the gaseous fuel being capable of being injected directly into said space (45) through injection holes (60) located in said body (40) and / or in said head (50), said body (40) being connected to said at least one flange (20) by bars (70) which are located in the flow of air which passes through said injection device (10).

2. Injection device (10) according to claim 1 further comprising a separator (80) which connects said body (40) and said head (50) and which separates said space (45) into two cavities (451, 452).

3. Injection device (10) according to claim 2 wherein said separator (80) has gaseous fuel injection holes (60).

4. Injection device (10) according to any one of claims 1 to 3, wherein it comprises at least two flanges (20) and at least one injector (30) extending in a plane defined by said principal axis (R) which is parallel to said longitudinal axis (X) and a second transverse direction (Z) perpendicular to said first transverse direction (Y) and said principal axis (R), each of said at least two flanges (20) extending in a plane parallel to said plane and said at least one injector (30) being situated between two of said adjacent flanges (20).

5. Injection device (10) according to any one of claims 1 to 3, wherein it comprises at least two coaxial annular flanges (20) with longitudinal axis (X), wherein said at least one injector (30) is located between two of said adjacent flanges (20) and is annular and coaxial with said flanges (20), said principal axis (R) being parallel to said longitudinal axis (X), said first transverse direction (Y) being radial and a second transverse direction (Z) perpendicular to said first transverse direction (Y) and said principal axis (R) being circumferential.

6. Injection device (10) according to any one of claims 1 to 3, wherein it comprises at least one helical flange (20) with longitudinal axis (X), wherein said at least one injector (30) is helical and extends over at least a portion of its helical length between two radially adjacent portions of said at least one flange (20) and is coaxial with said at least one flange (20), said principal axis (R) being parallel to said longitudinal axis (X), said first transverse direction (Y) being radial and a second transverse direction (Z) being perpendicular to said first transverse direction (Y) and said principal axis (R) being circumferential.

7. Injection device (10) according to any one of claims 1 to 3, wherein it comprises at least two radial injectors (30), each extending in a radial plane with respect to said principal axis (R), which is parallel to said longitudinal axis (X), and comprising at least two flanges (20), each of said planes extending along a second radial transverse direction (Z) perpendicular to said first circumferential transverse direction (Y) and to said principal axis (R), each of said at least two flanges (20) being radial and situated between two of said adjacent injectors (30).

8. Injection device (10) according to any one of claims 1 to 3, wherein it comprises at least two radial injectors (30), each extending in a radial plane with respect to said principal axis (R), which is radial and perpendicular to said longitudinal axis (X), and comprising at least two flanges (20), each of said planes extending along a second transverse direction (Z) parallel to said longitudinal axis (X) and perpendicular to said first transverse direction (Y), which is circumferential, each of said at least two flanges (20) being radial and situated between two of said adjacent injectors (30).

9. Combustion chamber (90) comprising a plurality of injection devices (10) according to any one of the preceding claims, distributed along said bottom (94) of this chamber (90).

10. Turbomachine comprising a combustion chamber (90) according to claim 9.

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