EP3877699B1 - Injector nozzle for turbomachine comprising a primary fuel circuit arranged around a secondary fuel circuit - Google Patents

Description

TECHNICAL AREA

The invention relates to the general field of fuel injectors which equip the combustion chamber of a turbomachine, in particular a turbomachine of the type intended for the propulsion of aircraft.

PRIOR ART

The combustion chambers of turbomachines are generally equipped with fuel injectors associated with premixing systems, commonly referred to as "injection systems", generally comprising one or more swirls (axial and/or radial), also referred to as "swirls ”, which use the air coming from a compressor arranged upstream of the combustion chamber to spray the fuel into the combustion chamber.

Two categories of injectors are commonly used: aerodynamic injectors, which mainly use the pressure and air velocity at the compressor outlet to rotate the fuel at the outlet of the injector nose, and aeromechanical injectors which use primarily fuel pressure inside the injector nose to spin up and atomize the fuel.

Furthermore, the nozzles of the dual fuel circuit injectors comprise a primary fuel circuit, also called the pilot circuit, comprising a primary fuel swirl supplying a primary injector (also called the pilot injector) arranged on an axis of the injector nose, and a secondary fuel circuit, also called the main circuit, comprising a secondary fuel swirl feeding a secondary injector (also called the main injector) arranged around the primary injector. These may be aero-mechanical injectors or a combination of an aeromechanical primary injector and an aerodynamic secondary injector.

The use of this type of injector has developed to meet ever more stringent standards in terms of pollutant emissions.

The primary circuit is generally intended to supply the combustion chamber with fuel at all speeds, in particular during the ignition and winding phases, that is to say propagation of the flame to neighboring sectors.

The secondary circuit is intended to supply the engine at speeds ranging from cruising flight to takeoff.

The nozzles of the injectors are generally subjected to the high temperatures of the combustion chamber, which causes a risk of coking of the stagnant fuel within the secondary fuel circuit at the speeds of the turbomachine at which the secondary injector does not is not in operation.

A known solution consists in arranging a cooling air circuit on the periphery of the injector nose in order to provide thermal protection and thermal cooling of the entire injector nose.

However, this solution has the particular drawback of increasing the size of the injector nose.

Another solution, known from the documents US20160237911A1 , FR2896303 A1 and US20070068164A1 , consists in arranging an upstream part of the primary fuel circuit around an upstream part of the secondary fuel circuit.

The injector nozzles presented in these documents do not, however, allow the injection of air between the primary and secondary injectors.

DISCLOSURE OF THE INVENTION

The object of the invention is in particular to remedy this problem while limiting the radial size of the injector nose.

It proposes for this purpose an injector nose for a turbomachine, comprising a primary fuel circuit terminated by a fuel ejection nozzle opening onto an injection axis, and a secondary fuel circuit comprising a fuel ejection terminal part of annular shape arranged around the fuel ejection nozzle, and in which an upstream part of the primary fuel circuit, housed in the injector nose, comprises an annular channel extending around the secondary fuel circuit and delimited by an outer wall of the injector nose.

According to the invention, the injector nose further comprises air inlet channels extending through the annular channel of the primary fuel circuit and having respective inlets opening in the outer wall and respective outlets opening into an annular air injection channel arranged radially inward with respect to the fuel ejection terminal part, around the fuel ejection nozzle, and cooperating with the fuel ejection terminal part to form an aerodynamic secondary injector.

Because fuel circulates in the upstream part of the primary circuit regardless of the operating speed of the turbomachine, the upstream part of the primary circuit thus makes it possible to provide thermal protection and cooling of the injector nose, in particular of the secondary circuit around which extends the upstream part of the primary circuit.

In addition, the integration of air inlet channels, which extend through the annular channel of the primary fuel circuit and have respective inlets opening in the outer wall and respective outlets opening into an annular channel air injector arranged radially inward relative to the fuel ejection terminal part, allows the injection of air intended to mix with the fuel of the secondary fuel circuit within the injector nose , in a particularly compact manner, especially in the radial direction.

Preferably, the primary fuel circuit comprises primary connecting channels connecting the upstream part of the primary fuel circuit to the fuel ejection nozzle and comprising respective inlets and respective outlets, the respective inlets being arranged radially towards the external to the respective outputs.

Preferably, the secondary fuel circuit comprises a tubular channel centered on the injection axis and which is divided, at a downstream end, into several secondary connection channels each shaped to move away from the injection axis in a direction from upstream to downstream, and each arranged between two consecutive primary connection channels.

Preferably, the annular channel of the upstream part of the primary fuel circuit is arranged around the tubular channel and around the secondary connecting channels of the secondary fuel circuit.

Preferably, the secondary fuel circuit comprises a secondary fuel swirl formed of swirl channels having respective upstream ends, and having respective downstream ends opening into the terminal fuel ejection part.

Preferably, the secondary fuel circuit comprises a secondary plenum chamber of annular shape to which the respective upstream ends of the swirl channels forming the secondary fuel swirl are connected.

Preferably, the annular channel of the upstream part of the primary fuel circuit extends downstream beyond the primary connecting channels so as to form a terminal annular chamber surrounding the secondary fuel swirl.

Preferably, each swirl channel has a passage section which is reduced in a direction going from the upstream end towards the downstream end of the swirl channel.

Preferably, the secondary fuel circuit comprises a secondary plenum chamber of annular shape to which the respective upstream ends of the swirl channels forming the secondary fuel swirl are connected.

The invention also relates to an injection module for a turbomachine, comprising an injection system, and an injector nose of the type described above, in which the injection system comprises, from upstream to downstream , a socket in which is mounted the injector nose, at least one air intake swirl opening downstream of the injector nose, and a bowl.

The invention also relates to a turbomachine, comprising at least one injector nose of the type described above, or at least one injection module of the type described above.

BRIEF DESCRIPTION OF DRAWINGS

• la figure 1 est une vue schématique en coupe axiale d'une turbomachine selon un mode de réalisation préféré de l'invention ;
• la figure 2 une vue schématique en section axiale d'une chambre de combustion de la turbomachine de la figure 1 ;
• la figure 3 est une vue schématique en perspective et en coupe axiale d'un nez d'injecteur équipant la chambre de combustion de la figure 2 ;
• la figure 4 est une vue schématique en perspective et en coupe axiale du nez d'injecteur de la figure 3 privé d'un embout terminal d'un circuit primaire de carburant, et vu sous un angle différent ;
• la figure 5 est une vue schématique en perspective et en coupe oblique du nez d'injecteur de la figure 3 ;
• la figure 6 est une vue schématique du nez d'injecteur de la figure 3, vu de face depuis l'aval ;
• la figure 7 est une vue schématique en perspective du nez d'injecteur de la figure 3 ;
• la figure 8 est une vue schématique partielle en perspective du circuit primaire de carburant du nez d'injecteur de la figure 3 ;
• la figure 9 est une vue schématique partielle en perspective d'un circuit secondaire de carburant du nez d'injecteur de la figure 3 ;
• la figure 9A est une vue à plus grande échelle d'une partie de la figure 9.

The invention will be better understood, and other details, advantages and characteristics thereof will appear on reading the following description given by way of non-limiting example and with reference to the appended drawings in which:

• the figure 1 is a schematic view in axial section of a turbomachine according to a preferred embodiment of the invention;
• the figure 2 a schematic view in axial section of a combustion chamber of the turbomachine of the figure 1 ;
• the picture 3 is a schematic view in perspective and in axial section of an injector nose fitted to the combustion chamber of the picture 2 ;
• the figure 4 is a schematic view in perspective and in axial section of the injector nose of the picture 3 deprived of a terminal fitting of a primary fuel circuit, and seen from a different angle;
• the figure 5 is a schematic view in perspective and in oblique section of the injector nose of the picture 3 ;
• the figure 6 is a schematic view of the injector nose of the picture 3 , seen from the front from downstream;
• the figure 7 is a schematic perspective view of the injector nose of the picture 3 ;
• the figure 8 is a partial schematic perspective view of the primary fuel circuit of the injector nose of the picture 3 ;
• the figure 9 is a partial schematic perspective view of a secondary fuel circuit of the injector nose of the picture 3 ;
• the figure 9A is a larger scale view of part of the figure 9 .

DETAILED DISCUSSION OF PREFERRED EMBODIMENTS

The figure 1 illustrates a turbomachine 10 for an aircraft of a known type, generally comprising a fan 12 intended for the suction of an air flow which is divided downstream of the fan into a primary flow circulating in a flow channel of primary flow, hereinafter referred to as primary stream PF, within a core of the turbomachine, and a secondary flow bypassing this core in a secondary flow flow channel, hereinafter referred to as secondary stream SF.

The turbomachine is for example of the double-flow, double-body type. The heart of the turbomachine thus generally comprises a low pressure compressor 14, a high pressure compressor 16, a combustion chamber 18, a high pressure turbine 20 and a low pressure turbine 22.

The respective rotors of the high-pressure compressor and of the high-pressure turbine are connected by a so-called "high-pressure shaft", while the respective rotors of the low-pressure compressor and of the low-pressure turbine are connected by a so-called "low-pressure shaft". in a well-known way.

The turbomachine is streamlined by a nacelle 24 surrounding the secondary stream SF. Furthermore, the rotors of the turbine engine are rotatably mounted around a longitudinal axis 28 of the turbine engine.

Throughout this description, the longitudinal direction X is the direction of the longitudinal axis 28.

In addition, in a first part of this description, the radial direction R is at all points a direction orthogonal to the longitudinal axis 28 and passing through the latter, and the circumferential or tangential direction C is at all points a direction orthogonal to the radial direction R and to the longitudinal axis 28. The terms “internal” and “external” respectively refer to a relative proximity, and a relative remoteness, of an element with respect to the longitudinal axis 28. Furthermore, the “Upstream” and “downstream” directions are defined by reference to the general direction of gas flow in the primary PF and secondary SF streams of the turbomachine.

The picture 2 represents the combustion chamber 18 of the turbomachine 10 of the figure 1 and its immediate environment.

Conventionally, this combustion chamber, which is for example of the annular type, comprises two coaxial annular walls, respectively radially internal 32 and radially external 34, which extend from upstream to downstream, in the direction 36 d flow of the primary gas flow in the turbomachine, around the longitudinal axis 28 of the turbomachine. These internal 32 and external 34 annular walls are interconnected at their upstream end by an annular chamber bottom wall 40 which extends substantially radially around the longitudinal axis 28. This annular chamber bottom wall 40 is equipped with injection systems 42 distributed around the longitudinal axis 28, one of which is visible on the picture 2 , each receiving an injector nose 43 mounted at the end of an injector rod 45, to allow the injection of a premixture of air and fuel centered along a respective injection axis 44.

More specifically, each injection system 42 comprises a sleeve 46, commonly referred to as a “sliding bushing”, in which the corresponding injector nose 43 is mounted with a sliding faculty to allow differential thermal expansions in operation.

In the example illustrated, the sleeve 46 internally delimits a single air intake swirl 48, for example of the axial type, formed within the injection system 42.

Each injection system 42 further comprises a divergent bowl 49 arranged at the outlet of the air intake swirl 48 and opening into the combustion chamber 18.

The assembly formed by an injection system 42 and the corresponding injector nose 43 constitutes an injection module, in the terminology of the present invention.

In operation, part 50 of an air flow 52 coming from a diffuser 54 and coming from the high pressure compressor 16 supplies the injection systems 42, while another part 56 of the air flow 52 supplies air inlets 58 formed in the walls 32 and 34 of the combustion chamber, in a well-known manner.

In the remainder of this description, with reference to figures 3 to 9 , the radial direction R' is at all points a direction orthogonal to the injection axis 44 and passing through the latter, and the circumferential or tangential direction C' is at all points a direction orthogonal to the radial direction R' and to the injection axis 44. The terms “internal” and “external” respectively refer to a relative proximity, and a relative remoteness, of an element with respect to the injection axis 44. Furthermore, the directions "upstream" and "downstream" are defined by reference to the general direction of air and fuel flow in the injector nose 43. In addition, a transverse plane is defined as a plane orthogonal to the injection axis 44, while an axial plane is defined as the plane containing the injection axis 44.

The figures 3 to 9 illustrate in more detail an injector nose 43 according to a preferred embodiment of the invention.

The injector nose 43 comprises a body 60, preferably in one piece, comprising an end piece 61 ( figure 3 and 5 ) by which the injector nose 43 is intended to be connected to an injector rod 45 as on the figure 2 .

Within the body 60 are arranged two fuel circuits, namely a primary circuit 62 and a secondary circuit 64 ( picture 3 ).

The primary circuit 62 ends with a central fuel ejection nozzle 66 of the aeromechanical type, while the secondary circuit 64 has a terminal fuel ejection part 68 of the aerodynamic type arranged around the fuel ejection nozzle 66 ( figures 3-6 ), as will become clearer in the following.

The primary circuit 62 comprises an annular channel 70 defined between an outer wall 72, of generally annular shape, of the body 60 ( figures 3-7 ) which delimits the latter on the outside, and an internal envelope 74 which is generally annular and of complex shape, shown isolated on the figure 8 .

The primary circuit 62 further comprises primary connection channels 76 ( figures 3, 4 and 8 ) which connect the annular channel 70 to an inlet chamber 78 ( figures 3 and 4 ) of the fuel ejection nozzle 66. The channels of primary connections 76 are for example four in number and are preferably regularly distributed around the injection axis 44.

The inlet chamber 78 is arranged in the injection axis 44, radially inward with respect to the annular channel 70.

The primary connection channels 76 thus have respective inlets connected to the annular channel 70, and respective outlets connected to the inlet chamber 78. The respective inlets of the primary connection channels 76 are arranged radially outwards with respect to their respective outputs. In the example illustrated, the primary connecting channels 76 extend along respective directions substantially orthogonal to the injection axis 44, for example substantially radial.

The annular channel 70 extends downstream beyond the primary connection channels 76 so as to form a terminal annular chamber 79.

The fuel ejection nozzle 66 comprises a core 80 which forms part of the body 60 and which is centered on the injection axis 44 and arranged at a downstream end of the inlet chamber 78 ( figures 3 to 6 ). The core 80 has an upstream part 82 which extends downstream into an annular surface 84 which internally delimits a primary plenum chamber 86 of annular shape within the fuel ejection nozzle 66. Supply channels 87 inclined with respect to the injection axis 44 and with respect to the radial direction R' connect the inlet chamber 78 to the primary plenum chamber 86. Ortho-radial injection channels 88 ( figure 4 and 6 ), that is to say orthogonal to the injection axis 44 and not intersecting with the latter, connect a downstream end of the primary plenum chamber 86 to a converging swirl chamber 90 ( picture 3 ). The orientation of the injection channels 88 makes it possible to promote the gyration of the fuel within the swirl chamber 90.

The primary circuit 62, and more particularly the fuel ejection nozzle 66, comprises a terminal fitting 92 ( figure 3 and 5 ) which is mounted on a downstream end of the body 60 and which externally delimits the primary plenum chamber 86 and the swirl chamber 90. This end piece 92 comprises a upstream part of cylindrical shape of revolution externally delimiting the primary plenum chamber 86, and a downstream part of frustoconical shape externally delimiting the swirl chamber 90 and terminated by a fuel ejection orifice 93 ( picture 3 ) intended to diffuse the fuel from the swirl chamber 90 in the form of a spray.

The secondary circuit 64 will now be described with reference to the figures 3-6 and 9 . The figure 9 shows the internal volume of the secondary circuit 64, that is to say the space occupied by the fuel in operation. The walls delimiting the various parts of the secondary circuit 64 which will be described are visible as reliefs within the internal envelope 74 of the primary circuit 62, visible on the figure 8 .

The secondary circuit 64 comprises a tubular channel 100 (of which only one end part is shown in the figures), centered on the injection axis 44, and delimited on the outside by a cylindrical wall 102 (of which only one end part is shown in the figures). figures), which internally delimits an upstream part of the annular channel 70 of the primary circuit (and which therefore forms an upstream part of the aforementioned internal casing 74).

As it appears more clearly on the figure 9 which represents the secondary circuit 64 isolated from the rest of the injector nose, the tubular channel 100 is divided, at its downstream end, into four secondary connection channels 104 regularly distributed around the injection axis 44 and each shaped to s move away from the injection axis 44 in the direction going from upstream to downstream.

Each of the secondary connection channels 104 is for example inscribed in a respective axial plane. The secondary connecting channels 104 have respective downstream ends opening onto an upstream end surface 106 of a secondary plenum chamber 108 of annular shape, centered on the injection axis 44. This secondary plenum chamber 108 is delimited downstream by a downstream end surface 110 into which open respective upstream ends 111 of auger channels 112 forming a secondary fuel auger 114.

The auger channels 112 have respective downstream ends 115 ( figure 4 , 6 and 9 ) opening into an annular space constituting the terminal ejection part 68 of the secondary circuit 64. As shown by the figures 3, 4 and 6 , this annular space is delimited externally by an annular outer lip 116 of the body 60 having a free end 117, and is delimited internally by an annular inner lip 118 of the body 60 having a free end 119.

As shown in figure 4 , the secondary plenum chamber 108 and the spin channels 112 extend around an annular wall 120 which extends downstream forming the inner lip 118, and which has an inner radius R1 which is for example greater than an outer radius R2 of the cylindrical wall 102 which internally delimits the upstream part of the annular channel 70 of the primary circuit.

The secondary connection channels 104 each form, with the injection axis 44, an angle Ω which is preferably between 30 degrees and 60 degrees, and which is for example equal to 45 degrees ( figure 4 ).

As it appears on the figure 8 , the secondary connection channels 104 delimit between them, two-by-two, spaces respectively forming the primary connection channels 76 belonging to the primary circuit 62.

Moreover, as more clearly shown by the figure 3 and 8 , the secondary fuel swirl 114 is surrounded by the terminal annular chamber 79 which extends the annular channel 70 of the primary circuit 62.

The injector nose 43 also incorporates an air inlet twist 122 ( figure 4 , 5 and 8 ) and an annular air injection channel 124 cooperating with the terminal ejection part 68 of the secondary circuit 64 to form an aerodynamic secondary injector.

The air inlet swirl 122 is formed of air inlet channels 126, for example four in number, having respective inlets 128 ( figure 7 ) opening into the outer wall 72 of the body 60, and respective outlets 130 ( figures 4-6 ) opening into the annular air injection channel 124, preferably in a substantially orthoradial manner in order to promote the gyration of the air around the injection axis 44.

The air inlet channels 126 extend through the annular channel 70 of the primary circuit 62, between the secondary connecting channels 104 ( figure 8 ).

The annular air injection channel 124 is delimited externally by the annular wall 120, and internally by the fuel ejection nozzle 66, in particular by the end fitting 92 ( figures 3 and 4 ). The annular air injection channel 124 is thus arranged radially inside with respect to the fuel ejection terminal part 68 and is arranged around the fuel ejection nozzle 66.

As emerges from the foregoing, an upstream part of the primary circuit 62, housed in the injector nose 43, and formed in this case by the annular channel 70 and the terminal annular chamber 79, extends around the secondary circuit 64. This upstream part of the primary circuit 62 is delimited on the outside by the outer wall 72 of the body 60 of the injector nose, so that the upstream part of the primary circuit 62 extends around the periphery of the injector nose.

Because fuel circulates in the upstream part of the primary circuit 62 regardless of the operating speed of the turbomachine, the upstream part of the primary circuit 62 thus makes it possible to provide thermal protection and cooling of the injector nose 43.

In particular, the terminal annular chamber 79 makes it possible to ensure the thermal protection and cooling effect of the injector nose 43 beyond the primary connecting channels 76, in the downstream direction, and in particular makes it possible to provide thermal protection and cooling of the secondary fuel swirl 114.

With reference to figures 9 and 9A , the swirl channels 112 each extend along a respective plane P forming an acute angle θ with the direction D of the injection axis, preferably between 40 degrees and 60 degrees, and for example equal to 50 degrees.

By way of example, each of the swirl channels 112, forming the secondary fuel swirl 114, has an evolving passage section, which is reduced in the direction going from the upstream end 111 towards the downstream end 115 of the channel. The The reduction in cross section between the upstream end and the downstream end of each of the auger channels 112 is preferably between 10 and 50 percent of the cross section at the upstream end of the channel.

Reducing the passage section of each of the twist channels 112 makes it possible to increase the pressure drop between the inlet and the outlet of the secondary fuel twist 114 and in particular thus to accelerate the fuel within the secondary twist. fuel 114, while allowing lower fuel flow rates at equal pressure at the inlet of the secondary spin.

The passage section at the inlet of each of the auger channels 112 is for example equal to 0.2 mm ² .

In addition, each of the swirl channels 112 is curved in the corresponding plane P, so that a direction D1 tangent to a mean line L of the channel at the level of the downstream end 115 of the latter makes an angle α with a direction D2 tangent to the mean line L of the channel at the level of the upstream end 111 of the latter. The angle α is preferably between 5 degrees and 15 degrees, and is for example equal to 8 degrees. Due to its curvature, each of the swirl channels 112 extends substantially at a constant distance from the injection axis 44, from the upstream end to the downstream end of the channel 112.

It should be noted that the body 60 is preferably made by additive manufacturing. In the example illustrated, this body 60 forms the entirety of the injector nose 43 with the exception of the end piece 92. Additive manufacturing techniques are in fact particularly advantageous for producing the body 60 due to the geometry complex of the latter.

In operation, fuel circulates in the primary circuit 62 and is ejected in the form of a jet at the outlet of the fuel ejection nozzle 66, whatever the speed of the turbomachine.

At speeds ranging from cruise flight to takeoff, fuel also circulates in the secondary circuit 64. This fuel is rotated and accelerated by crossing the spin channels 112 forming the secondary spin of fuel 114, and forms, at the outlet thereof, a film of swirling fuel within the terminal ejection part 68 of the secondary circuit 64.

At these operating speeds, the flow of air set in rotation by the air inlet swirler 122, and introduced into the annular air injection channel 124, presents a sufficient flow rate to shear the film of fuel at the level of the free end 119 of the inner lip 118 and of the free end 117 of the outer lip 116.

Claims (11)

1. Injector nose (43) for a turbomachine, comprising:

   - a primary fuel circuit (62) terminating in a fuel-ejection nozzle (66) emerging on an injection axis (44), and

   - a secondary fuel circuit (64) comprising an annular-shaped terminal fuel-ejection part (68) arranged around the fuel-ejection nozzle (66),

   wherein an upstream part of the primary fuel circuit (62), housed in the injector nose (43), comprises an annular channel (70) extending around the secondary fuel circuit (64), characterised in that the annular channel (70) extending around the secondary fuel circuit (64) is delimited by an external wall (72) of the injector nose,

   and in that the injector nose further comprises air inlet channels (126) extending through the annular channel (70) of the primary fuel circuit (62) and having respective inlets (128) opening in the external wall (72) and respective outlets (130) emerging in an annular air-injection channel (124) arranged radially to the inside with respect to the terminal fuel-ejection part (68), around the fuel-ejection nozzle (66), and cooperating with the terminal fuel-ejection part (68) in order to form an aerodynamic secondary injector.
2. Injector nose according to claim 1, wherein the primary fuel circuit (62) comprises primary connection channels (76) connecting the upstream part of the primary fuel circuit (62) to the fuel-ejection nozzle (66) and comprising respective inlets and respective outlets, the respective inlets being arranged radially towards the outside with respect to the respective outlets.
3. Injector nose according to claim 2, wherein the secondary fuel circuit (64) comprises a tubular channel (100) centred on the injection axis (44) and which divides, at a downstream end, into a plurality of secondary connection channels (104) each formed so as to move away from the injection channel (44) in a direction going from upstream to downstream, and each arranged between two consecutive primary connection channels (76).
4. Injector nose according to claim 3, wherein the annular channel (70) of the upstream part of the primary fuel circuit (62) is arranged around the tubular channel (100) and around the secondary connection channels (104) of the secondary fuel circuit (64).
5. Injector nose according to any one of claims 1 to 4, wherein the secondary fuel circuit (64) comprises a secondary fuel swirler (114) formed by swirler channels (112) having respective upstream ends (111), and having respective downstream ends (115) emerging in the terminal fuel-ejection part (68).
6. Injector nose according to claim 5, wherein the secondary fuel circuit (64) comprises an annular-shaped secondary tranquilisation chamber (108) to which the respective upstream ends (111) of the swirler channels (112) forming the secondary fuel swirler (114) are connected.
7. Injector nose according to claim 5 or 6, taken in combination with claim 2, wherein the annular channel (70) of the upstream part of the primary fuel circuit (62) is extended downstream beyond the primary connection channels (76) so as to form a terminal annular chamber (79) surrounding the secondary fuel swirler (114).
8. Injector nose according to any one of claims 5 to 7, wherein each swirler channel (112) has a cross section of flow that decreases in a direction going from the upstream end (111) towards the downstream end (115) of the swirler channel (112).
9. Injector nose according to any one of claims 1 to 8, wherein the terminal fuel-ejection part (68) is delimited externally by an external lip (116) and is delimited internally by an internal lip (118) that separates the terminal fuel-ejection part (68) from the annular air-injection channel (124).
10. Injection module for a turbomachine, comprising an injection system (42), and an injector nose (43) according to any one of claims 1 to 9, wherein the injection system (42) comprises, from upstream to downstream, a bushing (46) into which the injector nose (43) is mounted, at least one air inlet swirler (48) emerging downstream of the injector nose (43), and a bowl (49).
11. Turbomachine, comprising at least one injector nose (43) according to any one of claims 1 to 9, or at least one injection module according to claim 10.

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