CONSTANT OUTLET SECTION AIR FLOW EJECTION NOZZLE EQUIPPED WITH A VEIN ADJUSTMENT DEVICE AND TURBOMACHINE EQUIPPED WITH SUCH A NOZZLE.

Abstract

The invention relates to an airflow ejection nozzle (102, 126) for a turbomachine, particularly an aircraft turbomachine, the ejection nozzle extending around a longitudinal axis (XL), the nozzle being partially delimited by a radially external panel (2001) and a radially internal panel (2002) forming between them at least partially a flow duct for an airflow, the nozzle comprising a plurality of struts (202) extending radially between the external and internal panels so as to maintain them at a radial distance (HC, HS) from each other, the struts being arranged around the longitudinal axis and each having a first radial end (3001) rigidly fixed to one of the external or internal panels, characterized in that each strut comprises a second radial end (3002), opposite the first end, which is fixed to the other of the internal or external panels so as to allow adjustment of said radial distance.Figure for the abbreviation: Figure 3.

Description

Title of the invention: CONSTANT OUTLET SECTION AIR FLOW EJECTION NOZZLE EQUIPPED WITH A VEIN ADJUSTMENT DEVICE AND TURBOMACHINE EQUIPPED WITH SUCH A NOZZLE. Technical field of the invention

[0001] The present invention relates to the field of turbomachinery, and in particular to a specific design of an ejection nozzle through which a flow path of turbomachine air flows, and to a turbomachine comprising such a nozzle. Technological background

[0002] Climate change is a major concern for many legislative and regulatory bodies worldwide. Indeed, various restrictions on carbon emissions have been, are being, or will be adopted by various states. In particular, an ambitious standard applies to both new types of aircraft and those already in service, requiring the implementation of technological solutions to bring them into compliance with current regulations. Civil aviation has been actively working for several years now to contribute to the fight against climate change.

[0003] Technological research efforts have already led to very significant improvements in the environmental performance of aircraft. The Applicant takes into account the factors impacting all phases of design and development in order to obtain aeronautical components and products that are less energy-intensive, more environmentally friendly, and whose integration and use in civil aviation have moderate environmental consequences, with the aim of improving the energy efficiency of aircraft.

[0004] Consequently, the Applicant is constantly working to reduce its negative climate impact by using methods and operating virtuous development and manufacturing processes that minimize greenhouse gas emissions to the minimum possible in order to reduce the environmental footprint of its activity.

[0005] This sustained research and development work focuses on new generations of aircraft engines, the weight reduction of aircraft, in particular through the materials used and lighter on-board equipment, the development of the use of electrical technologies to provide propulsion, and, as essential complements to technological progress, aviation biofuels.

[0006] One of these research projects relates to a turbomachine equipped with one or more flow ducts of an aerodynamic airflow generating at least part of the thrust. Each ejection nozzle through which a flow duct flows is typically annular and delimited by a radially internal wall and a radially external wall. These radially internal and external walls extend between an inlet section and an outlet section along the longitudinal axis of the turbomachine.

[0007] On certain types of turbomachinery, particularly those with a dilution ratio between 5 and 10, the height separating the two walls is relatively large, for example greater than 200 mm.

[0008] Other types of turbomachinery include a flow duct with a very small cross-section (for example, less than 30 mm) which defines its performance. For example, the outlet cross-section of the ejection nozzles allows the flow rate of the air circulating in the turbomachine to be regulated, as well as the operating parameters of certain turbomachine components, such as a compressor, which are located at the inlet cross-section of the flow duct. In the event of a failure, for example, the ingestion of a foreign object, it is difficult to intervene due to the small dimensions of the duct to repair a damaged section. Dismantling the entire ejection nozzle would be necessary. However, dismantling all parts of the ejection nozzle would affect the adjustment of the outlet cross-section, for example.Furthermore, the very small height of the ejection nozzle also makes certain tests on the turbomachine impossible, such as the dismantling or reassembly of its instrumentation components.

[0009] It may therefore be desirable to provide a nozzle which makes it possible to overcome at least some of the aforementioned problems and constraints. Summary of the invention

[0010] An airflow ejection nozzle for a turbomachine, particularly an aircraft turbomachine, is therefore proposed, the ejection nozzle extending around a longitudinal axis, the nozzle being delimited at least in part by a radially external panel and a radially internal panel forming between them at least in part a flow duct for the airflow, the nozzle comprising a plurality of struts extending radially between the external and internal panels so as to maintain them at a radial distance from each other, the struts being arranged around the longitudinal axis and each having a first radial end rigidly fixed to one of the external or internal panels, characterized in that each strut comprises a second radial end, opposite the first end, which is fixed to the other of the internal or external panels so as to allow adjustment of said strut radial distance.

[0011] Thus, thanks to the invention, it is possible, after assembly of the internal and external panels and the spacer, to adjust more easily and precisely the radial distance between the panels and, in particular, to control the output section defined by the panels.

[0012] The invention therefore makes it possible to avoid possible deformations of the panels during the assembly of the turbomachine.

[0013] The invention may further include one or more of the following optional features, in any technically feasible combination: - the first end of each spacer is rigidly fixed to the outer panel and the second end is adjustablely fixed to the inner panel; - the ejection nozzle includes a vein adjustment device which comprises at least one set of adjustment elements designed to at least radially displace each spacer; - the set of adjustment mechanisms includes at least one first support connected to the internal panel and designed to receive at least one spacer; - the set of adjustment devices includes at least one adjusting screw or nut whose rotation results in a change in the radial distance between the external and internal panels; - the set of adjustment devices includes an adjustment shim located under an internal face of the internal panel and whose variation in thickness results in a modification of the radial distance between the external and internal panels; - the adjusting screw or nut is screwed around a radial axis to the longitudinal axis; - the second end of each spacer has at least one additional threaded portion of the adjusting screw or nut to achieve the radial movement of said spacer; - the threaded portion is an opening or a rod; - the set of adjusting elements further includes a locking nut arranged axially around the adjusting screw or nut and designed to fix the position of the spacer at a desired value of the radial distance; - The set of adjusting components further includes a plate arranged axially around the locking nut to prevent the locking nut from loosening, - the set of adjustment mechanisms further includes a second support on which the internal panel partly rests, the first and second supports being attached and fixed to the internal panel by means of fixing; - the assembly of components further includes at least one pre-adjustment shim positioned between the inner panel and the second support, the pre-adjustment shim being designed to achieve alignment of the first support and the inner panel so as to control the radial displacement of each spacer; - the internal panel includes at least a plurality of holes which open radially outwards and in which the second ends (3002) of the spacers move radially; - the radial distance, preferably from an outlet section of said nozzle, is between 15 mm and 50 mm, and preferably between 25 mm and 30 mm; - the nozzle includes at least one thermal protection flashing covering at least the set of adjustment elements and extending around the longitudinal axis, said flashing being removably fixed to the internal panel; - the outer panel is an annular panel; - the inner panel is an annular panel; - the spacers are arranged regularly around the longitudinal axis.

[0014] The invention also relates to a turbomachine comprising an ejection nozzle as described above.

[0015] The turbomachine may further include one or more of the following optional features, in any technically feasible combination: - the turbomachine includes an ejection nozzle comprising a primary flow duct in which a primary flow generated by a blower circulates, the blower also generating a secondary flow circulating radially around the primary flow duct; - The turbomachine includes an ejection nozzle comprising an external flow channel arranged at least partly radially outside the primary flow channel and in which flows a radially external flow resulting from the division of the primary flow having passed through at least one compressor, the ejection nozzle being the ejection nozzle as described above. Brief description of the figures

[0016] The invention will be better understood with the aid of the following description, given solely by way of example and made with reference to the accompanying drawings in which: - [Fig.1] illustrates an axial section of an example of a turbomachine according to the invention; - [Fig.2] represents in more detail a portion of an ejection nozzle through which flows a stream of air with an outlet section according to the invention; - [Fig.3] illustrates an axial section of an ejection nozzle comprising a mechanism for adjusting the outlet section according to the invention; - [Fig.4] is a perspective view of the ejection nozzle of [Fig.3]; - [Fig.5] is an inverted view of the nozzle of [Fig.4]; - [Fig. 6] is an axial section of a variant of the ejection nozzle comprising a mechanism for adjusting the outlet section according to the invention. Detailed description of the invention

[0017] In the present invention, and generally, the terms "upstream", "downstream", "axial" and "axially" are defined with respect to the gas flow in the turbomachine and with respect to the longitudinal axis XL of the turbomachine 100. Similarly, the terms "radial", "radially", "internal" and "external" are defined with respect to a radial axis perpendicular to the longitudinal axis XL and with respect to the distance from the longitudinal axis XL.

[0018] Figure 1 represents a multi-flow turbomachine 100 intended for mounting on an aircraft such as an airplane. The turbomachine 1 shown comprises a fan 104.

[0019] Those skilled in the art will understand that this example is not limiting and that the invention can also be applied, for example, to a turbomachine (not shown) comprising an unducted propeller having a flow channel into which the invention could be integrated. Such a turbomachine is a turboprop and is known by the English term "open rotor" or "unducted fan." Within this category of turbomachine, there are those with two unducted, counter-rotating propellers (known by the English acronym UDF for "Unducted Dual Fan") or those with a single unducted propeller and a stator that is also unducted and comprises several stator blades (known by the English acronym USF for "Unducted Single Fan"). Of course, the invention also applies to other types of turbomachines such as turbojets, and in particular turbofans and twin-spool turbojets.

[0020] With further reference to [Fig. 1], the turbomachine 100 further comprises, from upstream to downstream, a low-pressure compressor or (in English, "booster") 118, a high-pressure compressor 132, a combustion chamber 130, a high-pressure turbine 128, and a low-pressure turbine 124. The rotors of the low-pressure compressor 118 and the low-pressure turbine 124 are mechanically connected by a low-pressure shaft 120 to form a low-pressure housing. The rotors of the high-pressure compressor 132 and the high-pressure turbine 128 are mechanically connected by a high-pressure shaft 122 to form a high-pressure housing. The low-pressure shaft 120 extends inside the high-pressure shaft 122. and are coaxial to the longitudinal axis XL.

[0021] The blower 104 is mounted upstream of the low-pressure compressor 120 (and preferably its upstream portion). The blower 104 comprises a plurality of movable blades 106 arranged around the longitudinal axis XL and extending radially from an internal housing 108 forming the hub of the blower 104.

[0022] A straightener 110 is arranged downstream of the blower 104. The straightener 110 comprises a plurality of stator vanes 112 (or fixed vanes) known by the English acronym "OGV" for Outlet Guide Vane. In the present invention, the term "stator vane" or "fixed vane" refers to a vane that is not driven in rotation about the longitudinal axis XL of the turbomachine. The stator vanes 112 are distributed around the longitudinal axis XL and are arranged downstream of the moving vanes 106 of the blower 104 so as to straighten the airflow generated by the latter.

[0023] The airflow F passing through the fan 104 is split into a primary flow Fi and a secondary flow F2 by a separation nozzle 114a. The primary airflow Fi flows in a primary flow channel 116a, while the secondary flow F2 flows radially outside the primary flow channel 116a. In particular, the secondary flow F2 flows radially outside the casings and sweeps the unshod stator 110. In the case of a turbofan engine comprising shod movable blades 106, the secondary flow F2 flows in a secondary flow channel.

[0024] In [Fig. 1], the primary flow Fi is divided into a radially internal flow Fn and a radially external flow Fi2. This division is achieved by means of an annular dividing nozzle 114b. This nozzle is advantageously, but not exclusively, arranged downstream of the separating nozzle 114a. The radially internal flow Fn circulates within the primary flow channel 116a and, in particular, within the dividing nozzle 114b. The primary flow channel 116a extends downstream, opening into a primary nozzle 126 through which the gases from the combustion chamber 130 are ejected. The radially external flow Fn circulates radially outside the dividing nozzle 114b in an external flow channel 116b. In other words, the external flow vein 116b is arranged at least partly radially outside the primary flow vein 116a.The radially external flow exits outside the turbomachine 100 through an ejection nozzle 102.

[0025] In this embodiment, the radially external flow circulating in the external flow channel 116b enables heat exchange and generates part of the turbomachine's thrust. Equipment such as heat exchangers can be installed for this purpose in the external flow channel.

[0026] Figure 2 shows an example of an external flow vein 116b and in particular its rear part. The external flow vein 116b extends on the one hand, around of the longitudinal axis XL and, on the other hand, between an inlet section 204a and an outlet section 206 along the longitudinal axis XL. The external flow stream 116best is formed at least in part by a radially external structure or panel 200i called OFS (Outer Fixed Structure) and a radially internal structure or panel 2002 called IFS (Inner Fixed Structure). The inner panel 2002 and the outer panel 200i define at least in part an ejection nozzle. These inner and outer structures or panels 200i and 2002 are concentric and each has an axis of revolution centered on the longitudinal axis XL.

[0027] The primary flow channel 116a and / or the secondary flow channel may have the same configuration as described above (internal structure or panel and external structure or panel) as well as those described in the remainder of this description. At least one of the primary and secondary flow channels flows through an ejection nozzle.

[0028] Advantageously, the outer panel 200i and the inner panel 2002 are made of a composite material. For example, the composite material comprises a sandwich structure which may include two carbon fiber reinforced skins sandwiching a honeycomb core.

[0029] Advantageously, the external panel 200i is fixed to a compressor housing, for example of the high-pressure compressor 132. The fixing is advantageously, but not exclusively, achieved by means of at least one tooth carried by the external structure 200i and acting with a groove provided in the compressor housing.

[0030] With further reference to [Fig. 2], the ejection nozzle 102 through which the external flow stream 116b flows comprises a plurality of spacers 202 extending radially between the radially external panel 200i and the radially internal panel 2002 so as to maintain them at a radial distance from each other. The spacers 202 are arranged around the longitudinal axis XL and each has a first radial end 300i rigidly fixed to the radially external panel 200i by means of fastening means 220c (see [Fig. 3]). Preferably, the spacers are arranged regularly around the longitudinal axis XL.

[0031] Each spacer further comprises a second radial end 3002, opposite the first end 300i, which is fixed to the inner radial panel so as to allow adjustment of said radial distance. The radial distance to be adjusted can be a radial height Hc (see [Fig. 3]) of a throat section located upstream of the outlet section or a radial height Hs of the outlet section 204b of the nozzle 102. The throat is axially located at a point in the nozzle where the radial distance is smallest. In the example of [Fig. 2], the radial distance is the radial height Hs of the outlet section 204b.

[0032] In another variant (not shown), the spacers each have a The first radial end is rigidly fixed to the inner radial panel via fastening means. In this configuration, the second radial end of the spacer, opposite its first end, is fixed to the outer radial panel to allow adjustment of said radial distance.

[0033] The adjustment is made so that the radial height Hc, Hs, in operating operation, is fixed and constant.

[0034] In this application, we mean by the expression "in operating condition" a configuration of the turbomachine equipped with the ejection nozzle that will be used for flight.

[0035] Still with reference to [Fig.2], the radial height Hs of the outlet section 204b is measured between the downstream end 208 and the radially external surface FE2Oo of the internal panel 2002. The spacers 202 ensure, on the one hand, the connection between the radially external and internal panels 200i, 2002 and, on the other hand, prevent the radially external and internal panels from moving apart and / or deforming radially with respect to each other.

[0036] Advantageously, but not limitingly, the radial height Hs is the minimum height of the outlet section 204b in the case of a convergent-di-vergent nozzle.

[0037] According to an example of an embodiment, the radial height Hs of the outlet section 204b is between 15 mm and 50 mm, and preferably between 25 mm and 30 mm.

[0038] Advantageously, but not exclusively, the spacers 202 are arranged at a predetermined axial distance Di from the downstream end 208 of the radially external panel 200i. The axial distance Di can be between 0 and 300 mm. Preferably, the axial distance Di is 150 mm. Alternatively, the axial distance Di is equal to between three and seven times the radial height Hs of the outlet section 204b. Preferably, the axial distance Di is equal to five times the radial height Hs. In this way, the spacers 202 are located in a flow zone where the Mach number is between 0.4 and 0.5, which helps to limit aerodynamic losses.

[0039] For example, and not limited to, the spacers 202 can each have an aerodynamic shape (in the manner of an airfoil or a NACA type airfoil (whose initials stand for National Advisory Committee for Aeronautics)) shaped to align the aerodynamic flow lines.

[0040] The number of spacers 202 envisaged is, for example, five. Of course, the number of spacers could be greater and the ejection nozzle 102 could include a minimum of two spacers 202 depending on the dimensions of the turbomachine 100.

[0041] With reference to [Fig. 3], the nozzle 102 further comprises an adjustment device for The vein comprises a set of adjustment elements designed to at least radially displace each spacer 202 relative to the panel on which the vein adjustment device is positioned. In the example of [Fig. 3], the vein adjustment device is positioned on the inner panel 200i. The displacement of each spacer 202 allows the outer panel 200i, to which the first end of the spacer 202 is rigidly fixed, to be moved closer to or further from the inner panel 200i.

[0042] The assembly of components includes at least one adjusting nut 212, the rotation of which causes a change in the radial distance Hc, Hs between the outer and inner panels 200i, 2002. In this configuration, each spacer has at its second end at least one threaded portion 304 complementary to the nut 212 to achieve the radial displacement of the spacer 202. The threaded portion is preferably a rod 304.

[0043] Alternatively, the assembly may include an adjusting screw whose rotation causes a change in the radial distance Hc, Hs between the outer and inner panels. In this configuration, each spacer 202 has at its second end at least one opening leading to a threaded cavity (not shown) complementary to the screw for achieving the radial displacement of the spacer 202.

[0044] The screw or nut 212 is screwed around a radial axis XR to the longitudinal axis XL.

[0045] Still referring to [Fig. 3], the set of adjusting elements may include In addition, a locking nut 214 is arranged axially around the adjusting screw or nut 212 and is designed to fix the position of the spacer 202. As mentioned above, actuating the tightening screw or nut allows a desired value for the radial distance Hc, Hs to be set. Thus, once this value is set, the locking nut maintains this value constant by immobilizing the spacer 202.

[0046] The assembly of components may further include a plate 216 arranged axially around the locking nut to prevent loosening of the locking nut 214.

[0047] The turbomachine can be subjected to high stresses and vibrations during operation. Advantageously, the locking nut 214 and the plate 216 secure the positioning of the spacer 202 and maintain a constant radial distance Hc, Hs regardless of the turbomachine's operating range. The locking nut and the plate also compensate for any play in the adjusting nut 212 with the threaded portion 304 of the spacer.

[0048] The internal panel 2002 of the ejection nozzle comprises at least a plurality of holes 222 which open radially outwards and in which the second ends of the struts move radially.

[0049] The set of adjusting elements includes at least one first support 206 connected to the internal panel 2002 and designed to receive at least one spacer 202. The first support 206 can be fixed, by means of a screw 220e, on a radially internal face of the internal panel 2002.

[0050] The first support 206 may be formed as a single block or comprise, for example, as in [Fig. 3] and without limitation, a first block 206a, for example and without limitation a counter plate (with an aerodynamic function) and a second block 206b, for example and without limitation a plate, connected to each other by fastening means 220b (for example nuts). The first block 206a rests on the second block 206b, which is connected to the internal panel 2002 by means of the screw 220e.

[0051] In this configuration, the first block 206a may include a recess 206d configured to receive the second end of the spacer 202. The recess allows for the storage of a profiled portion of the spacer 202. In this way, when there is a need, for example, to increase the radial distance between the outer and inner panels (and consequently the radial dimension of the channel), the profiled portion of the spacer housed in the recess is used. Thus, the recess ensures the presence of a profiled portion of the spacer in the channel, even when the radial distance between the outer and inner panels is at its maximum.

[0052] The support 206 includes a hole 206e made in the recess 206d and passing through the first and second blocks 206a to allow the passage of the threaded rod 304 (as in [Fig.3]) or the clamping screw (not shown).

[0053] The set of adjustment elements further includes a second support 210 on which the internal panel 2002 rests in part. The first and second supports 206, 210 are attached and fixed to the internal panel 2002 by fastening means 220d, 220e, the second support 210 resting on the arm of the first support 206.

[0054] The assembly of components further includes at least one pre-adjustment shim 218 disposed between the inner panel 2002 and the second support 210. The pre-adjustment shim is designed to achieve an alignment of the first support and the inner panel 2002 so as to control the aerodynamic alignment (or step) of the first block 206a with the inner panel 2002.

[0055] A plurality of holes 222 are provided in the internal panel 2002 of the ejection nozzle which open radially outwards and in which the second ends of the struts move radially.

[0056] During the assembly of the turbomachine 100 and in particular the mounting of the spacers 202, the second support 210 is first installed on the inner panel via at least one pre-adjustment shim 218. The first support 206 is then fixed to the second support 210. The pre-adjustment shim 210 includes a predetermined thickness allowing alignment of the first support 206 and the inner panel 2002. The spacer is then attached to the first support 206 using the adjusting nut. The adjusting nut is adjusted to set the desired radial distance. After setting the radial distance, the position of the adjusting nut is secured with the locking nut. The retaining plate is then used to prevent the locking nut from loosening.

[0057] Advantageously, a person skilled in the art will understand that the solution described above allows management of the position of the various supports in relation to the internal panel and makes it easier and more precise to adjust the positioning of the external panel 200i after mounting the spacer on the internal panel 2002.

[0058] The nozzle further comprises at least one thermal protection cover 226 covering at least the entire set of adjusting elements and extending around the longitudinal axis XL. The thermal protection cover 226 is removably attached to the inner panel 2002.

[0059] Figures 4 and 5 show perspective views of a portion of the nozzle illustrated in [Fig. 3]. In [Fig. 4], the nozzle has the same orientation as in [Fig. 3], i.e., the outer panel 2002 is above the inner panel 2002. As for [Fig. 5], it shows an inverted view of [Fig. 4], with the outer panel below the inner panel.

[0060] In these examples, the holes 222 in the internal panel 2002 have a cylindrical shape as illustrated in figures 4.

[0061] With reference to [Fig.5], the first and second blocks 206a, 206b of the first support 206 also have a cylindrical shape adapted to the holes 222 of the internal panel 2002.

[0062] Although in the example of figures 4 and 5, the holes in the internal panel 2002 and the first support 206 have a cylindrical shape, the person skilled in the art will understand that this shape is not limiting and that the holes can have various shapes such as, for example, and in a non-limiting way, a square.

[0063] A person skilled in the art will therefore understand that the shape of the first support 206 can be adapted according to the shape of the hole.

[0064] Fig. 6 represents a variant of the ejection nozzle according to the invention.

[0065] In this variant, the first end of the spacer 202 is rigidly fixed to the outer panel 200i as in the example of [Fig.3]. The support 206, suitable for receiving the second end 3002 of the spacer 202, comprises a single block.

[0066] The assembly of components includes at least one adjustment shim 224 disposed under an inner face FI2Oo of the inner panel 2002. The shim 224 is disposed between an arm of the first support 206 and an inner face of the inner panel 2002.

[0067] Advantageously, those skilled in the art will understand that by varying the thickness of the shim 224, the radial distance Hc, Hs between the external panels is also modified. and internal 200i, 2002 and in particular, the radial height Hs of the outlet section 204b of the nozzle 102.

[0068] For example, and without limitation, by positioning a thick shim 224, the support 206 moves radially towards the longitudinal axis (radially internal displacement). This has the effect of reducing the radial distance Hc, Hs between the external and internal panels.

[0069] Conversely, by positioning a thin shim 224 between the inner face of the inner panel 2002 and the arm of the first support 206, the support 206 moves towards the outer panel away from the longitudinal axis XL. This has the effect of increasing the radial distance between the panels and, in particular, the radial height Hc, Hs.

[0070] Thus, advantageously, the invention eliminates the risk of potential panel deformation during assembly. Furthermore, controlling the radial distance using a screw, nut, or plate allows for greater adjustment precision during or after turbomachine assembly.

Claims

Demands

1. Airflow ejection nozzle (102, 126) for a turbomachine, in particular for aircraft, the ejection nozzle extending around a longitudinal axis (XL), the nozzle being delimited at least in part by a radially external panel (2000) and a radially internal panel (2002) forming between them at least in part a flow channel of the airflow (116a, 116b), the nozzle comprising a plurality of struts (202) which extend radially between the external and internal panels so as to maintain them at a radial distance (Hc, Hs) from each other, the struts (202) being arranged around the longitudinal axis (XL) and each having a first radial end (3000) rigidly fixed to one of the external or internal panels (200i, 2002), characterized in that each spacer (202) comprises a second radial end (3002), opposite the first end (3000), which is fixed to the other of the internal or external panels (200i,2002) so as to allow adjustment of said radial distance (Hc, Hs).

2. Ejection nozzle (102, 126) of a flow according to claim 1, wherein the first end (3000) of each spacer (202) is rigidly fixed to the outer panel (2000) and the second end (3002) is adjustablely fixed to the inner panel (2002).

3. Ejection nozzle (102, 126) of a flow according to claim 1 or 2, comprising a flow adjustment device which includes at least one set of adjustment members designed to at least radially displace each spacer (202).

4. Ejection nozzle (102, 126) of an airflow according to claim 3, wherein the set of adjustment members comprises at least: - a first support (206) connected to the inner panel (2002) and designed to receive at least one spacer (202); - an adjustment screw or at least one adjustment nut (212) the rotation of which causes a change in the radial distance between the outer (2000) and inner (2002) panels; and - an adjustment shim (224) disposed under an inner face (FI200) of the inner panel (2002) and the variation in thickness of which causes a change in the radial distance (Hc, Hs) between the outer (2000) and inner (2002) panels.

5. Ejection nozzle (102, 126) of an airflow according to the preceding claim, wherein the second end (3002) of each spacer (202) has at least one threaded portion (304) complementary to the adjusting screw or nut (212) to achieve the radial movement of said spacer (202).

6. Ejection nozzle (102, 126) of an airflow according to any one of claims 4 or 5, wherein the set of adjusting members further comprises: - a locking nut (214) disposed axially around the adjusting screw or nut (212) and designed to fix the position of the spacer at a desired value of the radial distance (Hc, Hs); - a plate (216) disposed axially around the locking nut to prevent loosening of said locking nut (214), and - a second support (210) on which the inner panel (2002) rests in part, the first (206) and second (210) supports being attached to and fixed to the inner panel (2002) by fastening means (220d, 220e).

7. Ejection nozzle (102, 126) of an airflow according to any one of claims 4 to 6, wherein the assembly of components further comprises at least one pre-adjustment shim (218) disposed between the inner panel (2002) and the second support (210), the pre-adjustment shim (218) being designed to achieve an alignment of the first support (206) and the inner panel (2002) so as to control the radial displacement of each spacer (202).

8. Ejection nozzle (102, 126) of an airflow according to any one of claims 1 to 7, wherein the inner panel (2002) comprises at least a plurality of holes (222) which open radially outwards and in which the second ends (3002) of the struts (202) move radially.

9. Turbomachine (100), characterized in that it comprises at least one ejection nozzle (102, 126) according to any one of the preceding claims.

10. Turbomachine according to the preceding claim, wherein it comprises an ejection nozzle including: a primary flow channel (116a) in which flows a primary flow generated by a blower (104), the blower (104) also generating a secondary flow circulating radially around the primary flow channel (116a); and an external flow channel (116b) arranged at least partly radially outside the primary flow channel (116a) and in which flows a radially external flow (Fi2) from the division of the primary flow (Fi) having passed through at least one compressor (118, 132), the ejection nozzle being the ejection nozzle according to any one of claims 1 to 8.

Images