Airflow ejector nozzle having a constant outlet cross-section provided with a stream adjustment device, and turbine engine provided with such a nozzle

Abstract

The invention relates to an airflow ejector nozzle (102, 126) for a turbine engine, in particular of an aircraft, the ejector nozzle extending about a longitudinal axis (XL), the nozzle being partially defined by a radially outer panel (2001) and a radially inner panel (2002) which, between them, at least partially form a flow stream for an airflow, the nozzle comprising a plurality of spacers (202) which extend radially between the outer and inner panels so as to keep them at a radial distance (HC, HS) from one another, the spacers being arranged about the longitudinal axis and each having a first radial end (3001) which is rigidly attached to one of the outer or inner panels, characterised in that each spacer comprises a second radial end (3002) which is opposite the first end and which is attached to the other one of the inner or outer panels so as to make it possible for the radial distance to be adjusted.

Description

Description TITLE: AIR FLOW EJECTION NOZZLE WITH CONSTANT OUTLET SECTION 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 turbomachines, and in particular to a particular design of an ejection nozzle through which a flow stream of a turbomachine air stream circulates, and to a turbomachine comprising such a nozzle. Technological background

[0002] It is known in the prior art, documents US-B2-11 236 701, US-A1 - 2009 / 077978 and WQ-A2-2007 / 005520.

[0003] Climate change is a major concern for many legislative and regulatory bodies around the world. Indeed, various carbon emission restrictions have been, are being, or will be adopted by various states. In particular, an ambitious standard applies to both new aircraft types and those already in operation, requiring the implementation of technological solutions to ensure their compliance with current regulations. Civil aviation has been mobilizing for several years now to contribute to the fight against climate change.

[0004] Technological research efforts have already led to very significant improvements in the environmental performance of aircraft. The Applicant takes into consideration the impact factors in all phases of design and development to obtain less energy-intensive, more environmentally friendly aeronautical components and products whose integration and use in civil aviation have moderate environmental consequences with the aim of improving the energy efficiency of aircraft.

[0005] Consequently, the Applicant is constantly working to reduce its negative climate impact by using methods and operating virtuous development and manufacturing processes and minimizing greenhouse gas emissions to the minimum possible in order to reduce the environmental footprint of its activity.

[0006] This sustained research and development work focuses on new generations of aircraft engines, the weight reduction of aircraft, particularly through the materials used and lighter on-board equipment, the development of the use of electrical technologies to ensure propulsion, and, as an essential complement to technological progress, aeronautical biofuels.

[0007] One of these research works concerns a turbomachine which is equipped with one or more flow veins of an aerodynamic air flow generating at least part of the thrust. Each ejection nozzle where a flow vein circulates is typically annular and is delimited by a radially inner wall and a radially outer wall. These radially inner and outer walls extend between an inlet section and an outlet section along the longitudinal axis of the turbomachine.

[0008] On certain types of turbomachine, particularly those with a bypass ratio of between 5 and 10, the height separating the two walls is relatively significant, for example greater than 200 mm.

[0009] Other types of turbomachines include a flow vein with a cross-section that is very small (for example, less than 30 mm) and which defines its performance. For example, the outlet cross-section of the exhaust nozzles makes it possible to adjust the flow rate of the airflow circulating in the turbomachine as well as the operating parameters of certain components of the turbomachine, such as a compressor, which are placed at the inlet cross-section of the flow vein. In the event of damage, for example, when a foreign body is ingested, it is difficult to intervene due to the small dimensions to repair a damaged part of the vein. Dismantling the entire exhaust nozzle would be necessary. However, dismantling all parts of the exhaust nozzle would impact the adjustment of the outlet cross-section, for example.Furthermore, the very small height of the exhaust nozzle also makes certain tests on the turbomachine impossible, such as the disassembly or reassembly of components of its instrumentation.

[0010] 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

[0011] There is therefore proposed an ejection nozzle for an air flow for a turbomachine, in particular an aircraft, 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 vein for the air flow, the nozzle comprising a plurality of spacers which extend radially between the external and internal panels so as to maintain them at a radial distance from each other, the spacers being arranged around the longitudinal axis and each comprising a first radial end rigidly fixed to one of the external or internal panels, characterized in that each spacer 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 radial distance.

[0012] 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 outlet section defined by the panels.

[0013] The invention therefore makes it possible to avoid possible deformation of the panels during assembly of the turbomachine.

[0014] The invention may further comprise one or more of the following optional features, in any technically possible combination: the first end of each spacer is rigidly fixed to the outer panel and the second end is adjustably fixed to the inner panel; the ejection nozzle comprises a flow adjustment device which comprises at least one set of adjustment members designed to at least radially move each spacer; the set of adjustment members comprises at least one first support connected to the inner panel and designed to receive at least one spacer; the set of adjustment members comprises at least one adjustment screw or at least one adjustment nut, the rotation of which causes a modification of the radial distance between the outer and inner panels;the set of adjustment members comprises an adjustment shim arranged under an internal face of the internal panel and the variation in thickness of which results in a modification of the radial distance between the external and internal panels; the adjusting screw or nut is screwed around an axis radial to the longitudinal axis; the second end of each spacer comprises at least one threaded portion complementary to the adjusting screw or nut to achieve radial displacement of said spacer; the threaded portion is an orifice or a rod; the set of adjusting members further comprises a locking nut disposed 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 members further comprises a plate disposed axially around the locking nut to prevent loosening of said locking nut, the set of adjusting members further comprises a second support on which the internal panel partly rests, the first and second supports being attached and fixed to the internal panel by fixing means;the assembly of members further comprises at least one pre-adjusting shim disposed between the inner panel and the second support, the pre-adjusting shim being designed to align the first support and the inner panel so as to control the radial displacement of each spacer; the inner panel comprises at least a plurality of holes which open radially outwards and in which the second ends (SOOa) of the spacers move radially; the radial distance, preferably of an outlet section of said nozzle, is between 15 mm and 50 mm, and preferably between 25 mm and 30 mm; the nozzle comprises at least one thermal protection foil covering at least the assembly of adjustment members and extending around the longitudinal axis, said foil being removably fixed to the inner panel; the outer panel is an annular panel; the inner panel is an annular panel;the spacers are arranged regularly around the longitudinal axis.;

[0015] The invention also relates to a turbomachine comprising an ejection nozzle as described above.

[0016] The turbomachine may further comprise one or more of the following optional features, in any technically possible combination: the turbomachine comprises an exhaust nozzle in which a primary flow vein circulates in which a primary flow generated by a fan circulates, the fan also generating a secondary flow circulating radially around the primary flow vein; The turbomachine comprises an ejection nozzle in which circulates an external flow vein arranged at least partly radially outside the primary flow vein and in which circulates 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

[0017] The invention will be better understood with the aid of the following description, given solely by way of example and with reference to the appended drawings in which: Figure 1 illustrates an axial section of an example of a turbomachine according to the invention; Figure 2 shows in more detail a portion of an ejection nozzle where a flow stream of an air flow circulates with an outlet section according to the invention; Figure 3 illustrates an axial section of an ejection nozzle comprising a mechanism for adjusting the outlet section according to the invention; Figure 4 is a perspective view of the ejection nozzle of Figure 3; Figure 5 is an inverted view of the nozzle of Figure 4; Figure 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

[0018] In the present invention, and in general, the terms "upstream", "downstream", "axial" and "axially" are defined with respect to the circulation of gases in the turbomachine and with respect to the longitudinal axis X 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.

[0019] Figure 1 shows a multi-flow turbomachine 100 intended to be mounted on an aircraft such as an airplane. The turbomachine 1 shown comprises a fan 104.

[0020] 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 comprising a flow vein where the invention could be integrated. Such a turbomachine is a turboprop and is known by the English expression "open rotor" or "unducted fan" or "open fan". In this category of turbomachine, there are those which have two unducted and counter-rotating propellers (known by the English acronym UDF for "Unducted Dual Fan") or those having a single unducted propeller and a rectifier which is also unducted and which comprises several stator blades (known by the English acronym USF for "Unducted Single Fan"). Of course, the invention also applies to other types of turbomachine such as turbojets, and in particular double flow and double spool.

[0021] Still with reference to FIG. 1, the turbomachine 100 further comprises, from upstream to downstream, a low-pressure compressor or (“booster” in English) 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 of the low-pressure turbine 124 are mechanically connected by a low-pressure shaft 120 so as to form a low-pressure body. The rotors of the high-pressure compressor 132 and of the high-pressure turbine 128 are mechanically connected by a high-pressure shaft 122 so as to form a high-pressure body. The low-pressure shaft 120 extends inside the high-pressure shaft 122 and are coaxial with the longitudinal axis XL.

[0022] The blower 104 is mounted upstream of the low pressure compressor 120 (and preferably its upstream part). The blower 104 comprises a plurality of moving blades 106 arranged around the longitudinal axis XL and extending radially from an internal casing 108 forming the hub of the fan 104.

[0023] A rectifier 110 is arranged downstream of the fan 104. The rectifier 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, we understand by the term “stator vane” or “fixed vane”, a vane which is not driven in rotation about the longitudinal axis XL of the turbomachine. The stator vanes 112 are distributed about the longitudinal axis XL and are arranged downstream of the moving vanes 106 of the fan 104 so as to straighten the air flow generated by them.

[0024] The air flow F which passes through the blower 104 is split into a primary flow Fi and a secondary flow F2 by a separation nozzle 114 a. The primary air flow Fi circulates in a primary flow vein 116 a while the secondary flow F2 circulates radially outside the primary vein 1 16 a . In particular, the secondary flow F2 circulates radially outside the casings and sweeps the unducted rectifier 110. In the case of a dual-flow turbojet comprising ducted moving blades 106, the secondary flow F2 circulates in a secondary flow vein.

[0025] In Figure 1, the primary flow Fi is divided into a radially internal flow Fn and a radially external flow FI2. The division is achieved by means of a division nozzle 114b which is annular. The latter is arranged advantageously, but not limitingly, downstream of the separation nozzle 114 a . The radially internal flow Fu circulates inside the primary flow vein 1 16 aand in particular inside the dividing beak 114b. The primary flow vein 116 a extends downstream, opening onto a primary nozzle 126 through which the gases from the combustion chamber 130 are ejected. The radially external flow FI2 circulates radially outside the dividing nozzle 114 b in an external flow vein 116b. In other words, the external flow vein 116b is arranged at least partly radially outside the primary flow vein 116 a The radially external flow opens outside the turbomachine 100 through an ejection nozzle 102.

[0026] In this embodiment, the radially external flow circulating in the external flow vein 116b makes it possible to carry out heat exchanges and generate part of the thrust of the turbomachine. Equipment such as Heat exchangers can be installed for this purpose in the external flow vein.

[0027] 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 the longitudinal axis X L and on the other hand, between an input section 204 a and an outlet section 206 along the longitudinal axis XL. The external flow stream 116b is formed at least in part by a radially external structure or panel 200i called OFS (for Outer Fixed Structure in English) and a radially internal structure or panel 2002 called IFS (for Inner Fixed structure). The internal panel 2002 and the external panel 200i delimit at least in part an ejection nozzle. These internal and external structures or panels 200i, 2002 are concentric and each have an axis of revolution centered on the longitudinal axis X L .

[0028] The primary flow vein 116 a and / or the secondary flow vein may have the same configuration set out 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 veins circulates in an ejection nozzle.

[0029] Advantageously, the outer panel 200i and the inner panel 2OO2 are made of a composite material. For example, the composite material comprises a sandwich structure which may comprise two skins reinforced with carbon fibers and sandwiching a honeycomb core.

[0030] Advantageously, the external panel 200i is fixed to a compressor casing, for example of the high-pressure compressor 132. The fixing is carried out advantageously, but not limited to, by means of at least one tooth carried by the external structure 200i and acting with a groove provided in the compressor casing.

[0031] Still referring to Figure 2, the ejection nozzle 102 where the external flow vein 116b circulates comprises a plurality of spacers 202 which extend 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 X L and each comprise a first radial end 300i rigidly fixed to the radially panel external 200i via fixing means 220c (see Figure 3). Preferably, the spacers are arranged regularly around the longitudinal axis XL.

[0032] Each spacer further comprises a second radial end 3002, opposite the first end 300i, which is fixed to the radially inner panel so as to allow adjustment of said radial distance. The radial distance to be adjusted may be a radial height H c (see figure 3) of a throat section located upstream of the outlet section or a radial height H s from exit section 204 b of the nozzle 102. The throat is axially located at a point on the nozzle where the radial distance is the smallest. In the example of Figure 2, the radial distance is the radial height H s from exit section 204 b .

[0033] In another variant (not shown), the spacers each comprise a first radial end rigidly fixed to the radially inner panel via fixing means. In this configuration, the second radial end of the spacer, opposite its first end, is fixed to the radially outer panel so as to allow adjustment of said radial distance.

[0034] The adjustment is carried out so that the radial height H c , H s , in operating mode, is fixed and constant.

[0035] In this application, we understand by the expression "in operating mode" a configuration of the turbomachine equipped with the exhaust nozzle which will be used for flight.

[0036] Still referring to Figure 2, the radial height H s from exit section 204 bis measured between the downstream end 208 and the radially external surface FE2oo of the internal panel 2OO2. The spacers 202 ensure, on the one hand, the connection between the radially external and internal panels 200i, 2OO2 and, on the other hand, make it possible to prevent the radially external and internal panels from moving apart and / or deforming radially relative to each other.

[0037] Advantageously, but not limited to, the radial height H s is the minimum height of the output section 204 b in the case of a convergent-divergent nozzle.

[0038] According to an example of realization, the radial height H s from exit section 204 b is between 15 mm and 50 mm, and preferably between 25 mm and 30 mm.

[0039] Advantageously, but not limitingly, 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 H s from exit section 204 b . Preferably, the axial distance Di is equal to five times the radial height H s . In this way, the spacers 202 are located in a flow zone where the Mach number is between 0.4 and 0.5, which makes it possible to limit aerodynamic losses.

[0040] For example, and in a non-limiting manner, the spacers 202 may each have an aerodynamic shape (like a wing profile or a NACA type profile (the initials of which stand for National Advisory Committee for Aeronautics)) shaped to reattach the aerodynamic flow lines.

[0041] 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 comprise a minimum of two spacers 202 depending on the dimensions of the turbomachine 100.

[0042] Referring to Figure 3, the nozzle 102 further comprises a flow path adjustment device which comprises a set of adjustment members designed to at least radially move each spacer 202 relative to the panel on which the flow path adjustment device is positioned. In the example of Figure 3, the flow path adjustment device is positioned on the inner panel 200i. The movement of each spacer 202 makes it possible to move the outer panel 200i, to which the first end of the spacer 202 is rigidly fixed, closer to or further away from the inner panel 200i.

[0043] The assembly of members comprises at least one adjustment nut 212, the rotation of which causes a modification of the radial distance H c , H sbetween the external and internal panels 200i, 2002. In this configuration, each spacer comprises 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.

[0044] Alternatively, the assembly may comprise an adjustment screw, the rotation of which causes a modification of the radial distance Ho, Hs between the external and internal panels. In this configuration, each spacer 202 comprises at its second end at least one orifice opening onto a threaded cavity (not shown) complementary to the screw to achieve the radial displacement of the spacer 202.

[0045] The screw or nut 212 is screwed around an axis XR radial to the longitudinal axis X L .

[0046] Still referring to Figure 3, the set of adjustment members may further comprise a locking nut 214 disposed axially around the adjustment screw or nut 212 and designed to fix the position of the spacer 202. As mentioned above, actuation of the tightening screw or nut makes it possible to define a desired value of the radial distance H c , H s . Thus, once this value is set, the locking nut allows this value to be maintained constant by immobilizing the spacer 202.

[0047] The assembly of members may further comprise a plate 216 disposed axially around the locking nut to prevent loosening of the locking nut 214.

[0048] The turbomachine may be subjected to high stresses and vibrations during operation. Thus, advantageously, the locking nut 214 and the plate 216 make it possible to secure the positioning of the spacer 202 and to maintain the constant radial distance H. c , Hs regardless of the operating range of the turbomachine. The locking nut and the plate also ensure that play between the adjusting nut 212 and the threaded portion 304 of the spacer is taken up.

[0049] 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 spacers move radially.

[0050] The set of adjustment members comprises 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.

[0051] The first support 206 may be formed from a single block or comprise, for example, as in FIG. 3 and in a non-limiting manner, a first block 206a, for example and in a non-limiting manner a counter-plate (with an aerodynamic function) and a second block 206b, for example and in a non-limiting manner a plate, connected to each other by fixing 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.

[0052] In this configuration, the first block 206a may comprise a recess 206d configured to receive the second end of the spacer 202. The recess makes it possible to store a portion of the spacer 202 which is profiled. In this way, when there is a need, for example, to enlarge the radial distance between the outer and inner panels (and consequently the radial dimension of the vein), the profiled portion of the spacer which is housed in the recess is used. Thus, the recess makes it possible to ensure the presence of a profiled portion of the spacer in the vein, even when the radial distance between the outer and inner panels is maximum.

[0053] The support 206 comprises 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).

[0054] The set of adjustment members further comprises a second support 210 on which the internal panel 2002 partly rests. The first and second supports 206, 210 are attached and fixed to the internal panel 2002 by fixing means 220d, 220e, the second support 210 resting on the arm of the first support 206.

[0055] The assembly of members further comprises at least one pre-adjustment shim 218 disposed between the internal panel 2002 and the second support 210. The pre-adjustment shim is designed to achieve an alignment of the first support and the internal panel 2002 so as to control the aerodynamic alignment (or step) of the first block 206a with the internal panel 2002.

[0056] A plurality of holes 222 are provided in the inner panel 2002 of the ejection nozzle which open radially outwards and in which the second ends of the spacers move radially.

[0057] 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 internal panel via the at least one pre-adjustment shim 218. The first support 206 is then fixed to the second support 210. The pre-adjustment shim 210 comprises a thickness predetermined position to achieve alignment of the first support 206 and the inner panel 200?. The spacer is then secured to the first support 206 by means of the adjusting nut. The adjusting nut is adjusted to set a value of the desired radial distance. After setting a value of the radial distance, the position of the adjusting nut is fixed by means of the locking nut. The immobilizing plate is then used to prevent loosening of the locking nut.

[0058] Advantageously, the person skilled in the art will understand that the solution described above makes it possible to manage the position of the different supports relative to the internal panel and to be able to adjust more easily and precisely the positioning of the external panel 200i after mounting the spacer on the internal panel 2002.

[0059] The nozzle further comprises at least one thermal protection foil 226 covering at least the set of adjustment members and extending around the longitudinal axis XL. The thermal protection foil 226 is removably attached to the internal panel 2002.

[0060] Figures 4 and 5 show perspective views of a portion of the nozzle illustrated in Figure 3. In Figure 4, the nozzle has the same orientation as in Figure 3, i.e., the outer panel 2002 is above the inner panel 2002. Figure 5 shows a reverse view of Figure 4, with the outer panel below the inner panel.

[0061] In these examples, the holes 222 in the inner panel 2002 have a cylindrical shape as illustrated in Figures 4.

[0062] Referring to Figure 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.

[0063] 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, those 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 manner, a square.

[0064] Those 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.

[0065] Figure 6 represents a variant of the ejection nozzle according to the invention.

[0066] In this variant, the first end of the spacer 202 is rigidly fixed to the external panel 200i as in the example of FIG. 3. The support 206, capable of receiving the second end 3002 of the spacer 202, comprises a single block.

[0067] The assembly of members comprises at least one adjustment shim 224 arranged under an internal face FI200 of the internal panel 2002. The shim 224 is arranged between an arm of the first support 206 and an internal face of the internal panel 2002.

[0068] Advantageously, those skilled in the art will understand that by varying the thickness of the shim 224, the radial distance H is also modified. c , H s between the external and internal panels 200i, 20Û2 and in particular, the radial height H s from exit section 204 b of nozzle 102.

[0069] For example and in a non-limiting manner, by positioning a very thick shim 224, the support 206 moves radially towards the longitudinal axis (radially internal displacement). This has the effect of reducing the radial distance H c , H s between the external and internal panels.

[0070] Conversely, by positioning a thin shim 224 between the internal face of the internal panel 2002 and the arm of the first support 206, the support 206 moves towards the external panel, moving away from the longitudinal axis X. L This has the effect of increasing the radial distance between the panels and, in particular, the radial height H c , H s .

[0071] Thus, advantageously, the invention makes it possible to avoid possible deformation of the panels during their assembly. In addition, controlling the radial distance by means of a screw, a nut or a plate makes it possible to have greater precision of adjustment during the assembly of the turbomachine or after assembly.

Claims

Claims [1] Nozzle (102, 126) for ejecting an air flow for a turbomachine, in particular an aircraft, the ejection nozzle extending around a longitudinal axis (X L ), the nozzle being delimited at least in part by a radially external panel (200i) and a radially internal panel (200a) forming between them at least in part a flow vein for the air flow (116 a , 116b), the nozzle comprising a plurality of spacers (202) which extend radially between the outer and inner panels so as to maintain them at a radial distance (H c , H s) from each other, the spacers (202) being arranged around the longitudinal axis (X ) and each comprising a first radial end (300i) rigidly fixed to one of the external or internal panels (200i, 2002), characterized in that each spacer (202) comprises a second radial end (300i), opposite the first end (300i), which is fixed to the other of the internal or external panels (200i, 2002) so as to allow adjustment of said radial distance (H c , H s ). [2] A jet nozzle (102, 126) for a flow according to claim 1, wherein the first end (300i) of each spacer (202) is rigidly fixed to the outer panel (200i) and the second end (3002) is adjustably fixed to the inner panel (2002). [3] Ejection nozzle (102, 126) of a flow according to claim 1 or 2, comprising a vein adjustment device which comprises at least one set of adjustment members designed to at least radially move each spacer (202). [4] Ejection nozzle (102, 126) of an air flow according to claim 3, in which the set of adjustment members comprises at least: a first support (206) connected to the internal panel (2002) and designed to receive at least one spacer (202); an adjustment screw or at least one nut (212) whose rotation causes a modification of the radial distance between the external (200i) and internal (2002) panels; and an adjustment shim (224) arranged under an internal face (FI200) of the internal panel (2002) and whose variation in thickness causes a modification of the radial distance (Hc, Hs) between the external (200i) and internal (2002) panels. [5] Ejection nozzle (102, 126) of an air flow according to the preceding claim, in which the second end (300?) of each spacer (202) comprises at least one threaded portion (304) complementary to the adjustment screw or nut (212) to achieve the radial displacement of said spacer (202). [6] Ejection nozzle (102, 126) of an air flow according to one of claims 4 or 5, in which the set of adjustment 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 (H c , H s); a plate (216) arranged axially around the locking nut to prevent loosening of said locking nut (214), and a second support (210) on which the internal panel (2002) partly rests, the first (206) and second (210) supports being attached and fixed to the internal panel (2002) by fixing means (220d, 220 e ). [7] Ejection nozzle (102, 126) of an air flow according to one of claims 4 to 6, in which the set of members further comprises at least one pre-adjustment shim (218) arranged between the internal panel (2002) and the second support. (210), the pre-adjusting shim (218) being adapted to provide an alignment of the first support (206) and the internal panel (2002) so as to control the radial displacement of each spacer (202). [8] Ejection nozzle (102, 126) of an air flow according to one of claims 1 to 7, in which the internal panel (2002) comprises at least a plurality of holes (222) which open radially outwards and in which the second ends (300z) of the spacers (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, in which it comprises - an ejection nozzle where a primary flow vein circulates (116 a ) in which a primary flow generated by a blower (104) circulates, the blower (104) also generating a secondary flow circulating radially around the primary flow vein (1 16 a ) ; And - an ejection nozzle through which circulates an external flow vein (116b) arranged at least partly radially outside the primary flow vein (116 a ) and in which circulates a radially external flow (F12) resulting 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 one of claims 1 to 8.

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