THERMAL PROTECTION DEVICE FOR A LOWER SIDE BUILDING OF AN AIRCRAFT FRAME

Abstract

THERMAL PROTECTION DEVICE FOR THE LOWER SIDE LINER OF AN AIRCRAFT BOX The invention relates to a thermal protection device for the lower side spar of an aircraft box. This device comprises a shield consisting of: - a first panel extending parallel to and at a first distance from the lower side spar; - a second panel positioned between said first panel and the lower side spar, extending parallel to and at a second distance from the lower side spar. These panels define a channel extending parallel to and at a distance from the lower side spar. A forward end of said channel forms an inlet for an airflow from the aircraft's fan, flowing from the front to the rear of the aircraft through said channel. The invention thus provides rigid thermal protection for the lower side spar by directing an airflow from the fan within the shield.Such a shield also provides robust protection with an optimized thickness, and therefore size. Fig. 5.

Description

Title of the invention: DEVICE FOR THERMAL PROTECTION OF A LOWER SIDE BUILDING OF AN AIRCRAFT FRAMES technical field

[0001] The present invention relates to a thermal protection device for a lower spar of an aircraft box, as well as a propulsion system and an aircraft comprising such a protection device. PREVIOUS STATE OF THE ART

[0002] Conventionally, and as illustrated in Figs. 1 and 2, an aircraft 50 comprises a fuselage 51 and a wing 52 on each side of the fuselage 51. At least one propulsion system 100 is fixed under each wing 52 and comprises a turbojet 102 and a jet engine pylon 104.

[0003] By convention, X designates the longitudinal axis of the propulsion system 100 corresponding to a longitudinal axis X of the turbojet 102. Furthermore, Y designates the transverse axis of the system 100 corresponding to a transverse axis of the turbojet 102, this axis being horizontal when the aircraft is on the ground, and Z designates the vertical axis or vertical height of the propulsion system 100 corresponding to a vertical axis of the turbojet 102, this axis being vertical when the aircraft is on the ground, these three axes X, Y and Z being mutually orthogonal.

[0004] Furthermore, the terms "front" and "rear" are to be considered in relation to a forward direction of movement of the aircraft when the turbojet 102 is in operation, this direction being schematically represented by arrow 107. The turbojet 102 also has a vertical median plane P XZ passing through the longitudinal axis X and the vertical axis Z.

[0005] The turbojet 102 comprises, at the front, a fan casing 102a surrounding a tubular fan duct in which a fan rotates and, at the rear of the fan casing 102a, a smaller central casing 102b, enclosing the core of the turbojet 102. The fan casing 102a and the central casing 102b extend globally coaxially around the longitudinal axis X.

[0006] Figure 2 shows the propulsion system 100 with the turbojet engine 102 and the mast reactor 104 by which the turbojet 102 is fixed to the wing 52. The reactor mast 104 is represented here by its primary structure 106 which is fixed under the wing 52.

[0007] The primary structure 106 extends along the longitudinal axis X between a front end and a rear end and takes the form of a box which includes a lower spar 106a, an upper spar 106b, two side panels (not shown) connecting the two longerons and internal ribs 106c distributed along the box 106.

[0008] The turbojet 102 is fixed under the engine mast 104 by means of engine attachments which conventionally include, at the front, a front engine attachment 107a, at the rear, a rear engine attachment 107b, and between the front and rear engine attachments, a thrust force recovery assembly comprising recovery rods 107c fixed between the turbojet 102 and the box 106, to absorb the thrust forces generated by the turbojet 102.

[0009] The reactor mast also includes a secondary structure 108 which is located at the forward end of the casing 106 and below the lower spar 106a. This secondary structure is situated directly opposite the fan casing 102a and therefore receives outside air from the fan 102. The secondary structure 108 is thus not exposed to very high temperature levels since the outside air is generally cold and cools down within the secondary structure 108.

[0010] This is not the case for the lower spar 106a of the box 106. Indeed, and as illustrated in hatching on [Fig.2], the area 110 located between the lower spar 106a, the secondary structure 108 and the central casing 102b of the turbojet is exposed to very high temperatures and this area therefore constitutes an area of ​​significant fire risk.

[0011] In order to thermally protect the reactor pylon 106 casing 104, it is known to implement a thermal cover under the lower spar 106a. Such a thermal cover is generally flexible and is affixed against the lower spar 106a extending from the secondary structure 108 to the rear end of the lower spar 106a.

[0012] Figure 3 illustrates an example of a prior art attachment point for a thermal cover 109 on the lower side member 106a. Generally, the thermal cover 109 comprises an insulating plate 109a having a core, for example made from mineral silica powder, sandwiched between two thin sheets, for example 0.2 mm thick, made of Inconel (registered trademark). The plate 109a is attached to the underside of the lower side member 106a via a spacer 109b which is attached on one side to the lower side member 106a by two bolts 109c and on the other side to the insulating plate 109a by a bolt 109d.

[0013] One drawback of this solution lies in the fact that each fixing point of the thermal cover 109 constitutes a significant thermal bridge. Indeed, at each fixing point, the cover 109 is non-existent (or almost non-existent), which can lead to a sharp localized increase in the temperature of the lower stringer 106a. Furthermore, the cover 109 is generally thicker than 20 mm, which represents a relatively large size limiting The possibilities for installing other equipment in this zone 110. Furthermore, the materials used to manufacture such a thermal blanket are relatively expensive. Finally, since such a thermal blanket is relatively fragile, it can easily be damaged during handling, installation, or the installation of neighboring equipment.

[0014] Thus, there is a need to provide optimal thermal protection for the lower spar of an aircraft engine pylon box which addresses at least some of these drawbacks. Description of the invention

[0015] An object of the present invention is to propose a device for the thermal protection of a lower spar of an aircraft box which ensures optimal thermal protection by limiting thermal bridges, which is simple to implement and which is robust, in particular.

[0016] To this end, a device is proposed for the thermal protection of a lower spar of an aircraft fuselage, said aircraft comprising a turbojet engine intended to be fixed below said lower spar and comprising a fan intended to blow an airflow from the front to the rear of said aircraft. Said device, comprising a thermal protection shield intended to be disposed between said lower spar and said turbojet engine, includes:

[0017] - a first panel intended to extend globally parallel to a face lower of said lower spar and at a first distance from said lower face of said lower spar;

[0018] - a second panel intended to be placed between said first panel and said lower face of said lower spar, said second panel being intended to extend globally parallel to said lower face of said lower spar and at a second distance from said lower face of said lower spar.

[0019] The first and second panels define between them a channel extending generally parallel to and at a distance from the lower face, the channel having a front end intended to be located at the rear and opposite the fan of the turbojet engine, the front end forming an inlet for a primary portion of the airflow, the primary portion of the airflow flowing from the front to the rear of the aircraft through the channel. The device further includes fastening means for attaching the heat shield to the lower face of the lower spar.

[0020] In this way, the invention provides rigid thermal protection for the lower spar, which ensures that the shield temperature remains optimal by directing an airflow from the blower into the shield. Thus, The temperature of the lower spar is effectively lowered to maintain it at an optimal temperature significantly lower than the temperature of the very hot central zone of the turbojet engine. This type of shield also provides robust protection with an optimized thickness, and therefore a reduced size.

[0021] According to a first embodiment, said first and second panels are solid so that said primary part of said airflow flows only inside said channel.

[0022] According to a second embodiment, said first panel is solid and said second panel is at least partially perforated so that said primary part of said airflow flows inside said channel and at least a secondary part of said primary part of said airflow flows through said second panel towards said lower spar.

[0023] According to a particular aspect of the invention, said first panel comprises a plurality of first holes and said second panel comprises, for each first hole, a second hole coaxial with said first hole. Furthermore, the thermal protection shield comprises, for each pair of a first hole and an associated second hole, an insert disposed between said first and second panels, wherein the insert comprises a first central hole coaxial with said first and second holes. Said first central hole, first hole, and second hole allow the passage of an element of said fastening means.

[0024] According to another particular aspect of the invention, each insert comprises a first support surface to which the first panel is fixed and a second support surface to which the second panel is fixed.

[0025] According to yet another particular aspect of the invention, said second distance is greater than 2mm, and preferably between 5 and 45 mm.

[0026] According to a particular aspect of the invention, the device comprises, for each insert, a spacer made of a thermally resistant material, said spacer being intended to be disposed between said second panel and said lower face of said lower stringer, where said spacer has a thickness globally equal to said second distance, and where said spacer has a second central hole extending coaxially with said first hole of the associated insert and allowing the passage of said an element of said fastening means.

[0027] According to another particular aspect of the invention, the device comprises means for attaching said heat shield to said lower side member, said attachment means comprising:

[0028] - a nut support intended to be disposed against an upper face of said longitudinal member lower, said nut support having, for each insert, a drilling coaxial with said first central drilling of said insert;

[0029] - for each hole, a fixing nut disposed against said nut support;

[0030] - for each fixing nut, a fixing screw comprising a threaded rod intended to be threaded successively into said first central hole of the associated insert, into said second central hole of the associated spacer, into a hole of said lower stringer, into said associated hole of said nut support and into said associated fixing nut to be screwed into the latter, and a screw head intended to come into contact with said first panel.

[0031] The invention also proposes a propulsion system comprising a turbojet engine intended to be fixed to a lower spar of an aircraft box, said system comprising a device as described above.

[0032] The invention further proposes an aircraft comprising a propulsion system as described above. Brief description of the drawings

[0033] The features of the invention mentioned above, as well as others, will become clearer upon reading the following description of two exemplary embodiments, said description being made in relation to the accompanying drawings, among which:

[0034] [Fig-1] is a side view of an aircraft according to the invention;

[0035] [Fig.2] is a side and cross-sectional view of a propulsion system according to art previous;

[0036] [Fig.3] is a side and cross-sectional view of a thermal cover for a propulsion system according to the prior art;

[0037] [Fig.4] is a side and cross-sectional view of a propulsion system according to the invention;

[0038] [Fig. 5] is a perspective and cross-sectional view of a thermal protection device for a propulsion system according to the invention;

[0039] [Fig.6a] is a side and cross-sectional view of a thermal protection device according to a first embodiment of the invention;

[0040] [Fig.6b] is a detailed view of the thermal protection device of [Fig.6a];

[0041] [Fig.7a] is a side and cross-sectional view of a thermal protection device according to a second example of the realization of the invention;

[0042] [Fig. 7b] is a detailed view of the thermal protection device of [Fig. 7a]; and

[0043] [Fig. 8] is an exploded view of a thermal protection device according to the invention.

[0044] DETAILED DESCRIPTION OF TWO EMBODIMENTS

[0045] Fig. 1 illustrates an aircraft 50 according to the invention which comprises a fuselage 51 and a wing 52 on each side of the fuselage 51. At least one propulsion system 100 is fixed under each wing 52 and comprises a turbojet 102 and a jet pylon 104.

[0046] The turbojet 102 comprises, at the front, a fan casing 102a surrounding a tubular fan duct in which rotates a fan intended to blow an airflow F (from outside the aircraft 50) from the front to the rear of the aircraft 50 and, at the rear of the fan casing 102a, a smaller central casing 102b, enclosing the core of the turbojet 102. The fan casing 102a and the central casing 102b extend globally coaxially around the longitudinal axis X.

[0047] Fig. 4 shows the propulsion system 100 with the turbojet 102 and the engine pylon 104 by which the turbojet 102 is attached to the wing 52. The engine pylon 104 is represented here by its primary structure 106 which is attached under the wing 52.

[0048] The primary structure 106 extends along the longitudinal axis X between a front end and a rear end and takes the form of a box which includes a lower spar 106a, an upper spar 106b, two side panels (not shown) connecting the two spars and internal ribs 106c distributed along the box 106.

[0049] The reactor mast also includes a secondary structure 108 which is located at the front end of the box 106 and below the lower spar 106a. This secondary structure is located directly opposite the fan casing 102a and therefore receives the airflow F from the fan 102.

[0050] Figs. 4, 5, 6a and 7a illustrate examples of devices 2 intended for the thermal protection of the lower spar 106a of the box 106 of the aircraft 50.

[0051] More particularly, the device 2 includes a thermal protection shield 20 intended to be disposed between the lower spar 106a and the turbojet 102. The shield 20 includes a first panel 21 intended to extend generally parallel to a lower face 116 of the lower spar 106a and to a first distance dl from the lower face 116 of the lower spar 106a. For example, the first distance dl (visible in Figs. 6a and 7a) separating the first panel 21 from the lower face 116 of the lower spar 106a is between 10 and 70 mm.

[0052] The thermal protection shield 20 further comprises a second panel 22 intended to be positioned between the first panel 21 and the lower face 116 of the lower spar 106a. The second panel 22 is intended to extend generally parallel to the lower face 116 of the lower spar 106a, that is, generally parallel to the first panel 21, and at a second distance d2 from the lower face 116 of the lower spar 106a. For example, the second distance d2 (visible in Figs. 6a and 7a) separating the second panel 22 from the lower face 116 of the lower spar 106a is preferably between 5 and 45 mm.

[0053] It is therefore understood that the second distance d2 is less than the first distance dl. In this way, the first 21 and second 22 panels are separated from each other by The other two elements define a channel 23 which extends generally parallel to and at a distance from the lower face 116 of the lower spar 106a. The thickness of the channel 23, which is obtained by subtracting the second distance d2 from the first distance dl, is between approximately 5 and 20 mm. The thickness of the channel 23 is selected according to the volume of air required to ventilate the heat shield 20 (this therefore also depends on the dimensions of the lower face 116 of the lower spar 106a in particular).

[0054] More specifically, a forward end 231 of the channel 23 is intended to be located at the rear and opposite the fan of the turbojet 102 and to form an inlet for a primary portion Fl of the airflow F. The channel 23 has a second end 232 located at the rear of the propulsion system 100 which allows the primary portion Fl of the airflow F to be discharged. The primary portion Fl of the airflow F thus flows from the front to the rear of the aircraft 50 through the channel 23. The shield 20 is thus ventilated so as to lower its temperature and protect the lower spar 106a from the heat coming from the very hot central area 110 of the propulsion system 100.

[0055] The device 2 further includes fastening means 26 (described in more detail later in this description) intended to fix the thermal protection shield 20 to the lower face 116 of the lower spar 106a.

[0056] Such a shield 20, positioned at a distance from the lower face 116 of the lower spar 106a, provides on the one hand rigid thermal protection for the lower spar 106a and on the other hand ensures that the temperature of the shield 20 is always optimal by directing an airflow from the blower into the shield 20. In this way, the temperature of the lower spar 106b is effectively lowered so that it is maintained at an optimal temperature significantly lower than the temperature of the very hot central area 110.

[0057] Such a shield 20 also eliminates the need for a thick, flexible thermal cover. Thus, the thickness, and therefore the size, of the shield 20 is optimized. Compared to prior art solutions, the use of the shield 20 according to the invention frees up at least 10 mm of space, for example, along the entire length of the lower longitudinal member 106a. Furthermore, the materials used to manufacture the shield are significantly less expensive than the materials used for the prior art thermal cover (and in particular, the material of the cover body).

[0058] A thermal protection shield 20 made of titanium stainless steel (e.g., TA6V titanium) ensures high robustness so as to limit the risk of damage during handling and installation of the shield 20. Furthermore, this also limits the risk of damage due, for example, to the installation of other equipment near the shield 20. Similarly, Panels 21 and 22 have a thickness between 0.2mm and 1mm in order to further improve the robustness of shield 20.

[0059] Figs. 6a and 6b illustrate a first example of an embodiment of the invention in which the first 21 and second 22 panels are solid (i.e. they do not have perforations). In other words, the use of solid panels 21 and 22 allows the primary portion Fl of the airflow F to flow only within the channel 23. Indeed, the primary portion Fl of the airflow F entering the channel through the first end 231 can only escape from the channel 23 through the second end 232 of the channel 23 located at the rear of the propulsion system 100. In this way, the shield 20 acts as a cold barrier between the very hot central zone 110 of the propulsion system 100 and the lower spar 106a of the reactor pylon 104. The lower spar 106a is therefore protected from the heat emitted by the propulsion system 100.

[0060] In particular, the airflow F supplies channel 23 as soon as the turbojet fan 102 is running. Air therefore continuously supplies channel 23 when the turbojet 102 is running so that the lower spar 106a is protected when the central area 110 is hot (i.e. when the turbojet 102 is running).

[0061] Figs. 5, 7a, 7b and 8 illustrate a second embodiment of the invention in which the first panel 21 is solid and the second panel 22 is at least partially perforated. In other words, the primary portion Fl of the airflow F can flow in the channel 23 from the first end 231 to the second end 232, but at least a secondary portion F2 of the primary portion Fl of the airflow F can flow through the second panel 22, which is at least partially perforated, so that this secondary portion F2 can flow towards the lower spar 106a and directly cool the latter.

[0062] In this way, the shield 20 acts as a cold barrier between the very hot central zone 110 of the propulsion system 100 and the lower spar 106a of the reactor mast 104 while allowing continuous and direct ventilation of the lower face 116 of the lower spar 106a so as to optimally protect the lower spar 106a from the heat of the central zone 110.

[0063] In particular, the airflow F supplies channel 23 as soon as the turbojet fan 102 is running. Air therefore continuously supplies channel 23 when the turbojet 102 is running so that the lower spar 106a is protected from heat and ventilated by air when the central area 110 is hot (i.e. when the turbojet 100 is running).

[0064] The second panel 22 has perforations which are preferably distributed in a generally homogeneous manner. Depending on ventilation requirements On shield 20, the perforations can have a diameter of approximately 1 mm and be spaced 3.5 mm apart, or a diameter of 2.5 mm and be spaced 6 mm apart, for example. In this way, the secondary section F2 provides optimal airflow to ensure protection and ventilation of the lower spar 106a.

[0065] In accordance with the two embodiments described above, and as illustrated in Figs. 5 to 8, the first 21 and second 22 panels respectively comprise a plurality of first 211 and second 221 holes that extend generally coaxially between them. In other words, the first panel 21 comprises a plurality of first holes 211, and the second panel 22 comprises, for each first hole 211, a second hole 221 coaxial with the first hole 211. Furthermore, the thermal protection shield 20 comprises, for each pair of an associated first hole 211 and second hole 221, an insert 24 that is disposed between the first 21 and second 22 panels. More specifically, each insert 24 comprises a central first hole 241 that extends coaxially to an associated first hole 211 of the first panel 21 and to an associated second hole 221 of the second panel 22.The first central hole 241, first hole 211 and second hole 221 allow the passage of an element of the fastening means 26 (described below).

[0066] In particular, each insert 24 comprises a first bearing surface 242, substantially circular in shape in this example, to which the first panel 21 is attached, and a second bearing surface 243, also substantially circular in shape in this example, to which the second panel 22 is attached. The first 242 and second 243 bearing surfaces extend generally parallel to each other and are located opposite each other. The first 242 and second 243 bearing surfaces extend generally at the ends of the central bore 241.

[0067] As illustrated in Figs. 5 to 8, the panels 21 and 22 are fixed to the outer faces of the bearing surfaces 242 and 243. In other words, the inserts 24 are enclosed / sandwiched between the panels 21 and 22.

[0068] The thickness of the insert 24 (i.e., the distance between the first 242 and second 243 bearing surfaces) can be selected according to the desired thickness of the channel 23 to optimally protect the lower longitudinal member 106a from heat. Preferably, the thickness of the insert 24 is approximately between 5 and 20 mm.

[0069] For example, the panels 21 and 22 are welded, or brazed, to the inserts 24. However, other fixing techniques can be considered without departing from the principle of the invention.

[0070] These inserts make it possible to reinforce / rigidify the shield 20 and, as detailed later in this description, to fix the shield 20 to the lower longitudinal member 106a.

[0071] It is therefore easy to understand that it is possible to implement as many inserts 24 as necessary to ensure, on the one hand, optimal attachment of the shield 20 to the lower longitudinal member 106a and, on the other hand, good structural stability of the shield 20.

[0072] In addition, inserts 24 can be implemented solely to reinforce the structure of the shield 20. In this case, these reinforcing inserts 24 do not cooperate with fastening means 26 (described below).

[0073] Preferably, the second distance d2 separating the second panel 22 from the lower face 116 of the lower spar 106a is approximately between 5 and 45 mm.

[0074] In accordance with the two embodiments described above, and as illustrated, the device 2 comprises, for each insert 24, a spacer 25 made of a thermally resistant material (i.e., a material capable of withstanding the specific environment of the invention in which temperatures can reach 500 °C, for example). Preferably, the spacer 25 is made of a ceramic material. Indeed, such a material has a conductivity of 0.01 J / s / cm² (°C / cm), which allows it, in certain cases, to withstand temperatures up to 1260 °C, for example. The spacer 25 is intended to be positioned between the second panel 22 and the lower face 116 of the lower stringer 106a. The spacer 25 has a thickness that is roughly equal to the second distance d2 and ensures thermal insulation and a constant spacing between the lower face 116 of the lower spar 106a and the shield 20.The spacer 25 also helps to optimize the thermal barrier role played by the shield 20.

[0075] As before, the spacer 25 has a second central hole 251 extending coaxially from the first hole 241 of the associated insert 24 and allowing the passage of the element of the fasteners 26 of the heat shield 20 to the lower longitudinal member 106a (as detailed later in this description). The spacer 25 thus has a thickness (generally equal to the second distance d2) which is selected to avoid any risk of crushing the shield 20 when tightening the fasteners 26. The thickness of the spacer 25 can therefore vary depending on the mounting configuration.

[0076] In addition, the spacer 25 helps to limit thermal bridges between the shield 20 and the lower face 116 of the lower spar 106a. It also provides a mounting clearance between the shield 20 and the lower spar 106a, in order to take into account the splice fixings of the reactor mast 104 (i.e. the fixings between the spars and the side panels and / or the ribs, in particular).

[0077] As discussed previously, the device 2 includes means 26 for attaching the heat shield 20 to the lower side member 106a. These means 26 include a nut support 261 intended to be positioned against an upper face 126 (i.e. the opposite face to the lower face 116) of the lower stringer 106a. The nut support 261 has, for each insert 24, a hole 261a which extends coaxially with the first central hole 241 of the corresponding insert 24 (and therefore also coaxially with the associated holes 211 and 221 of the first and second panels 21 and 22).

[0078] The fastening means 26 comprise, for each hole 261a, a fastening nut 262 disposed against the nut support 261 on the face of the nut support 261 opposite the lower longitudinal member 106a. The fastening nut 262 comprises a tapped hole 262a which extends coaxially to the first central hole 241 of the associated insert 24 (and therefore also coaxially to the associated holes 211 and 221 of the first and second panels 21 and 22 and to the associated hole 261a of the nut support 261).

[0079] The fastening means 26 also include, for each fastening nut 262, a fastening screw 263 which has a threaded shank 263a for successively threading into the first central hole 241 of the associated insert 24, into the second central hole 251 of the associated spacer 25, into a hole 118 of the lower longitudinal member 106a, into the associated hole 261a of the nut support 261, and into the tapped hole 262a of the associated fastening nut 262 for screwing into the latter. The fastening screw 263 also has a screw head 263b for contacting the first panel 21 so that the screw head 263b and the fastening nut 262 clamp the shield 20 and the lower longitudinal member 106a.

[0080] Such fastening means ensure reliable assembly of the shield 20 to the lower longitudinal member 106a. Furthermore, the way in which the shield 20 is attached to the lower longitudinal member 106a makes it possible to limit, or even eliminate, thermal bridges at the various attachment points of the shield 20 to the lower longitudinal member 106a.

[0081] In addition, such fastening means 26 are simple and inexpensive to implement.

[0082] Preferably, the fastening means 26 further comprise a washer 27 having a third central hole 271. The washer 27 is disposed between the screw head 263b and the first panel 21 and the threaded rod 263a is intended to be threaded into the third central hole 271.

Claims

Demands

1. Device (2) for the thermal protection of a lower spar (106a) of an aircraft box (106) (50), said aircraft (50) comprising a turbojet (102) intended to be fixed below said lower spar (106a) and comprising a fan intended to blow an airflow (F) from the front to the rear of said aircraft (50), said device (2) comprising a thermal protection shield (20), intended to be disposed between said lower spar (106a) and said turbojet (102), which comprises: - a first panel (21) intended to extend globally parallel to a lower face (116) of said lower spar (106a) and to a first distance (dl) from said lower face (116) of said lower spar (106a);- a second panel (22) intended to be arranged between said first panel (21) and said lower face (116) of said lower spar (106a), said second panel (22) being intended to extend globally parallel to said lower face (116) of said lower spar (106a) and at a second distance (d2) from said lower face (116) of said lower spar (106a); where said first (21) and second (22) panels delimit between themselves a channel (23) having a front end (231) intended to be located at the rear and opposite said fan of said turbojet (102), said front end (231) forming an inlet orifice of a primary part (Fl) of said airflow (F), said primary part (Fl) of said airflow (F) flowing from the front to the rear of said aircraft (50) through said channel (23);and said device (2) further comprising fastening means (26) for fixing said thermal protection shield (20) to said lower face (116) of said lower spar (106a).;

2. Device (2) according to claim 1, characterized in that said first (21) and second (22) panels are solid so that said primary part (Fl) of said airflow (F) flows only inside said channel (23).

3. Device (2) according to claim 1, characterized in that said first panel (21) is solid and said second panel (22) is at least partially perforated so that said primary part (Fl) of said airflow (F) flows inside said channel (23) and at least a secondary part (F2) of said primary part (Fl) of said airflow (F) flows through said second panel (22) in the direction of said lower spar (106a).

4. Device (2) according to claim 2 or 3, characterized in that said first panel (21) has a plurality of first holes (211), in that said second panel (22) has for each first hole (211), a second hole (221) coaxial with said first hole (211), and in that said thermal protection shield (20) has for each pair of an associated first hole (211) and second hole (221), an insert (24) disposed between said first (21) and second (22) panels, wherein the insert (24) has a central first hole (241) coaxial with said first hole (211) and second hole (221), wherein said central first hole (241), first hole (211) and second hole (221) allow the passage of an element of said fastening means (26).

5. Device (2) according to claim 4, characterized in that each insert (24) comprises a first bearing surface (242) to which the first panel (21) is fixed and a second bearing surface (243) to which the second panel (22) is fixed.

6. Device (2) according to any one of claims 1 to 5, characterized in that said second distance (d2) is between 5 and 45 mm.

7. Device (2) according to any one of claims 4 to 6, characterized in that it comprises, for each insert (24), a spacer (25) intended to be disposed between said second panel (22) and said lower face (116) of said lower stringer (106a), wherein said spacer (25) has a thickness overall equal to said second distance (d2), and wherein said spacer (25) has a second central hole (251) extending coaxially from said first hole (241) of the associated insert (24) and allowing passage of said an element of said fastening means (26).

8. Device (2) according to claim 7, characterized in that said fastening means (26) comprise:

9.

10. - a nut support (261) intended to be disposed against an upper face (126) of said lower spar (106a), said nut support (261) having, for each insert (24), a hole (261a) coaxial with said first central hole (241) of said insert (24); - for each hole (261a), a fixing nut (262) is positioned against said nut support (261), - for each fixing nut (262), a fixing screw (263) having a threaded rod (263a) intended to be threaded successively into said first central hole (241) of the associated insert (24), into said second central hole (251) of the associated spacer (25), into a hole (118) of said lower stringer (106a), into said hole (261a) associated with said nut support (261) and into said fixing nut (262) associated for being screwed into the latter, and a screw head (263b) intended to come into contact with said first panel (21). Propulsion system (100) comprising a turbojet (102) intended to be fixed to a lower spar (106a) of an aircraft box (106) (50), said system (100) comprising a device (2) according to any one of claims 1 to 8. Aircraft (10) comprising a propulsion system (102) according to claim 9.

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