Propulsion assembly comprising at least one protective housing configured to accommodate at least one section of a long element such as an electrical cable

Abstract

Propulsion assembly comprising at least one protective housing configured to house at least one section of a long element such as an electrical cable. The invention relates to a propulsion assembly comprising: a motor (42), a primary structure (50) of a mast configured to connect the motor (42) to an aircraft structure, at least one long element, selected from an electrical cable (60), a conduit, and a sheath, extending from the primary structure (50) to the motor (42), and at least one thermally insulated protective housing (62), separate from the primary structure (50), delimiting an internal zone extending from the primary structure (50) to the nearest point of the motor (42) and in which the long element is positioned. Thus, the section of the long element positioned in the protective housing (62) does not need to be configured for very high temperatures. Figure 5

Description

Title of the invention: Propulsion assembly comprising at least one protective housing configured to accommodate at least one section of a long element such as an electrical cable

[0001] The present application relates to a propulsion assembly comprising at least one protective housing configured to house at least one section of a long element such as an electrical cable and to an aircraft comprising at least one such propulsion assembly.

[0002] According to a configuration visible in figures 1 to 3, an aircraft 10 comprises several propulsion units 12 which are positioned under the wing 14 of the aircraft 10.

[0003] A propulsion assembly 12 includes a motor 16, a nacelle 18 (not shown in [Fig.2]) positioned around the motor 16 and a mast 20 connecting the motor 16 to the rest of the aircraft 10, in particular to the wing 14.

[0004] For the remainder of this description, a longitudinal direction X is parallel to the axis of rotation A16 of the motor 16. A transverse plane is a plane perpendicular to the axis of rotation A16 of the motor 16. A horizontal transverse direction Y is a direction perpendicular to the axis of rotation A16 of the motor 16 and horizontal. A vertical transverse direction Z is a direction perpendicular to the axis of rotation A16 of the motor 16 and vertical. A vertical median plane PMV is a vertical plane containing the axis of rotation A16 of the motor 16. The terms front and rear refer to the direction of airflow in the motor 16, which flows from front to rear.

[0005] The engine 16 includes a fan 22 which has a fan casing 22.1 and a reactor core 24 which extends from a front part 24.1 positioned inside the fan 22 to a rear part 24.2. The reactor core 24 has an outer casing called the engine casing F24.

[0006] The nacelle 18 includes an inner wall 18.1 which delimits with the motor housing F24 an annular conduit 26 in which an airflow flows.

[0007] The drive assembly 12 also includes upper and lower bifurcations, positioned at 12 o'clock and 6 o'clock respectively, connecting the inner wall 18.1 of the nacelle and the drive assembly 16. Each upper and lower bifurcation is hollow and forms a housing in which equipment can be positioned.

[0008] The mast 20 comprises a primary structure 28, in the form of a box, which is connected to the sail 14 by a sail attachment system and to the motor 16 by a motor attachment system. This primary structure 28 includes a lower wall 28.1, oriented towards the motor 16, which forms a fire barrier.

[0009] According to an embodiment visible in [Fig.2], the engine attachment system comprises a front attachment 30.1 connecting the front end of the primary structure 28 and the fan casing 22.1, a rear attachment 30.2 connecting the rear end of the primary structure 28 and the rear part 24.2 of the reactor core 24 and two connecting rods 30.3, positioned symmetrically with respect to the vertical median plane PMV of the engine 16, connecting the primary structure 28 and the reactor core 24.

[0010] As illustrated in [Fig. 3], electrical cables 32 and possibly piping run through the upper bifurcation between the primary structure 28 of the mast 20 and the drive unit 16. These electrical cables 32 must be protected against high temperatures (well above 200°C), particularly in the area below the lower wall 28.1 of the primary structure 28, which is a fire zone. To this end, each cable includes a protective sheath to insulate it from high temperatures. This embodiment is not satisfactory because it increases the mass and size of the electrical cables 32.

[0011] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0012] To this end, the invention relates to a propulsion system comprising: a. an engine, b. a nacelle surrounding the engine, c. an annular conduit positioned between the engine and the nacelle, d. at least one superior bifurcation extending into the annular canal and connects the gondola and the motor, e. a primary mast structure configured to connect the propulsion system to an aircraft structure, f. at least one long element, chosen from an electrical cable, a conduit and a sheath, which extends in the bifurcation, and from the primary structure to the motorization.

[0013] According to the invention, the propulsion assembly includes at least one thermally insulated protective housing, separate from the primary structure, delimiting at least part of an internal zone which extends from the primary structure to the closest point to the motorization and in which the long element is positioned.

[0014] According to the invention, the part of the long element positioned in the protective housing being protected, only a reduced section of the long element, located between the protective housing and the motorization, needs to be protected, which helps to reduce the mass and size of the long element.

[0015] According to another feature, the protective housing includes at least one air inlet allowing communication between an external area of ​​the protective housing located in the annular duct and the internal area of ​​the protective housing.

[0016] According to another feature, the upper bifurcation includes a leading edge at which the air inlet is positioned.

[0017] According to another feature, the protective housing includes at least one exhaust allowing air to exit the protective housing.

[0018] According to another feature, the protective case comprises: a. at least one passage wall, slightly spaced from the motorization, having at least one through hole through which the long element passes, b. at least one sealing system, at the level of each through hole, configured to fill a space between the passage wall and the long element.

[0019] According to another feature, the protective housing has a front transverse wall, a rear transverse wall, a substantially horizontal end wall connecting the front and rear transverse walls, and right and left side walls connected to the end wall and the front and rear transverse walls.

[0020] According to another feature, the rear transverse wall includes an upper edge connected in a sealed manner to the primary structure.

[0021] According to another feature, the front transverse wall has an upper edge distant from the primary structure, the propulsion assembly comprising at least one partition connected in a watertight manner to the front transverse wall and to the upper bifurcation.

[0022] According to another feature, the right and left side walls have upper edges distant from the primary structure, the propulsion assembly comprising, for each of the right and left side walls, at least one sealing joint interposed between the right or left side wall and the upper bifurcation.

[0023] According to another feature, the propulsion assembly includes a first sealing joint interposed between, on the one hand, an upper edge of the right side wall, a right edge of the rear transverse wall and a right edge of the primary structure and, on the other hand, the upper bifurcation and a second sealing joint interposed between, on the one hand, an upper edge of the left side wall, a left edge of the rear transverse wall and a left edge of the primary structure and, on the other hand, the upper bifurcation.

[0024] According to another feature, each of the right and left side walls has a first face adjoining the end wall and inclined so as to be oriented towards the motorization as well as a second panel forming an angle between 60 and 120° with the first panel.

[0025] According to another feature, the protective housing is suspended below the primary structure, the propulsion assembly comprising at least one connecting rod which links the protective housing and the primary structure.

[0026] The invention also relates to an aircraft comprising at least one propulsion assembly according to one of the preceding characteristics.

[0027] Other features and advantages will become apparent from the following description of the invention, given by way of example only, with reference to the accompanying drawings, among which:

[0028] [Fig-1] is a side view of an aircraft,

[0029] [Fig.2] is a side view of a nacelleless propulsion assembly illustrating a method of implementation of the prior art,

[0030] [Fig.3] is a schematic representation of part of a propulsion assembly illustrating a method of realizing earlier art,

[0031] [Fig.4] is a schematic representation of part of a propulsion assembly illustrating one embodiment of the invention,

[0032] [Fig. 5] is a side view of a protective housing illustrating one embodiment of the invention,

[0033] [Fig.6] is a perspective view of a bifurcation of a propulsion assembly at which level a protective casing is positioned, illustrating one embodiment,

[0034] [Fig.7] is a longitudinal section of part of the bifurcation visible on the [Fig.6]

[0035] [Fig.8] is a perspective view of a protective housing illustrating a mode of realization of the invention,

[0036] [Fig.9] is a longitudinal section of the protective housing visible in [Fig.8].

[0037] According to an embodiment visible in [Fig.4], a propulsion assembly 40 comprises a motor 42, a nacelle 44 positioned around the motor 42 and a mast connecting the motor 42 to an aircraft structure such as an aircraft wing for example.

[0038] The motor 42 includes an outer casing F42. In addition, the nacelle 44 includes an inner wall F44 which delimits with the outer casing F42 of the motor 42 an annular duct 46 located between the nacelle 44 and the motor 42 and in which an airflow flows.

[0039] The drive assembly 40 includes at least one upper bifurcation 48, positioned at 12 o'clock, which extends into the annular conduit 46 and connects the inner wall F44 of the nacelle 44 and the drive 42. Generally, the drive assembly 40 also includes a lower bifurcation positioned at 6 o'clock. The upper bifurcation 48 is hollow and forms a housing in which equipment, conduits, electrical cables, and other components can be positioned. According to an embodiment shown in [Fig. 6], the upper bifurcation 48 forms an aerodynamic fairing and comprises a leading edge 48.1, a trailing edge 48.2, and side walls 48.3, connecting the leading and trailing edges 48.1 and 48.2, which are substantially symmetrical with respect to the vertical median plane PMV. In [Fig. 6], only one of the side walls 48.3 is shown in dashed form.

[0040] The mast includes a primary structure 50 configured to connect the drive unit 42 to an aircraft structure such as a wing. This primary structure 50 is connected to the drive unit 42 by a drive attachment system and generally has a box-section structure. This primary structure 50 includes a lower wall 50.1 oriented towards the drive unit 42 and configured to form a fire barrier. In one arrangement, a portion of the primary structure 50 is positioned inside the upper bifurcation 48.

[0041] According to one embodiment, the motor attachment system may include a front attachment 52.1 connecting the front end of the primary structure 50 and the motor 42, a rear attachment 52.2 connecting the rear end of the primary structure 50 and the motor 42, and two connecting rods 52.3, positioned symmetrically with respect to the vertical median plane PMV of the motor 42, connecting the primary structure 50 and the motor 42.

[0042] The engine 42, the nacelle 44, the upper and lower bifurcations 48, the primary structure 50 of the mast, and the engine attachment system are not further described, as they are known to those skilled in the art and can be substantially identical to those of the prior art. Regardless of the embodiment, an aircraft comprises at least one propulsion unit 40.

[0043] The propulsion assembly 40 includes at least one heat exchanger 54 positioned between the primary structure 50 and the engine 42 inside the upper bifurcation 48, said heat exchanger 54 being configured to provide heat exchange between two fluids. This heat exchanger 54 includes a first inlet 54.1, oriented towards the leading edge 48.1 of the upper bifurcation 48, allowing a first fluid to enter the heat exchanger 54, and a first outlet 54.2, oriented towards the trailing edge 48.2, allowing the first fluid to exit the heat exchanger 54.

[0044] According to one arrangement, the heat exchanger 54 is positioned near the rear edge 48.2 of the upper bifurcation 48. In addition, the propulsion assembly 40 includes a pipe 56, positioned in the upper bifurcation 48, which connects to a through port 56.1 provided at the leading edge 48.1 of the bifurcation. upper 48 and the first inlet 54.1 of the heat exchanger 54. Of course, the invention is not limited to this arrangement for the heat exchanger 54.

[0045] According to one embodiment, the heat exchanger 54 is integral with the primary structure 50. By way of example, the heat exchanger 54 is suspended below the primary structure 50 and connected to the latter by connecting rods 58.

[0046] The propulsion assembly 40 includes at least one electrical cable 60 which runs from the nacelle 44 to the motor 42. According to one configuration, the electrical cable 60 is positioned inside the upper bifurcation 48 and extends from the lower wall 50.1 of the primary structure 50 to the motor 42.

[0047] According to one arrangement, the propulsion assembly 40 comprises several electrical cables 60 grouped into one or more bundles of electrical cables.

[0048] According to a particular feature of the invention, the propulsion assembly 40 comprises at least one thermally insulated protective housing 62 positioned between the primary structure 50 and the motor 42, in which is located at least one electrical cable 60 which runs from the nacelle 44 to the motor 42. The protective housing 62 comprises at least one passage wall 64 closely spaced from the motor 42 and through which the electrical cable 60 passes. By closely spaced, it is understood that the passage wall 64 is located at a distance from the motor 42, more particularly from its outer casing F42, of a distance of less than 20 cm and preferably less than 10 cm.

[0049] This protective housing 62 is separate from the primary structure 50 and configured to form a fire barrier. By way of example, this protective housing 62 is made of stainless steel, TA6V titanium, or an alloy resistant to relatively high temperatures.

[0050] The passage wall 64 includes at least one through hole 66 (visible in [Fig.8]) to house at least one electrical cable 60 and allow it to pass through the passage wall 64. To obtain a seal between the passage wall 64 and each electrical cable 60 passing through it, the protective housing 62 includes at least one sealing system 68, such as a cable gland (visible in [Fig.9]) at each through hole 66, configured to fill a space between the passage wall 64 and the electrical cable 60.

[0051] This protective housing 62 includes at least one air inlet 70 allowing communication between an external zone located outside the protective housing 62 and in the annular duct 46 and an internal zone located inside the protective housing 62. This air inlet 70 allows fresh air circulating in the annular duct 46 to enter the protective housing 62 in order to ventilate the interior of the protective housing 62 and limit a rise in temperature inside the protective housing 62. By way of example, the fresh air that enters the protective housing 62 at a temperature of around 100°C allows to maintain inside the protective housing 62 a temperature below 200°C, significantly lower than the temperature of the air surrounding the protective housing 62 outside of the latter, which can reach around 500°C.

[0052] According to one configuration, the air inlet 70 is located at the leading edge 48.1 of the bifurcation 48. Thus, when the motor 42 is running, the air circulating in the annular duct 46 naturally enters the protective housing 62.

[0053] In addition to the air inlet 70, the protective housing 62 includes an exhaust 70' allowing the air inside the protective housing to escape. The air inlet 70 and the exhaust 70' are arranged to promote ventilation in all areas inside the protective housing 62.

[0054] According to one arrangement, the protective housing 62 has a front transverse wall 72.1 (perpendicular to the longitudinal direction X), a rear transverse wall 72.2 parallel to the front transverse wall 72.1 and offset rearward from the latter, a substantially horizontal end wall 74 connecting the front and rear transverse walls 72.1, 72.2 and right and left side walls 76, 76' connected to the end wall 74 and connecting the front and rear transverse walls 72.1, 72.2.

[0055] According to one configuration, the right and left side walls 76, 76' are not vertical. Each right and left side wall 76, 76' has a first panel 76.1, 76.1' adjoining the end wall 74 and inclined to form (from inside the protective housing 62) an angle greater than 110° with the end wall 74 in order to be oriented towards the motor 42 and a second panel 76.2, 76.2' forming an angle between 60 and 120° with the first panel 76.1, 76.1'.

[0056] According to this configuration, at least one element among the first sections 76.1, 76.1' of the right and left side walls 76, 76' as well as the terminal wall 74 can form a passage wall 64 through which the electrical cable(s) 60 passes.

[0057] In one embodiment, the rear transverse wall 72.2 is almost abutting the heat exchanger 54 and extends to the primary structure 50. It thus comprises an upper edge 78 sealed to the primary structure 50 and an opening 80 to allow passage of the pipe 56 that supplies the heat exchanger 54. In this embodiment, the rear transverse wall 72.2 is sealed to the primary structure 50 and to the pipe 56. This rear transverse wall 72.2 includes the exhaust 70' allowing air to escape from the protective housing 62.

[0058] According to one arrangement, the forward transverse wall 72.1 has an upper edge 82 distant from the primary structure 50. In this case, the propulsion assembly comprises at least one partition 84, substantially horizontal, connected in a watertight manner to the The front transverse wall 72.1 and the upper bifurcation 48 are similarly arranged. The right and left side walls 76, 76' have upper edges 86, 86' that are offset from the primary structure 50. According to this arrangement, a portion of the upper bifurcation 48 provides continuity between the protective housing 62 and the primary structure 50 and / or the nacelle 44. Thus, the protective housing 62 and a portion of the upper bifurcation 48 define a ventilated cavity in which a temperature below 200°C is maintained. According to this arrangement, the propulsion assembly includes, for each of the right and left side walls 76, 76', at least one sealing gasket 88, 88' interposed between the right or left side wall 76, 76' and the upper bifurcation 48.The latter ensures continuity between, on the one hand, the partition 84 and the upper edges 86, 86' of the right and left side walls 76, 76' and, on the other hand, the primary structure 50 and / or the nacelle 44. According to one embodiment, at least one sealing joint 88 is provided between the bifurcation 48 and at least one element among the upper edges 86, 86' of the right and left side walls 76, 76', the partition 84 and the rear transverse wall 72.2. According to one configuration, a first sealing joint 88 is interposed between, on the one hand, the right edge of the partition 84, the upper edge 86 of the right side wall 76 and the right edge of the rear transverse wall 72.2 and, on the other hand, the bifurcation 48. This first sealing joint 88 can extend to the right edge of the lower wall 50.1 of the primary structure 50.In addition, a second sealing joint 88' is interposed between, on the one hand, the left edge of the partition 84, the upper edge 86' of the left side wall 76' and the left edge of the rear transverse wall 72.2 and, on the other hand, the bifurcation 48. This second sealing joint 88' can extend to the left edge of the lower wall 50.1 of the primary structure 50.

[0059] In one embodiment, the protective housing 62 is suspended below the primary structure 50, and the propulsion assembly 40 includes at least one connecting rod 90 linking the protective housing 62 and the primary structure 50. In one configuration, the upper edge 78 of the rear transverse wall 72.2 is fixed to the primary structure 50. In addition, the propulsion assembly 40 includes a first connecting rod 90 comprising a first end 90.1 connected to the primary structure 50 and a second end 90.2 connected to the upper edge 86 of the right side wall 76 at a point as far as possible from the rear transverse wall 72.2, as well as a second connecting rod 90' comprising a first end 90.1' connected to the primary structure 50 and a second end 90.2' connected to the upper edge 86' of the left side wall 76' at a point as far as possible from the rear transverse wall 72.2.Of course, the invention is not limited to this embodiment for connecting the protective housing 62 to the nacelle 44 and / or to the primary structure 50.

[0060] Regardless of the embodiment, the propulsion assembly 40 comprises at least one linear element, selected from an electrical cable 60, a conduit, and a sheath, extending in the upper bifurcation 48 from the primary structure 50 to the motor 42, as well as at least one thermally insulated protective housing 62 that delimits at least part of an internal zone in which the linear element is positioned. This internal zone extends from the primary structure 50 of the mast to as close as possible to the motor 42, with a temperature below 200°C being maintained in this internal zone. Thus, the linear element, namely the electrical cable 60, the conduit, and / or the sheath, is not configured to be fire-rated on the section positioned within the protective housing 62, thereby reducing the mass of said linear element.

[0061] According to a preferred configuration, the propulsion assembly 40 includes a ventilation system for the interior area of ​​the protective housing 62 in order to maintain a temperature below 200°C, said ventilation system including at least one air inlet 70 configured to draw air from the annular duct 46 and return it to the protective housing 62 and an exhaust 70' allowing the air present in the protective housing 62 to be evacuated.

Claims

1.

2.

3.

4.

5. Demands Propulsion system including: a. a motor (42), b. a nacelle (44) surrounding the motor (42), c. an annular conduit (46) positioned between the motor (42) and the nacelle (44), d. at least one upper bifurcation (48) which extends into the annular conduit (46) and connects the nacelle (44) and the motorization (42), e. a primary structure (50) of a mast configured to connect the propulsion system (42) to an aircraft structure, f. at least one long element, chosen from an electrical cable (60), a conduit and a sheath, which extends in the upper bifurcation (48), and from the primary structure (50) to the motorization (42); g. characterized in that the propulsion assembly includes at least one thermally insulated protective housing (62), separate from the primary structure (50), delimiting at least part of an internal zone which extends from the primary structure (50) to the closest point to the motorization (42) and in which the long element is positioned. A propulsion assembly according to the preceding claim, characterized in that the protective housing (62) comprises at least one air inlet (70) allowing communication between an external area of ​​the protective housing (62) located in the annular duct (46) and the internal area of ​​the protective housing (62). A propulsion assembly according to the preceding claim, characterized in that the upper bifurcation (48) comprises a leading edge (48.1) at which the air inlet (70) is positioned. A propulsion assembly according to any one of the preceding claims, characterized in that the protective housing (62) comprises at least one exhaust (70') allowing air to exit the protective housing (62). Propulsion assembly according to any one of the preceding claims, characterized in that the protective housing (62) comprises: a. at least one passage wall (64), slightly spaced from the motorization (42), which has at least one through hole (66) through which the long element passes, b. at least one sealing system (68), at the level of each through hole (66), configured to fill a space between the passage wall (64) and the long element.

6. Propulsion assembly according to any one of the preceding claims, characterized in that the protective housing (62) has a front transverse wall (72.1), a rear transverse wall (72.2), a substantially horizontal end wall (74) connecting the front and rear transverse walls (72.1, 72.2) and right and left side walls (76, 76') connected to the end wall (74) and to the front and rear transverse walls (72.1, 72.2).

7. Propulsion assembly according to the preceding claim, characterized in that the rear transverse wall (72.2) comprises an upper edge (78) connected in a hermetically sealed manner to the primary structure (50).

8. Propulsion assembly according to any one of claims 6 to 7, characterized in that the front transverse wall (72.1) has an upper edge (82) distant from the primary structure (50) and in that the propulsion assembly comprises at least one partition (84) connected in a watertight manner to the front transverse wall (72.1) and to the upper bifurcation (48).

9. Propulsion assembly according to any one of claims 6 to 8, characterized in that the right and left side walls (76, 76') have upper edges (86, 86') distant from the primary structure (50) and in that the propulsion assembly comprises, for each of the right and left side walls (76, 76'), at least one sealing joint (88) interposed between the right or left side wall (76, 76') and the upper bifurcation (48).

10. Propulsion assembly according to any one of claims 6 to 9, characterized in that the propulsion assembly comprises a first sealing joint (88) interposed between, on the one hand, an upper edge (86) of the right-hand side wall (76), a right-hand edge of the rear transverse wall (72.2) and a right-hand edge of the primary structure (50) and, on the other hand, the upper bifurcation (48) thus that a second sealing joint (88') is interposed between, on the one hand, an upper edge (86') of the left side wall (76'), a left edge of the rear transverse wall (72.2) and a left edge of the primary structure (50) and, on the other hand, the upper bifurcation (48).

11. Propulsion assembly according to any one of claims 6 to 10, characterized in that each of the right and left side walls (76, 76') has a first panel (76.1, 76.1') adjoining the terminal wall (74) and inclined so as to be oriented towards the motorization (42) and a second panel (76.2, 76.2') forming an angle between 60 and 120° with the first panel (76.1, 76.1').

12. Propulsion assembly according to any one of the preceding claims, characterized in that the protective housing (62) is suspended below the primary structure (50) and in that the propulsion assembly (40) includes at least one connecting rod (90) linking the protective housing (62) and the primary structure (50).

13. Aircraft comprising at least one propulsion assembly according to one of the preceding claims.

Images