Aircraft

Abstract

The invention relates to an aircraft comprising at least one aerodynamic wall and at least one chamber (50) open at the aerodynamic wall, against which an air flow flows in a flow direction when the aircraft is in flight, said chamber (50) being defined by a tubular side wall (52) and a bottom (54), characterized in that the bottom (54) is arranged in the tubular side wall (52). The chamber (50) includes at least one channel cross-section reduction (56) extending away from the bottom (54) and only over a portion of the perimeter of the tubular sidewall (52). This arrangement allows a reduction in the noise of the aerodynamic source to be achieved.

Description

Technical Field

[0001] The application relates to an aircraft comprising at least one chamber opening at an aerodynamic wall and provided with a partial passage cross-section reduction. Background Art

[0002] According to one embodiment, the aircraft 10 includes a fuselage 12, wings 14 disposed on both sides of the fuselage 12, and a propulsion assembly 16 connected to the wings via a pylon 18. Figure 2 As can be seen in FIG. 1 , the aircraft 10 includes at least one air intake device 20, which opens at an aerodynamic wall 22 that contacts an air flow 24 when the aircraft 10 is in flight. The air intake device 20 is configured to capture a portion of the air flow 24 and direct it in a direction toward the equipment of the aircraft. The aerodynamic wall 22 may be provided at the fuselage 12, the wing 14, the propulsion assembly 16, or the pylon 18.

[0003] According to one construction, the air intake device 20 comprises: an air intake duct 26 extending between a first end 26.1 connected to the aerodynamic wall 22 and a second end 26.2; and a valve 28 connected to the second end 26.2 of the air intake device and configured to be in an on state and a closed state, in which the valve 28 allows the air flow guided by the air intake duct 26 to pass through the valve, and in the closed state, the valve 28 blocks the air flow from entering the air intake duct 26.

[0004] According to one configuration, the first end 26.1 opening at the aerodynamic wall 22 is flared and forms a flush air inlet. According to this configuration, the first end 26.1 of the air inlet duct 26 is positioned on a reference surface substantially parallel to the air flow 24, which, on the outside of the air inlet duct 26, coincides with the outer surface of the aerodynamic wall 22 in contact with the air flow 24.

[0005] The air inlet 20 is optimized to reduce the drag of the aircraft when the valve 28 is in the open state.

[0006] When the valve 28 is in the closed state, the air inlet pipe 26 and the valve 28 in the closed state form a chamber 30, such as Figure 3 As schematically shown, the chamber opens at the aerodynamic wall 22. The air flow 24 flowing over the chamber 30 generates noise of aerodynamic origin, in particular whistling noises, due to the coupling between the return air flow 24.1 formed in the chamber 30 and the disturbed air flow 24.2 emerging after the upstream edge 30.1 of the chamber 30. Summary of the invention

[0007] The present invention aims to remedy some or all of the deficiencies in the prior art.

[0008] To this end, the present invention relates to an aircraft comprising at least one aerodynamic wall and at least one chamber, wherein an air flow flows along a flow direction against (close to) the at least one aerodynamic wall when the aircraft is in flight, and the at least one chamber opens at the aerodynamic wall, the chamber being defined by a tubular side wall extending between a first end and a second end and a bottom located away from the aerodynamic wall and at the second end of the tubular side wall, the first end of the tubular side wall being located at the aerodynamic wall, the chamber having a reference channel cross-section and a depth, the tubular side wall being parallel to the reference direction and having a perimeter.

[0009] According to the invention, the chamber comprises at least one channel cross-section reduction remote from the bottom, which extends only over a portion of the circumference of the tubular side wall.

[0010] The fact that the channel cross-section reduction is remote from the bottom and is local (not formed continuously over the entire periphery of the tubular side wall) allows achieving a reduction in noise of aerodynamic origin.

[0011] According to another feature, the channel cross-section reduction extends over half of the circumference of the tubular side wall, with a tolerance interval of + / -20%, preferably + / -5%.

[0012] According to another feature, the passage section reduction is positioned in an upstream half-space defined by a median plane perpendicular to the flow direction of the air stream.

[0013] According to another feature, the channel cross-section reduction is positioned in a transverse plane perpendicular to the reference direction.

[0014] According to another feature, the transverse plane is located at a distance from the bottom that is approximately 30% of the depth of the chamber, with a tolerance interval of + / - 20%, preferably approximately + / - 5%.

[0015] According to another feature, the channel cross-section reduction has a channel cross-section of approximately 80% of the reference channel cross-section, with a tolerance interval of approximately + / -10%, preferably approximately + / -5%.

[0016] According to another feature, the tubular sidewall is cylindrical and has a reference diameter. In addition, the diameter of the channel cross-section reduction is about 80% of the reference diameter, with a tolerance interval of about + / - 10%, preferably about + / - 5%.

[0017] According to another feature, the passage section reduction portion comprises a rib protruding relative to the tubular sidewall, the rib comprising a first side extending from the tubular sidewall and oriented toward the first end of the tubular sidewall and a second side extending from the tubular sidewall and oriented toward the bottom.

[0018] According to another feature, the first side makes an angle with the tubular side wall comprised between 20° and 60°, preferably between 30° and 40°.

[0019] According to another feature, the second side is substantially perpendicular to the tubular side wall.

[0020] According to another feature, the rib is a hollow profile mounted (fixed or attached) against the tubular side wall.

[0021] According to another feature, the aircraft includes an air intake device, which includes: an air intake duct extending between a first end connected to an aerodynamic wall and a second end; and a valve connected to the second end of the air intake duct, the valve being constructed to be able to be in an on state and a closed state, in which the valve allows an air flow guided by the air intake duct to pass through the valve, and in which the valve blocks the air flow from entering the air intake duct, the air intake duct and the valve in the closed state defining a chamber opening at the aerodynamic wall. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Other features and advantages will appear from the following description of the invention, given by way of example only and with reference to the accompanying drawings, in which:

[0023] - Figure 1 This is a side view of the aircraft.

[0024] - Figure 2 is a longitudinal cross-sectional view showing an air intake device according to an embodiment of the prior art,

[0025] - Figure 3 yes Figure 2 A schematic diagram of an air inlet device forming a chamber and an air flow circulating above and in the chamber is shown in FIG.

[0026] - Figure 4 is a side view showing an air intake device for forming a chamber according to an embodiment of the present invention,

[0027] - Figure 5 is a side view showing an intake duct according to an embodiment of the present invention, a portion of the intake duct is not shown so that the interior of the intake duct is visible,

[0028] - Figure 6 is a cross-sectional view showing a chamber provided with a channel cross-section reduction portion according to an embodiment of the present invention,

[0029] - Figure 7 is a diagram showing an embodiment of the present invention. Figure 6 A cross-sectional view of a chamber provided with a channel cross-section reduction portion, taken along line VII-VII. DETAILED DESCRIPTION

[0030] according to Figure 4 In one embodiment, the aircraft includes at least one aerodynamic wall 40 and at least one air intake device 42.

[0031] The aerodynamic wall 40 has an outer surface F40 against which the air flow 44 flows in a flow direction when the aircraft is in flight. The aerodynamic wall (aerodynamic wall) may be provided at the fuselage, wings, propulsion assembly or pylon of the aircraft.

[0032] The air intake device 42 includes an air intake duct 46 and a valve 48, wherein the air intake duct 46 extends between a first end 46.1 connected to the aerodynamic wall 40 and a second end 46.2, and the valve 48 is connected to the second end 46.2 of the air intake duct 46 and is configured to be able to be in an on state and a closed state. In the on state, the valve 48 allows the air flow guided by the air intake duct 46 to pass through, and in the closed state, the valve 48 blocks the air flow in the air intake duct 46.

[0033] According to one configuration, the first end 46.1 opens at the aerodynamic wall 40 (at the height of the wall 40) and has a shape that flares in the direction of the outer surface F40 of the aerodynamic wall 40. Thus, the first end 46.1 of the air inlet duct 46 forms a flush air inlet. According to this configuration, the first end 46.1 of the air inlet duct 46 is positioned on a reference surface S substantially parallel to the air flow 44, outside the air inlet duct 46 and coinciding with the outer surface F40 of the aerodynamic wall 40 in contact with the air flow 44. The reference surface S and the outer surface F40 may also be flat or curved.

[0034] When the valve 48 is in the closed state, the air intake duct 46 and the valve 48 in the closed state form a chamber 50 opening at the aerodynamic wall 40 .

[0035] The chamber 50 is defined by a tubular side wall 52 extending between a first end 52.1 (corresponding to the first end 46.1 of the inlet duct 46) and a second end 52.2 (corresponding to the inlet duct 46) and a bottom 54 (corresponding to the valve 48 and more specifically to the blade or flap of the valve) remote from the aerodynamic wall 40 and located at the second end 52.2 of the tubular side wall 52. The first end 52.1 of the tubular side wall 52 (corresponding to the first end 46.1 of the inlet duct 46) is located at the outer surface F40 of the aerodynamic wall 40. The tubular side wall 52 is substantially parallel to a reference direction DD which may be perpendicular or inclined relative to the reference surface S. As a guide, the reference direction DD forms an angle of about 60° with the reference surface S.

[0036] According to one configuration, the tubular side wall 52 is cylindrical and has an axis of revolution A52 parallel to the reference direction.

[0037] According to one arrangement, the bottom 54 is substantially perpendicular to the reference direction DD.

[0038] The chamber 50 has a reference channel cross section Sr corresponding to the cross section of the tubular sidewall 52. When the tubular sidewall 52 is cylindrical, the reference channel cross section Sr is characterized by a diameter Dr, such as Figure 6 shown.

[0039] The chamber 50 has a depth P corresponding to the average distance between the reference surface S and the bottom 54. When the tubular sidewall 52 is cylindrical, the depth P corresponds to the distance separating the first intersection point (crossover point) between the axis of revolution A52 and the reference surface S and the second intersection point between the axis of revolution A52 and the bottom 54.

[0040] According to one characteristic of the invention, the chamber 50 comprises at least one partial channel section reduction 56 remote from the bottom 54. "Partial" means that the channel section reduction 56 extends only over a portion of the circumference of the tubular side wall 52 and not over the entire circumference.

[0041] According to one configuration, the channel cross-section reduction 56 is positioned in a transverse plane perpendicular to the reference direction DD. This transverse plane is located at a distance from the bottom 54 of about 30% of the depth P, with a tolerance interval of + / - 20% and preferably + / - 5%.

[0042] According to one configuration, the channel cross section of the channel cross section reduction portion 56 is about 80% of the reference channel cross section Sr, with a tolerance interval of about + / -10%, preferably + / -5%. When the tubular sidewall 52 is cylindrical and has a reference diameter Dr, the diameter D56 of the channel cross section reduction portion 56 is about 80% of the reference diameter Dr, with a tolerance interval of about + / -10%, preferably about + / -5%.

[0043] According to one arrangement, the channel cross-section reduction 56 extends over half of the circumference of the tubular side wall 52 , with a tolerance interval of + / −20% and preferably + / −5%.

[0044] According to one arrangement, when the tubular side wall 52 is inclined, the passage section reduction 56 is located in an upstream half-space defined by a mid-plane through which the axis of revolution A52 passes and which is perpendicular to the flow direction of the air flow 44. The term upstream means that with reference to the flow direction of the air flow 44, the air flow flows from upstream to downstream.

[0045] According to one embodiment, the channel cross-section reduction portion 56 includes a rib 58, which protrudes relative to the tubular side wall 52 and includes a first side 58.1 extending from the tubular side wall 52 and facing the first end 52.1 of the tubular side wall, and also includes a second side 58.1 extending from the tubular side wall 52 and facing the bottom 54.

[0046] According to one configuration, the first side surface 58 . 1 forms an angle A1 with the tubular side wall 52 of between 20° and 60°, preferably between 30° and 40°.

[0047] According to one arrangement, the second side surface 58 . 2 is substantially perpendicular to the tubular side wall 52 .

[0048] According to an embodiment, the rib 58 has a middle area 58.3 interposed between the first side 58.1 and the second side 58.2 and connecting the two. According to one configuration, the middle area 58.3 may be curved.

[0049] according to Figure 7 In one embodiment, which can be seen in FIG. 5 , the rib 58 is a hollow profile (or flange) attached to the tubular side wall 52. As an indication, the rib 58 can be made of plastic and abut and fix to the tubular side wall 52 by gluing or any other means.

[0050] The ribs 58 may be solid. The fact that the profile is hollow may allow a reduction in weight to be achieved.

[0051] The fact that the passage section reduction 56 is remote from the bottom 54 and is partial or local (not continuous over the entire periphery of the tubular side wall 52 ) allows achieving a reduction in noise of aerodynamic origin.

Claims

1. An aircraft, comprising: at least one aerodynamic wall (40) against which an air flow (44) flows in a flow direction when the aircraft is in flight; as well as at least one chamber (50), the chamber (50) opening at the aerodynamic wall (40) and defined by a tubular side wall (52) extending between a first end (52.1) and a second end (52.2) and a bottom (54) remote from the aerodynamic wall (40) and located at the second end (52.2) of the tubular side wall (52), the first end (52.1) of the tubular side wall (52) being located at the aerodynamic wall (40), the chamber (50) having a reference channel cross section (Sr) and a depth (P), the tubular side wall (52) being parallel to a reference direction (DD) and having a perimeter; Characterized in that the chamber (50) comprises at least one passage section reduction portion (56) remote from the bottom (54) and extending only over a portion of the periphery of the tubular side wall (52).

2. The aircraft according to claim 1, characterized in that The passage cross-section reduction (56) extends over half of the circumference of the tubular side wall (52) with a tolerance interval of + / -20%, preferably + / -5%.

3. The aircraft according to claim 2, characterized in that: The passage cross-section reduction portion (56) is located in an upstream half-space defined by a median plane perpendicular to the flow direction of the air flow (44).

4. An aircraft according to any one of the preceding claims, characterised in that The channel cross-section reduction (56) is positioned in a transverse plane perpendicular to the reference direction (DD).

5. The aircraft according to claim 4, characterized in that The transverse plane is located at a distance from the bottom (54) of about 30% of the depth (P) of the chamber (50), with a tolerance interval of + / -20%, preferably + / -5%.

6. An aircraft according to any one of the preceding claims, characterised in that The channel cross section of the channel cross section reduction portion (56) is approximately 80% of the reference channel cross section (Sr), with a tolerance interval of approximately + / -10%, preferably approximately + / -5%.

7. The aircraft according to claim 6, characterized in that The tubular side wall (54) is cylindrical and has a reference diameter (Dr), and the diameter (D56) of the channel cross-section reduction (56) is about 80% of the reference diameter (Dr), with a tolerance interval of about + / -10%, preferably about + / -5%.

8. An aircraft according to any one of the preceding claims, characterised in that The channel cross-section reduction portion (56) includes a rib (58) protruding relative to the tubular side wall (52), and the rib (58) includes a first side (58.1) and a second side (58.1), the first side (58.1) extending from the tubular side wall (52) and facing the first end (52.1) of the tubular side wall (52), and the second side (58.1) extending from the tubular side wall (52) and facing the bottom (54).

9. The aircraft according to claim 8, characterized in that The first side surface (58.1) forms an angle with the tubular side wall (52) between 20° and 60°, preferably between 30° and 40°.

10. The aircraft according to claim 8 or 9, characterized in that The second side surface (58.2) is substantially perpendicular to the tubular side wall (52).

11. An aircraft according to any one of claims 8 to 10, characterized in that The rib (58) is a hollow profile fixed against the tubular side wall (52).

12. An aircraft according to any one of the preceding claims, characterised in that The aircraft also includes: an air intake device (42), the air intake device (42) comprising an air intake duct (46), the air intake duct (46) extending between a first end (46.1) connected to the aerodynamic wall (40) and a second end (46.2); and A valve (48) is connected to the second end (46.2) of the intake pipe (46) and is configured to be in an on state and a closed state. In the on state, the valve (48) allows the air flow guided by the intake pipe (46) to pass through the valve (48), while in the closed state, the valve (48) blocks the air flow from entering the intake pipe (46). The intake pipe (46) and the valve (48) in the closed state define a chamber (50) opening at the aerodynamic wall (40).

Images