Outflow valve assembly with sound absorption function and aircraft comprising same

Abstract

An outflow valve assembly for an aircraft, an aircraft including the outflow valve assembly, and a method for installing an outflow valve assembly to an aircraft are provided. In one example, the outflow valve assembly includes a louver movably disposed to at least partially cover an opening formed through a fuselage on the aircraft. An electric motor is coupled to the louver and configured to move the louver between a closed position that prevents fluid communication through the opening and an open position that allows fluid communication between an interior and an exterior of the aircraft through the opening. An acoustic panel is disposed adjacent to the opening to attenuate noise generated when the louver is in the open position.

Description

TECHNICAL FIELD

[0001] The technical field is generally related to an outflow valve for an aircraft, and more particularly, to an outflow valve assembly for an aircraft having noise attenuation functionality, an aircraft including such an outflow valve assembly, and a method for assembling such an outflow valve assembly to an aircraft. BACKGROUND

[0002] Outflow valves are commonly used in aircraft to ventilate the aircraft interior, including the cockpit area and the cabin area, and to regulate cabin pressure. During flight, when air flows into the aircraft interior, for example, from an onboard pressurization system, a positive pressure is created within the aircraft interior relative to the exterior of the aircraft. Outflow valves include one or more flaps or louvers positioned in an opening formed through the fuselage of the aircraft. The louvers of the outflow valve are adjustably openable to define a flow cross-section that regulates the amount of air allowed to escape through the opening to regulate and / or maintain a desired cabin pressure level.

[0003] High velocity air flow through the outflow valve, particularly over the louvers (e.g., at approximately the speed of the aircraft), generates broadband noise. This noise is transmitted through the aircraft interior, including into the cockpit area and / or the cabin area, and can be annoying. Unfortunately, various methods for blocking the noise from reaching the cockpit and / or cabin areas along its transmission path are inefficient, costly, and / or have significantly added weight to the aircraft.

[0004] Accordingly, it would be desirable to provide an outflow valve assembly that addresses one or more of the foregoing issues, an aircraft including such an outflow valve assembly, and a method for assembling such an outflow valve assembly to an aircraft. In addition, other desirable features and characteristics of various embodiments presented herein will become apparent from the subsequent detailed description and the appended claims, taken in conjunction with the accompanying drawings and this background. SUMMARY

[0005] Various non-limiting embodiments of an outflow valve assembly for an aircraft having a fuselage at least partially surrounding an interior, an aircraft including the outflow valve assembly, and a method for assembling the outflow valve assembly to the aircraft are provided herein.

[0006] In a first non-limiting embodiment, the outflow valve assembly includes, but is not limited to, a louver configured to be movably disposed to at least partially cover an opening formed through the fuselage. The outflow valve assembly further includes, but is not limited to, a motor coupled to the louver and configured to move the louver between a closed position that prevents fluid communication through the opening and an open position that allows fluid communication between an interior of the aircraft and an exterior of the aircraft through the opening. The outflow valve further includes, but is not limited to, an acoustic panel configured to be disposed adjacent to the opening to attenuate noise generated when the louver is in the open position.

[0007] In another non-limiting embodiment, the aircraft includes, but is not limited to, a fuselage at least partially surrounding an interior and having an opening formed therethrough to provide fluid communication between the interior of the aircraft and an exterior of the aircraft. The aircraft further includes, but is not limited to, an outflow valve assembly. The outflow valve assembly includes, but is not limited to, a louver movably disposed to at least partially cover the opening. The outflow valve assembly further includes, but is not limited to, a motor operably coupled to the louver to move the louver between a closed position that prevents fluid communication through the opening and an open position that allows fluid communication between the interior of the aircraft and the exterior of the aircraft through the opening. The outflow valve assembly further includes, but is not limited to, an acoustic panel disposed adjacent to the opening to attenuate noise generated when the louver is in the open position.

[0008] In another non-limiting embodiment, the method includes, but is not limited to, movably disposing a louver to at least partially cover an opening formed through the fuselage. The method further includes, but is not limited to, coupling a motor to the louver. The motor is configured to move the louver between a closed position that prevents fluid communication through the opening and an open position that allows fluid communication between an interior of the aircraft and an exterior of the aircraft through the opening. The method further includes, but is not limited to, disposing an acoustic panel adjacent to the opening to attenuate noise generated when the louver is in the open position. BRIEF DESCRIPTION OF DRAWINGS

[0009] Various embodiments will be described in relation to the drawings in which like numerals represent similar elements and in which:

[0010] Figure 1 a perspective view of an outflow valve assembly disposed in an interior of an aircraft according to an example embodiment is shown;

[0011] Figure 2a perspective view showing an outflow valve assembly disposed in an interior of an aircraft, according to an example embodiment;

[0012] Figure 3 a perspective view showing an outflow valve assembly disposed in an interior of an aircraft, according to an example embodiment;

[0013] Figure 4 a cross-sectional side view showing an outflow valve assembly disposed in an interior of an aircraft, according to an example embodiment;

[0014] Figure 5 a cross-sectional view showing a portion of an outflow valve assembly disposed in an interior of an aircraft, according to an example embodiment; and

[0015] Figure 6 a method for assembling an outflow valve assembly to an aircraft, according to an example embodiment. DETAILED DESCRIPTION

[0016] The following detailed description is merely exemplary in nature and is not intended to limit the various embodiments or the application and uses thereof. Furthermore, there is no intention to be bound by any theory of operation described in the preceding background or the following detailed description.

[0017] Various embodiments contemplated herein relate to an outflow valve assembly for an aircraft, an aircraft including an outflow valve assembly, and a method for assembling an outflow valve assembly to an aircraft. The aircraft includes a fuselage at least partially enclosing an interior and having an opening formed therethrough to provide fluid communication between the interior of the aircraft and the exterior of the aircraft.

[0018] In example embodiments, the outflow valve assembly is disposed in the interior proximate the opening and includes an outflow valve sub-assembly and at least one acoustic panel. The outflow valve sub-assembly includes a louver disposed moveable to at least partially cover the opening. An electric motor is operably coupled to the louver to move the louver between a closed position that prevents fluid communication through the opening and an open position that allows fluid communication through the opening between the interior and the exterior of the aircraft.

[0019] The acoustic panel is disposed proximate the opening to attenuate noise generated when the louver is in the open position (e.g., noise generated when air rapidly progresses over the louver between the interior and the exterior of the aircraft). In example embodiments, noise can be efficiently and effectively attenuated by attenuating noise proximate the source of the noise to prevent or substantially prevent the noise from being transmitted to other areas of the aircraft, e.g., the cockpit area and / or the passenger cabin area.

[0020] Figures 1 to 4Various views of an outflow valve assembly 10 arranged in an interior 12 of an aircraft 14 are shown in accordance with example embodiments. The aircraft 14 includes a fuselage 16 that at least partially surrounds the interior 12 of the aircraft 14. The fuselage 16 has an opening 18 formed therethrough for providing fluid communication between the interior 12 and an exterior 20 of the aircraft 14.

[0021] As shown, the outflow valve assembly 10 is disposed in the interior 12 proximate the opening 18. In example embodiments, the outflow valve assembly 10 includes an outflow valve subassembly 22 and acoustic panels 24, 26, 28, and 30.

[0022] In example embodiments, the outflow valve subassembly 22 includes louvers 32 and 34, arms 36 and 38, and a motor 40. The louvers 32 and 34 are movably disposed in the opening 18, with each louver being movable to cover a respective portion of the opening 18. As shown, the louver 34 is in a closed position 42 to block the respective portion of the opening 18, while the louver 32 is in an open position 44 to allow fluid communication between the interior 12 and the exterior 20 of the aircraft 14 through the respective portion of the opening 18. Although the louver 32 is shown in the open position 44, while the louver 34 is shown in the closed position 42, it should be understood that the louvers 32 and 34 can be independently moved between the closed position 42 and the open position 44. When both louvers 32 and 34 are in the closed position 42, the opening 18 is completely or substantially covered, and thus blocked, to substantially prevent any fluid communication between the interior 12 and the exterior 20 of the aircraft 14 through the opening 18. Similarly, when one or more of the louvers 32 and 34 are in the open position 44, fluid communication between the interior 12 and the exterior 20 of the aircraft 14 through the opening 18 occurs, with high speed air (e.g., traveling at approximately the speed of the aircraft 14 in flight) rushing through the louver(s) 32 and / or 34, thereby generating noise.

[0023] In example embodiments, the arm 36 operably couples the motor 40 to the louver 32, while the arm 38 operably couples the louver 32 to the louver 34 to move the louvers 32 and 34, respectively, between the closed position 42 and the open position 44. As shown, the arm 36 has a proximal end 46 coupled to the motor 40 and a distal end 48 pivotably coupled to a louver bracket 50 extending upwardly from an interior-facing side 52 of the louver 32. In response to a command signal to adjust cabin pressure via opening one or more of the louvers 32 and / or 34, the motor 40 responds by driving the arm 36 to move the louver 32, which drives the arm 38 to move the louver 34 from the closed position 42 to the open position 44, or vice versa.

[0024] The sound absorbing panels 24, 26, 28, and 30 are disposed adjacent to the opening 18 to attenuate noise generated when one or more of the louvers 32 and / or 34 are in the open position 44. As shown, the sound absorbing panels 24, 26, 28, and 30 are coupled together (e.g., via metal brackets, fasteners, etc.) to form a sound absorbing wall 54 that at least surrounds (e.g., substantially or completely surrounds) a lower subassembly portion 56 that includes the louvers 32 and 34 and optionally at least a lower portion of the arm 36. Thus, the sound absorbing wall 54 substantially or completely surrounds the opening 18 and the louvers 32 and 34 to efficiently and effectively attenuate noise proximate to the noise generating source, thereby preventing or substantially preventing the noise from being transmitted to other areas of the aircraft 14 (e.g., the cockpit area and / or the passenger cabin area). To maintain pressurization through this flow, only a portion of the sound absorbing panels 24, 26, 28, and 30 can be installed adjacent to the opening 18, and the sound absorbing wall 54 can or can not completely enclose the lower assembly portion 56.

[0025] Referring to Figure 5 In example embodiments, each of the sound absorbing panels 24, 26, 28, and / or 30 includes a porous layer 58 having a porous outer surface 60 disposed adjacent to and facing the louvers 32 and 34. The porous layer 58 has pores 62 formed therethrough that allow molecular oscillations to pass through the porous layer 58. Without being limited by theory, in example embodiments, it is believed that noise is transmitted through the wave-like motion of air molecules, and by allowing these air molecules to oscillate in the porous layer 58, the noise is converted to heat energy, thereby attenuating the noise.

[0026] In example embodiments, the porous layer 58 is made of a structural material that is adapted to maintain its integrity and set in the relatively harsh environment caused by the rapid flow of air through the opening 18 over the louvers 32 and 34. For example, the porous layer 58 includes or is formed of a porous metallic material, such as a metal felt, a perforated or micro-perforated metal layer, etc. In example embodiments, the porous layer 58 includes or is formed of a metal felt.

[0027] In example embodiments, the porous layer 58 has an acoustic flow impedance of about 5 to about 50 Rayls CGS.

[0028] As shown, the sound absorption panels 24, 26, 28, and / or 30 each further include a second or intermediate layer 64 disposed adjacent the porous layer 58 opposite the porous outer surface and a third solid layer 66 disposed adjacent the intermediate layer 64 opposite the porous layer 58. As shown, the intermediate layer 64 has openings 68 in fluid communication with the pores 62. Without being limited by theory, in example embodiments, it is believed that noise passing through the pores 62 passes through the openings 68 to the solid layer 66, is reflected by the solid layer 66, and passes back through the openings 68 to the porous layer 58 for further attenuation.

[0029] In example embodiments, the intermediate layer 64 is or includes a honeycomb structure 70, where each opening 68 in the honeycomb structure 70 has a diameter or maximum cross-sectional dimension of about 0.125 to about 1.5 inches. In example embodiments, the honeycomb structure 70 is formed of a structural material such as a metallic material (e.g., a metallic honeycomb structure), a composite material such as a Nomex honeycomb product, or the like. In another example embodiment, the intermediate layer 64 is completely or partially filled with a porous fiber or foam material.

[0030] In example embodiments, the solid layer 66 is formed of a non-porous solid structural material such as a fiber reinforced composite material, a metallic material, or the like. In example embodiments, the sound absorption panels 24, 26, 28, and / or 30 each have a total thickness (indicated by double-headed arrow 72) of from about 0.25 inches to about 10 inches, such as a total thickness 72 of from about 0.5 inches to about 6 inches.

[0031] Referring to Figure 1 , Figure 2 and Figure 5 In example embodiments, one or more of the sound absorption panels 24, 26, 28, and / or 30 are inwardly inclined toward the outflow valve subassembly 22 in a direction (upwardly) from the lower subassembly portion 56 toward the motor 40. In example embodiments, one or more of the sound absorption panels 24, 26, 28, and / or 30 are inwardly inclined at an angle 74 of from about 45° to about 85°.

[0032] Figure 6 A method 100 for assembling an outflow valve assembly to an aircraft in accordance with example embodiments is shown. The method 100 includes movably disposing (step 102) louvers to at least partially cover an opening formed through a fuselage.

[0033] A motor is coupled to the louvers (step 104). The motor is configured to move the louvers between a closed position that prevents fluid communication through the opening and an open position that allows fluid communication between the interior and exterior of the aircraft through the opening. A sound baffle is disposed adjacent the opening (step 106) to attenuate noise generated when the louvers are in the open position.

[0034] While at least one example embodiment has been presented in the foregoing detailed description of the disclosure, it should be appreciated that a vast number of variations exist. It should also be appreciated that the example embodiment or embodiments are only examples and are not intended to limit the scope, applicability, or configuration of the disclosure in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing an example embodiment of the disclosure. It should be understood that various changes can be made in the function and arrangement of elements described in the example embodiment without departing from the scope of the disclosure as set forth in the appended claims.

Claims

1. An outflow valve assembly for an aircraft having a fuselage at least partially surrounding its interior, the outflow valve assembly comprising: The blinds are configured to be movable to at least partially cover the opening formed through the body; An electric motor is connected to the louvers and configured to move the louvers between a closed position and an open position, the closed position preventing fluid communication through the opening and the open position allowing fluid communication between the interior and exterior of the aircraft through the opening; as well as Multiple sound-absorbing panels are configured adjacent to the opening to reduce noise generated when the louvers are in the open position, wherein the multiple sound-absorbing panels are connected together to form a sound-absorbing wall that at least surrounds the lower sub-assembly portion of the outflow valve assembly, including the louvers.

2. The outflow valve assembly according to claim 1, wherein, The sound-absorbing panel includes a first porous layer having a porous outer surface configured adjacent to the louvers, and the first porous layer having pores formed therethrough, the pores allowing molecular oscillations to pass through the first porous layer.

3. The outflow valve assembly according to claim 2, wherein, The first porous layer includes one of a metal felt and a perforated or micro-perforated metal layer.

4. The outflow valve assembly according to claim 2, wherein, The first porous layer has an acoustic-current impedance of 5 to 50 Rayleigh CGS.

5. The outflow valve assembly according to claim 2, wherein, The sound-absorbing panel includes a second layer, which is disposed adjacent to the first porous layer and opposite to the outer surface of the porous layer, and has an opening that is in fluid communication with the pores.

6. The outflow valve assembly according to claim 5, wherein, The second layer is completely or partially filled with porous fiber or foam material.

7. The outflow valve assembly according to claim 5, wherein, The second layer includes a honeycomb structure.

8. The outflow valve assembly according to claim 5, wherein, Each of the openings has a maximum cross-sectional dimension of 0.125 to 1.5 inches.

9. The outflow valve assembly according to claim 5, wherein, The sound-absorbing panel includes a third solid layer, which is disposed adjacent to the second layer and opposite to the first porous layer.

10. The outflow valve assembly according to claim 9, wherein, The third solid layer comprises one of fiber-reinforced composite material and metal material, and forms a rainproof layer for the outflow valve assembly.

11. The outflow valve assembly according to claim 1, wherein, The sound-absorbing panels have a total thickness of 0.25 to 10 inches.

12. An aircraft comprising: The fuselage, which at least partially surrounds the interior and has openings formed therethrough, provides fluid communication between the interior and exterior of the aircraft; as well as The outflow valve assembly includes: A louver, which is configured to be movable to at least partially cover the opening; A motor operably coupled to the louvers to move the louvers between a closed position and an open position, the closed position preventing fluid communication through the opening, and the open position allowing fluid communication between the interior and exterior of the aircraft through the opening; and Multiple sound-absorbing panels are arranged adjacent to the opening to reduce noise generated when the louvers are in the open position, wherein the multiple sound-absorbing panels are connected together to form a sound-absorbing wall that at least surrounds the lower sub-assembly portion of the outflow valve assembly, including the louvers.

13. The aircraft of claim 12, further comprising an arm having a first end connected to the louver and a second end connected to the motor, wherein, The motor is configured to drive the arm to move the louvers between the closed position and the open position.

14. The aircraft according to claim 13, wherein, The motor, the arm, and the louver form at least a portion of an outflow valve subassembly, wherein the outflow valve subassembly extends from the lower subassembly portion including the louver to the upper subassembly portion including the motor.

15. The aircraft according to claim 14, wherein, The sound-absorbing plate is inclined inward toward the outflow valve subassembly in the direction from the lower subassembly to the upper subassembly.

16. The aircraft according to claim 15, wherein, The sound-absorbing panel is tilted inward at an angle ranging from 45° to 85°.

17. The aircraft according to claim 14, wherein, The outflow valve subassembly further includes: at least one additional louver configured to be movable to at least partially cover the opening; and at least one additional arm that directly or indirectly connects the at least one additional louver to the motor to move the at least one additional louver between the closed position and the open position.

18. The aircraft according to claim 14, wherein, Each of the sound-absorbing panels of the sound-absorbing wall includes a first porous layer, the first porous layer having a porous outer surface at least facing the lower sub-assembly portion of the outflow valve sub-assembly, and the first porous layer having pores formed therethrough, the pores allowing molecular oscillations to pass through the first porous layer.

19. The aircraft according to claim 18, wherein, Each of the sound-absorbing panels in the sound-absorbing wall further includes: The second layer, which is disposed adjacent to the first porous layer and opposite to the outer surface of the porous structure, and has an opening in fluid communication with the pores; and A third solid layer is disposed adjacent to the second layer and opposite to the first porous layer.

20. A method for assembling an outflow valve assembly into an aircraft having a fuselage at least partially surrounding its interior, the method comprising the steps of: The louvers are movably configured to at least partially cover the opening formed through the fuselage; A motor is connected to the louvers, wherein the motor is configured to move the louvers between a closed position and an open position, the closed position preventing fluid communication through the opening, and the open position allowing fluid communication between the interior and exterior of the aircraft through the opening; and Multiple sound-absorbing panels are disposed adjacent to the opening to reduce noise generated when the louvers are in the open position, wherein the multiple sound-absorbing panels are connected together to form a sound-absorbing wall, the sound-absorbing wall at least surrounding the lower sub-assembly portion of the outflow valve assembly including the louvers.

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