Noise reduction and exhaust device of aero-engine
By designing an aircraft engine noise reduction exhaust device that includes a reflection cavity and a silencing cavity, noise is eliminated by multiple reflections, thus resolving the contradiction between the weight and noise reduction effect of existing noise reduction devices and achieving a combination of lightweight and efficient noise reduction.
Patent Information
- Application Number
- CN202520149530.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-21
- Publication Date
- 2025-12-16
- Estimated Expiration
- 2035-01-21
AI Technical Summary
Existing aircraft engine exhaust systems have increased weight in pursuit of noise reduction capabilities, making it difficult to design lightweight aircraft, while lightweight devices cannot effectively reduce noise.
An aircraft engine noise reduction and exhaust device was designed, comprising a noise reduction package, a reflection cavity, and a noise reduction chamber. Through the connection of the intake pipe and the exhaust pipe, exhaust gas and noise are reflected multiple times in the reflection cavity, and the peaks and troughs of the sound waves coincide to cancel out the noise.
It significantly reduces noise while ensuring exhaust performance, has a simple structure and is lightweight, and achieves a good sound reduction effect.
Smart Images
Figure CN223676361U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to an unmanned aerial vehicle aeroengine technical field, concretely relates to an aeroengine silencing exhaust device. BACKGROUND
[0002] At present, aeroengine exhausts are various, but all have some deficiencies. The silencing capacity and weight are important indexes of aeroengine exhausts, and the noisy aeroengine sound is not conducive to the concealment of the aircraft and will make the user often in a noisy environment.
[0003] The current aeroengine exhaust device pursues good silencing capacity, adopts a complicated internal structure, greatly increases the weight of the aeroengine exhaust device, and is not conducive to the lightweight design of the aircraft. On the contrary, the light-weight aeroengine exhaust device cannot effectively reduce the noise generated by the aeroengine. SUMMARY
[0004] The utility model discloses an aeroengine silencing exhaust device to solve the above technical problems existing in the prior art, and the preferred technical solutions in the plurality of technical solutions provided by the utility model can produce a plurality of technical effects. Details are described below.
[0005] To achieve the above object, the utility model provides the following technical scheme:
[0006] The utility model provides an aeroengine silencing exhaust device, which comprises a silencing package, an air inlet pipe and an exhaust pipe, wherein: a reflection cavity and a silencing cavity that are connected in communication are arranged in the silencing package, the air inlet end of the air inlet pipe is connected to an aeroengine, the air outlet end of the air inlet pipe is inserted into the reflection cavity, and the air inlet end of the exhaust pipe is inserted into the silencing cavity.
[0007] Preferably, the silencing package comprises a package body and an end cover arranged at the end of the package body, and the air outlet end of the air inlet pipe is provided with a first notch on one side of the end cover.
[0008] Preferably, the air inlet pipe is arranged at a position close to the end cover, the air outlet end of the air inlet pipe is inserted into the package body through the first side of the package body, and the air outlet end of the air inlet pipe is arranged at a position close to the second side of the package body.
[0009] Preferably, the end cover is arranged as an arc-shaped end cover, and the arc-shaped end cover protrudes outward.
[0010] Preferably, the air inlet end of the exhaust pipe is provided with a second notch on one side close to the end cover.
[0011] Preferably, the exhaust pipe is arranged near the middle of the package body; the air inlet end of the exhaust pipe is inserted into the package body through the second side of the package body, and the air inlet end of the exhaust pipe is arranged near the position close to the first side of the package body.
[0012] Preferably, the exhaust pipe is arranged on the section inside the sound attenuation cavity and is provided with a plurality of communication holes.
[0013] Preferably, a partition plate is arranged in the package body, the partition plate divides the inner cavity of the package body into the reflection cavity and the sound attenuation cavity; a throat pipe is arranged on the partition plate, the throat pipe is located in the reflection cavity and is connected with the reflection cavity and the sound attenuation cavity at two ends respectively, and the throat pipe is arranged away from the first notch.
[0014] Preferably, end covers are arranged at two ends of the package body, two partition plates are symmetrically arranged in the package body, the sound attenuation cavity is formed between the two partition plates, the reflection cavities are formed between the partition plates and the corresponding end covers; the number of the air inlet pipes is two; and the number of the exhaust pipes is two.
[0015] Preferably, the air inlet end of the air inlet pipe is provided with a mounting seat for connecting the aero-engine.
[0016] The aero-engine sound attenuation exhaust device provided by the utility model has at least the following beneficial effects:
[0017] The aero-engine sound attenuation exhaust device comprises a sound attenuation package, air inlet pipes and an exhaust pipe, the sound attenuation package has a sound attenuation effect, can reduce the noise during the exhaust of the aero-engine, the air inlet pipes are used for guiding the exhaust gas discharged by the aero-engine to the sound attenuation package, and the exhaust pipe is used for exhausting.
[0018] The sound attenuation package is provided with a reflection cavity and a sound attenuation cavity connected with each other, the air inlet end of the air inlet pipe is connected with the aero-engine, the air outlet end of the air inlet pipe is inserted into the reflection cavity, the air inlet end of the exhaust pipe is inserted into the sound attenuation cavity, during use, the exhaust gas and the noise generated by the aero-engine enter into the reflection cavity through the air inlet pipe and are reflected for multiple times, then enter into the sound attenuation cavity, and are exhausted by the exhaust pipe, during the reflection of the exhaust gas and the noise in the reflection cavity, most of the wave crests and the wave troughs of the sound waves generated by the aero-engine are coincident, thereby most of the noise is cancelled.
[0019] On the basis of guaranteeing the exhaust effect of the aero-engine, the utility model reflects the exhaust gas and the noise for multiple times through the reflection cavity, most of the wave crests and the wave troughs of the sound waves generated by the aero-engine are coincident, thereby the noise is effectively cancelled, the sound attenuation effect is remarkable, the structure is simple, and the quality is light and convenient. BRIEF DESCRIPTION OF DRAWINGS
[0020] In order to more clearly illustrate the technical solutions of the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiment or prior art description. Obviously, the drawings described below are only some of the embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor on the basis of these drawings.
[0021] Figure 1 is a structural schematic view of another view of the present application;
[0022] Figure 2 is a structural schematic view of another view of the present application;
[0023] Figure 3 is a front view schematic view of the present application;
[0024] Figure 4 is a side view schematic view of the present application;
[0025] Figure 5 is a top view schematic view of the present application;
[0026] Figure 6 is a sectional view schematic view of the present application;
[0027] Figure 7 is an exploded schematic view of the present application.
[0028] Reference signs
[0029] 1, sound attenuation package; 11, package body; 12, end cover; 13, partition; 14, throat pipe; 15, reflection cavity; 16, sound attenuation cavity; 2, air inlet pipe; 21, first notch; 3, air outlet pipe; 31, communication hole; 32, second notch; 4, mounting seat. DETAILED DESCRIPTION
[0030] In order to make the purpose, technical scheme and advantages of the present application more clear, the technical scheme of the present application will be described in detail below. Obviously, the described embodiments are only some of the embodiments of the present application, not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of the present application.
[0031] Embodiment 1:
[0032] The present application provides an aero-engine sound attenuation exhaust device, referring to Figures 1 to 7 The aero-engine sound attenuation exhaust device includes a sound attenuation package 1, an air inlet pipe 2 and an air outlet pipe 3.
[0033] The muffler 1 is provided with a reflector 15 and a muffler 16, which are connected. The intake end of the intake pipe 2 is connected to the aircraft engine. The exhaust end of the intake pipe 2 passes through the wall of the muffler 1 and is inserted into the reflector 15. The intake end of the exhaust pipe 3 passes through the wall of the muffler 1 and is inserted into the muffler 16. The exhaust end of the exhaust pipe 3 is located outside the muffler 1.
[0034] During exhaust, the exhaust gas and noise generated by the aircraft engine enter the reflector cavity 15 through the intake pipe 2, then pass through the muffler cavity 16, and are discharged through the exhaust pipe 3.
[0035] During the process of the exhaust gas and noise passing through the reflection cavity 15, the exhaust gas and noise are reflected multiple times in the reflection cavity 15, so that most of the peaks and troughs of the sound waves generated by the aero-engine coincide, thereby canceling out most of the noise and achieving the purpose of noise reduction.
[0036] While ensuring the exhaust effect of the aircraft engine, this utility model can effectively cancel noise by reflecting the exhaust gas and noise multiple times through the reflector cavity 15. It not only has a significant noise reduction effect, but also has a simple structure and is lightweight.
[0037] Example 2:
[0038] Example 2 is based on Example 1:
[0039] like Figures 1 to 7 As shown, the silencer 1 includes a body 11 and an end cap 12. The body 11 is horizontally arranged and adopts a cylindrical structure that runs through the axis. The end cap 12 is connected to the end of the body 11. The air outlet of the air inlet pipe 2 is provided with a first slot 21 on the side facing the end cap 12.
[0040] During the exhaust process, exhaust gas and noise enter through the first slot 21 and are directed towards the end cover 12, where they are reflected upon contact with the end cover 12.
[0041] Orienting the first slot 21 toward the end cap 12 can effectively ensure the reflection of noise.
[0042] As an optional implementation, the intake pipe 2 is positioned close to the end cover 12; thus, the distance between the first slot 21 and the end cover 12 is small, and exhaust gas and noise can be reflected after entering.
[0043] The air outlet of the air inlet pipe 2 is inserted into the housing 11 through the first side of the housing 11, and the air outlet of the air inlet pipe 2 is located near the second side of the housing 11; in this way, the reflection cavity 15 can be fully utilized, the number of reflections can be extended, and the noise reduction effect can be further improved.
[0044] As an optional implementation, the end cover 12 is provided as an arc-shaped end cover 12 which is outwardly convex, i.e., the inner end surface of the arc-shaped end cover 12 is concave. After the exhaust gas and the noise contact the arc-shaped end cover 12, the exhaust gas and the noise are scattered, and the noise reduction effect is obvious.
[0045] As an optional implementation, the second notch 32 is arranged on the side of the air inlet end of the exhaust pipe 3 which is close to the end cover 12. In the process of exhaust, the exhaust gas in the noise reduction cavity 16 enters the exhaust pipe 3 through the second notch 32 and is discharged by the exhaust pipe 3.
[0046] As an optional implementation, the exhaust pipe 3 is arranged at a position close to the middle of the package body 11. The air inlet end of the exhaust pipe 3 is inserted into the package body 11 through the second side of the package body 11, and the air inlet end of the exhaust pipe 3 is close to the position arranged close to the first side of the package body 11. The second notch 32 is close to the inner package wall of the package body 11.
[0047] Optionally, the second notch 32 is arranged on only one side of the air inlet end of the exhaust pipe 3.
[0048] Further optionally, the second notch 32 is arranged on both sides of the air inlet end of the exhaust pipe 3, i.e., the second notch 32 penetrates the pipe wall of the exhaust pipe 3 in the radial direction.
[0049] As an optional implementation, a plurality of communication holes 31 are arranged on the section of the exhaust pipe 3 inside the noise reduction cavity 16.
[0050] In the process of exhaust, the exhaust gas enters the exhaust pipe 3 through the second notch 32. Due to the fast flow rate of the exhaust gas inside the exhaust pipe 3, according to Bernoulli's principle, the exhaust gas is sucked into the exhaust pipe 3 through the communication hole 31. On the one hand, the exhaust capacity is increased, and the exhaust efficiency is improved. On the other hand, according to the above-mentioned sound wave cancellation principle, the noise generated by the aero-engine is further reduced.
[0051] As an optional implementation, a partition plate 13 is arranged in the package body 11. The partition plate 13 divides the inner cavity of the package body 11 into a reflection cavity 15 and a noise reduction cavity 16. In the process of exhaust, the partition plate 13 cooperates with the end cover 12 to realize the reflection of the exhaust gas and the noise.
[0052] The partition plate 13 is provided with a throat pipe 14. The throat pipe 14 is located in the reflection cavity 15 and is in communication with the reflection cavity 15 and the noise reduction cavity 16 at both ends. The throat pipe 14 is arranged at a position away from the first notch 21. In this way, the reflection times of the noise in the reflection cavity 15 are further increased, and the reflection noise reduction is fully realized.
[0053] As an optional implementation, the package body 11 is provided with the end cover 12 at both ends. The package body 11 is symmetrically provided with two partition plates 13. The two partition plates 13 form the noise reduction cavity 16 therebetween, and the partition plate 13 and the corresponding end cover 12 form the reflection cavity 15 therebetween.
[0054] In this way, two reflection cavities 15 are formed, wherein the sound attenuation cavity 16 is located in the middle position, and the two reflection cavities 15 are symmetrically distributed on both sides of the sound attenuation cavity 16.
[0055] The number of the air inlet pipes 2 is set to two, and the two air inlet pipes 2 are respectively connected with the two reflection cavities 15.
[0056] The number of the air outlet pipes 3 is set to two, and the two air outlet pipes 3 are symmetrically arranged.
[0057] As an optional embodiment, the air inlet end of the air inlet pipe 2 is provided with a mounting seat 4, and the mounting seat 4 is used for connecting the aero-engine.
[0058] In the description of the present application, it should be understood that the terms "upper", "lower", "inner", "outer", "top", "bottom" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.
[0059] In addition, the terms "first", "second" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features defined as "first", "second" can explicitly or implicitly include at least one of the features. In the description of the present application, the meaning of "a plurality of", "several" is at least two, for example, two, three, etc., unless otherwise explicitly specified.
[0060] In the present application, unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting", "fixing" and the like should be understood in a broad sense, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise explicitly limited. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.
[0061] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto, and any skilled person in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.
Claims
1. A silencer exhaust device for an aircraft engine, characterized in that, Includes a muffler, intake manifold, and exhaust manifold, among which: The silencer is provided with a resonant cavity and a silencer cavity that are connected to each other. The air intake end of the air intake pipe is connected to the aircraft engine, the air outlet end of the air intake pipe is inserted into the resonant cavity, and the air intake end of the exhaust pipe is inserted into the silencer cavity. The sound-absorbing bag includes a bag body and an end cap disposed at the end of the bag body. The air inlet pipe has a first slot on the side facing the end cap. The air inlet pipe is disposed near the end cap. The air inlet pipe is inserted into the bag body through a first side of the bag body, and the air inlet pipe is disposed near a second side of the bag body. The exhaust pipe has a second slot on the side near the end cap at its air inlet end; the exhaust pipe is positioned near the middle of the bag body; the air inlet end of the exhaust pipe is inserted into the bag body via the second side of the bag body, and the air inlet end of the exhaust pipe is positioned near the first side of the bag body; multiple connecting holes are provided on the section of the exhaust pipe inside the silencing cavity; a partition is provided inside the bag body, which divides the inner cavity of the bag body into the reflection cavity and the silencing cavity; a throat is provided on the partition, which is located inside the reflection cavity and its two ends are respectively connected to the reflection cavity and the silencing cavity, and the throat is positioned away from the first slot; end caps are provided at both ends of the bag body; two partitions are symmetrically arranged inside the bag body, forming the silencing cavity between the two partitions, and forming the reflection cavity between the partition and the corresponding end cap; the number of air inlets is set to two; the number of exhaust pipes is set to two.
2. The aircraft engine muffler exhaust device according to claim 1, characterized in that, The end cap is configured as an arc-shaped end cap; The arc-shaped end cap protrudes outward.
3. The aircraft engine muffler exhaust device according to claim 1, characterized in that, The air intake end of the air intake pipe is provided with a mounting bracket for connecting the aircraft engine.