Low-pressure buffering cavity of air conditioning system of airplane passenger cabin

Abstract

The utility model discloses a low-pressure buffer cavity of an air conditioning system of an airplane passenger cabin, which particularly relates to the field of airplane ventilation structures and comprises a shell sleeve, a buffer space is arranged in the shell sleeve, and airflow in the buffer space is conveyed to the cabin; the gas buffering assembly comprises an upper buffering layer, a lower buffering layer and a buffering partition piece, the buffering partition piece divides the buffering space in the shell sleeve into the upper buffering layer and the lower buffering layer which are arranged up and down, and a plurality of air guiding openings are formed in the buffering partition piece; the air inlet pipe assembly is used for guiding airflow generated by the air conditioner host to the buffer space; wherein the density degree of the air guide openings is in negative correlation with the distance between the air guide openings and the air inlet pipe assembly, the smaller the distance is, the larger the number of the air guide openings in the unit area is, airflow and sound field distribution is optimized through the trapezoidal geometric structure, the noise reduction performance is improved, meanwhile, airflow pressure loss can be relieved, and two purposes are achieved.

Description

TECHNICAL FIELD

[0001] The utility model relates to an airplane ventilation structure field more specifically, the utility model relates to a kind of airplane cabin air conditioning system low-pressure buffer cavity. BACKGROUND

[0002] The existing airplane air conditioning system usually adopts centralized air supply design, airflow is directly blown into cabin through top or side wall vent, but lacks effective dynamic buffering mechanism. Due to the long and narrow cabin space and dense seat layout, high-speed airflow is easy to form turbulent flow in local area, resulting in significant temperature difference between front and rear cabins and between aisle and window area. In addition, when the air supply speed is too large, airflow will periodically separate from luggage rack edge, personal ventilation nozzle and other structures, inducing broadband vortex noise and generating noise. SUMMARY

[0003] To overcome the above-mentioned defects of the prior art, the embodiments of the utility model provide a kind of airplane cabin air conditioning system low-pressure buffer cavity, and the technical problems to be solved by the utility model are: how to reasonably output airflow while reducing noise.

[0004] To achieve the above-mentioned purpose, the utility model provides the following technical scheme: a kind of airplane cabin air conditioning system low-pressure buffer cavity, including shell, built-in buffer space, for the airflow in buffer space is exported to cabin;Gas buffer assembly, including upper buffer layer, lower buffer layer and buffer partition, buffer partition divides the buffer space in shell into upper and lower arranged upper buffer layer and lower buffer layer, buffer partition is equipped with a plurality of air outlets;Air inlet pipe assembly is used to guide the airflow generated by air conditioning host to buffer space;Wherein, the density of air outlet is negatively correlated with the distance of air outlet and air inlet pipe assembly, the smaller the distance, the more the number of air outlet per unit area is set.

[0005] In a preferred embodiment, the buffer partition includes a frame partition and a fan leaf, the frame partition is connected in the shell, a plurality of air outlets are arranged along the extension direction of the frame partition on the frame partition, and the fan leaf is connected at the air outlet.

[0006] In a preferred embodiment, each fan leaf abuts against the side edge of the corresponding air outlet, and the number of air outlets is greater than the number of fan leaves.

[0007] In a preferred embodiment, the upper buffer layer and the lower buffer layer together form a trapezoid.

[0008] In a preferred embodiment, the shell includes a front shell body, a rear shell body and a shell bottom plate, the front shell body and the rear shell body are detachably connected with the airplane cabin, the space formed by the front shell body and the rear shell body is the buffer space, and the upper and lower positions of the buffer space are connected with the air inlet pipe assembly and the shell bottom plate respectively.

[0009] In a preferred embodiment, a heat insulation layer is connected inside the front housing.

[0010] In a preferred embodiment, the bottom plate of the shell is covered with a condensate adsorption layer.

[0011] In a preferred embodiment, the air inlet duct assembly includes a duct and a duct insulation sleeve. The two ends of the duct are respectively connected to a buffer space and the output port of the air conditioning unit, and the duct insulation sleeve is wrapped around the outside of the duct.

[0012] The technical effects and advantages of this utility model are as follows:

[0013] 1. This utility model is designed with a three-level distributed airflow buffer zone, which can buffer the airflow of the air conditioning in the aircraft cabin, ensure that the airflow is evenly distributed in the cabin, and avoid the problem of uneven heating and cooling in some areas of the cabin.

[0014] 2. This utility model is designed with a three-level distributed airflow buffer zone, which can reduce the noise caused by uneven airflow impact during the operation of the aircraft air conditioning system and effectively improve the comfort of the aircraft cabin environment. Attached Figure Description

[0015] The accompanying drawings are provided to further understand the technical solution of this utility model and constitute a part of this utility model. The embodiments of this utility model and their descriptions are used to explain this utility model and do not constitute an improper limitation of this utility model.

[0016] Figure 1 This is an exploded view of the buffer cavity component of this utility model.

[0017] Figure 2 This is a side view of the buffer cavity of this utility model.

[0018] Figure 3 This is a structural diagram of the buffer partition in this utility model.

[0019] Figure 4 This is a schematic diagram showing the positions of the upper and lower buffer layers in this utility model.

[0020] Figure 5 for Figure 4 A magnified view of A in the middle.

[0021] The attached figures are labeled as follows: 10, shell; 11, front shell; 12, rear shell; 13, shell bottom plate; 14, plate insulation layer; 15, condensate adsorption layer; 20, gas buffer assembly; 21, upper buffer layer; 22, lower buffer layer; 23, buffer partition; 231, frame partition; 232, fan blade; 30, air inlet duct assembly; 31, duct; 32, duct insulation sleeve. Detailed Implementation

[0022] Exemplary embodiments will now be described more fully with reference to the accompanying drawings. However, these exemplary embodiments can be implemented in many forms and should not be construed as limited to the examples set forth herein; rather, they are provided so that the description of this disclosure will be more complete and fully convey the concept of the exemplary embodiments to those skilled in the art. The drawings are merely illustrative of this disclosure and are not necessarily drawn to scale. The same reference numerals in the drawings denote the same or similar parts, and therefore repeated descriptions of them will be omitted.

[0023] Example

[0024] like Figures 1-5 This utility model provides a low-pressure buffer chamber for an aircraft cabin air conditioning system, which mainly includes a shell 10, a gas buffer assembly 20, and an air inlet duct assembly 30.

[0025] The casing 10 is the main structure, including a front casing 11, a rear casing 12, a bottom casing plate 13, a thermal insulation layer 14, and a condensate absorption layer 15. The front casing 11 and the rear casing 12 are detachably connected by threaded fasteners, and the rear casing 12 is connected to the side wall of the engine compartment. A buffer space is formed inside the front casing 11 and the rear casing 12. The top and bottom of the front casing 11 and the rear casing 12 are respectively connected to the air inlet duct assembly 30 and the bottom casing plate 13. The bottom casing plate 13 has small round holes for air dissipation. The cold / warm air generated in the air conditioning unit is output to the engine compartment after passing through the air inlet duct assembly 30, the buffer space, and the bottom casing plate 13.

[0026] Preferably, a heat insulation layer 14 is connected inside the front shell 11 for heat preservation. The heat preservation material is common and will not be described in detail in this embodiment.

[0027] Preferably, a condensate adsorption layer 15 is coated on the inner surface of the shell bottom plate 13 to remove water vapor from the gas sent to the cabin. The material of the condensate adsorption layer 15 is also quite common, and will not be described in detail in this embodiment.

[0028] The gas buffer assembly 20 is designed to effectively reduce vibration and noise caused by strong air supply. It includes an upper buffer layer 21, a lower buffer layer 22, and a buffer partition 23. The upper buffer layer 21 and the lower buffer layer 22 are located in the upper and lower layers of the buffer space, respectively. The air supplied to the buffer space by the air inlet duct assembly 30 passes through the upper buffer layer 21 and the lower buffer layer 22 before being output from the bottom plate 13 of the shell.

[0029] The above design rationally divides the buffer space into three levels of buffer zones: an upper buffer layer 21, a lower buffer layer 22, and a bottom shell plate 13 for outward air exhaust. The upper buffer layer 21 reduces the impact of strong airflow; the lower buffer layer is equipped with fan blades 232 to evenly distribute the airflow from the upper buffer layer 21 to the lower buffer layer 22, further buffering the airflow; the bottom shell plate 13 has circular holes to ensure even airflow delivery into the cabin, and a condensate absorption layer 15 is designed to absorb condensate droplets on the bottom shell plate 13, ensuring a comfortable humidity level inside the cabin. This three-level buffer zone design effectively reduces noise generated by uneven impact of strong airflow during aircraft air conditioning system operation.

[0030] Preferably, the upper buffer layer 21 and the lower buffer layer 22 together form a trapezoidal structure, with the upper buffer layer 21 located at the short apex of the trapezoid. This design optimizes airflow and sound field distribution through the trapezoidal geometry. The upper half of the structure can mitigate the impact energy of high-speed airflow, while the lower half guides the orderly diffusion of airflow. Combined with the fan blades, it forms a guiding field, effectively decomposing the vortex structure generated by noise and matching the reflection paths of sound waves of different frequencies through continuously varying chamber impedance. This design improves noise reduction performance while also mitigating airflow pressure loss, achieving two goals at once.

[0031] The upper buffer layer 21 and the lower buffer layer 22 are separated by a buffer partition 23. The buffer partition 23 includes a frame partition 231 and a fan blade 232. The frame partition 231 is connected to the front housing 11 and the rear housing 12, and the fan blade 232 is connected to the frame partition 231 to form a guide surface that guides the airflow into the lower buffer layer 22.

[0032] Preferably, the fan blade 232 and the frame partition 231 are fixedly connected. The more stable connection allows the fan blade 232 to continuously and stably guide the wind force into the buffer layer 22.

[0033] Preferably, there are four fan blades 232, and their angles with the frame partition 231 are 75.02°, 90°, 94°, and 90°, respectively.

[0034] Preferably, the air inlet duct assembly 30 is arranged diagonally above the housing 10. The density of the fan blades 232 is negatively correlated with the distance from the fan blades 232 to the air inlet duct assembly 30; the closer to the air inlet duct assembly 30, the denser the arrangement of the fan blades 232. This allows for more effective separation of strong airflow. The airflow input from the air inlet duct assembly 30 into the upper buffer layer 21 will first flow downwards and be separated by the dense fan blades 232. In the space of the upper buffer layer 21, which is far from the air inlet duct assembly 30, the air pressure is lower, so a less dense arrangement can be used, effectively saving costs.

[0035] Preferably, the distance between the fan blade 232 and the frame partition 231 can be adjusted according to the designer's usage requirements, and they do not need to be placed vertically.

[0036] Preferably, the frame partition 231 has several air vents. The airflow of the upper buffer layer 21 enters the lower buffer layer 22 through the air vents. The number of air vents is greater than the number of fan blades 232, but each fan blade 232 is designed to be close to a corresponding air vent.

[0037] The distance from the air vent to one side of the frame partition 231 can also be designed as: 7.3; 64.3; 107.3; 141.3; 180.3; 286.3; 321.3; 366.3; 411.3; 501.3; 571.3; 636.3; 681.3, all in mm.

[0038] The installation sequence for this product is as follows:

[0039] S1: Install pipe 31. Apply adhesive to the contact area between pipe 31 and the groove on the left side of the front housing 11, and install pipe 31 onto the front housing 11 using an adhesive bonding process.

[0040] S2: Install pipe insulation sleeve 32. Apply adhesive to the contact area between pipe insulation sleeve 32 and pipe 31, and install pipe insulation sleeve 32 onto pipe 31 using an adhesive bonding process.

[0041] S3: Install the frame partition 231 and fan blade 232. Align the positioning holes of the frame partition 231 with the mounting positioning holes of the front housing 11. Apply adhesive to the contact surface area between the frame partition 231 and the front housing 11, and fix them using adhesive. Then, use adhesive to install and fix the fan blade 232 to the front housing 11. First, apply adhesive to the mounting slot of the fan blade 232 on the front housing 11, and then simultaneously snap the fan blade 232 into the mounting slots of both the frame partition 231 and the front housing 11.

[0042] S4: Install the condensate adsorption layer 15. The condensate adsorption layer 15 is fixed to the rear housing 12 using an adhesive process.

[0043] S5: Install the plate insulation layer 14 and the rear shell 12. Fix the rear shell 12 and the plate insulation layer 14 to the front shell 11 using an adhesive process.

[0044] S6: Install the bottom shell plate 13. First, apply adhesive to the bonding area of ​​the bottom shell plate 13. Then, install the bottom shell plate 13 at the bottom of the front shell 11 and the rear shell 12 along the installation direction to form a buffer space.

[0045] The above assembly process uses adhesive bonding for installation, and the process is simple and convenient.

[0046] Working principle of this utility model:

[0047] This invention optimizes airflow and sound field distribution through a trapezoidal geometric structure. The upper layer mitigates the impact energy of high-speed airflow, while the lower layer guides the orderly diffusion of airflow. Combined with fan blades, this forms a guiding field, effectively decomposing the vortex structure generated by noise and matching the reflection paths of sound waves at different frequencies through continuously varying chamber impedance. This design improves noise reduction performance while also mitigating airflow pressure loss, achieving two goals at once.

[0048] The foregoing description only illustrates certain exemplary embodiments of the present invention. Undoubtedly, those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. A low-pressure buffer chamber for an aircraft cabin air conditioning system, characterized in that, include: Shell (10), with built-in buffer space, used to transport airflow in the buffer space to the cabin; The gas buffer assembly (20) includes an upper buffer layer (21), a buffer partition (23) and a lower buffer layer (22) arranged sequentially on the gas flow path. The buffer partition (23) divides the buffer space inside the shell (10) into an upper buffer layer (21) and a lower buffer layer (22) arranged vertically. The buffer partition (23) is provided with several air guides. Air inlet duct assembly (30) is used to guide the airflow generated by the air conditioning unit to the buffer space; The density of the air vents is negatively correlated with the distance between the air vents and the air inlet duct assembly (30). The smaller the distance, the more air vents are set per unit area.

2. The low-pressure buffer chamber of an aircraft cabin air conditioning system according to claim 1, characterized in that, The buffer partition (23) includes a frame partition (231) and a fan blade (232). The frame partition (231) is connected to the shell (10). The frame partition (231) has several air guides arranged along the extension direction of the frame partition (231), and the air guides are connected to the fan blades (232).

3. The low-pressure buffer chamber of an aircraft cabin air conditioning system according to claim 2, characterized in that, Each of the fan blades (232) is attached to the side of the corresponding air guide, and the number of air guides is greater than the number of fan blades (232).

4. The low-pressure buffer chamber of an aircraft cabin air conditioning system according to claim 1, characterized in that, The upper buffer layer (21) and the lower buffer layer (22) together form a trapezoid.

5. The low-pressure buffer chamber of an aircraft cabin air conditioning system according to claim 1, characterized in that, The shell (10) includes a front shell (11), a rear shell (12) and a bottom plate (13). The front shell (11) and the rear shell (12) are detachably connected to the aircraft cabin. The space formed by the front shell (11) and the rear shell (12) is a buffer space. The upper and lower positions of the buffer space are respectively connected to the air inlet pipe assembly (30) and the bottom plate (13). The bottom plate (13) has several round holes.

6. The low-pressure buffer chamber of an aircraft cabin air conditioning system according to claim 5, characterized in that, A heat insulation layer (14) is connected inside the front shell (11).

7. The low-pressure buffer chamber of an aircraft cabin air conditioning system according to claim 5, characterized in that: The bottom plate (13) of the shell is covered with a layer of condensate adsorption layer (15).

8. The low-pressure buffer chamber of an aircraft cabin air conditioning system according to claim 1, characterized in that: The air inlet pipe assembly (30) includes a pipe (31) and a pipe insulation sleeve (32). The two ends of the pipe (31) are connected to the buffer space and the air conditioning unit output port, respectively. The pipe insulation sleeve (32) is wrapped around the outside of the pipe (31).

Images