Aircraft ozone converter

Abstract

The invention discloses an airplane ozone converter which comprises a shell, a flow deflector, a catalyst, a catalyst carrier assembly, a wrapping material and a grounding ring, the shell is of a structure with an expanded inlet and a contracted outlet, and flow deflectors distributed in the circumferential direction are arranged on the inner wall of the expanded section of the inlet; the catalyst carrier assembly is of a porous structure and is fixed in the middle in the shell, and a catalyst is attached to the inner surface of the porous structure of the catalyst carrier assembly so as to carry out catalytic chemical reaction on ozone passing through airflow; the outer circumference of the catalyst carrier component is coated with the coating material; and a grounding ring is arranged on the shell. According to the invention, the aerodynamic resistance can be reduced while the ozone catalytic efficiency is improved.

Description

Technical Field

[0001] The invention relates to the field of aviation technology, and in particular to an aircraft ozone converter. Background Art

[0002] In the stratosphere of the earth's atmosphere, the airflow is smooth, there are few clouds, and the visibility is high. When an aircraft cruises in the stratosphere, the flight is safer and the energy consumption is lower. During the flight of an aircraft, the air in the cabin needs to be purified and recycled, and some of the exhaust gas is discharged outside the cabin. At the same time, an appropriate amount of air outside the cabin is introduced to supplement it. The atmosphere in the stratosphere contains a high concentration of ozone, which can absorb a large amount of ultraviolet rays and protect the earth's creatures from the ultraviolet rays of the sun. However, when the ozone outside the cabin enters the cabin, it becomes one of the main pollutants in the cabin. When it exceeds a certain dose, it will cause serious harm to the human body. The International Civil Aviation Organization (ICAO) has formulated international standards, and the aircraft flight certification standards have strictly limited the ozone concentration in the cabin. While controlling the amount of air intake, the aircraft environmental control system (ESC) will filter and purify the introduced high-altitude air, thereby providing a safe and comfortable atmospheric environment in the cabin. As part of the environmental control system, the ozone converter has a built-in carrier with a catalyst attached to remove ozone and other pollutants. This device ensures that the ozone concentration inside the cabin does not exceed a safe level when the aircraft passes through airspace with a high ozone concentration level. In the environmental control system, the ozone converter will cause a large flow resistance, which will bring great flow losses to the internal air flow. Therefore, while improving the ozone catalytic efficiency, reducing aerodynamic resistance is of great significance to improving the overall performance of the ozone converter of the aircraft environmental control system. Summary of the invention

[0003] In view of this, the present invention provides an aircraft ozone converter, which can reduce aerodynamic resistance while improving ozone catalytic efficiency.

[0004] The present invention provides an aircraft ozone converter, comprising a housing, a guide vane, a catalyst, a catalyst carrier assembly, a wrapping material and a grounding ring;

[0005] The shell has an expanded inlet and contracted outlet structure, and the inner wall of the expanded inlet section is provided with guide vanes distributed along the circumferential direction; the catalyst carrier assembly is a porous structure, fixed in the middle of the shell, and the catalyst is attached to the inner surface of the porous structure of the catalyst carrier assembly to catalyze a chemical reaction on ozone in the airflow; the outer circumference of the catalyst carrier assembly is coated with the wrapping material; and a grounding ring is provided on the shell.

[0006] Furthermore, the catalyst carrier assembly includes a combined carrier and one or more cylindrical carriers;

[0007] The combined carrier is located at the front end, facing the inlet, and one or more cylindrical carriers are arranged in layers behind the combined carrier; the combined carrier includes an outer ring carrier and an inner carrier, and the inner carrier is fixed in the outer ring carrier.

[0008] Furthermore, the inner carrier is a combination of a hemispherical structure and a cylindrical structure, the cylindrical structure is consistent in size with the columnar notch inside the outer ring carrier, and the hemispherical structure protrudes from the outer ring carrier toward the inlet direction.

[0009] Furthermore, the cylindrical carrier is a honeycomb beam cavity array porous structure, and the holes are regular hexagons;

[0010] The outer ring carrier is a honeycomb beam cavity array porous structure, and the holes are regular hexagons;

[0011] The inner carrier is a honeycomb beam cavity array porous structure, the holes are a combination structure of large regular hexagons and small regular hexagons, a circle of small regular hexagons is arranged outside the large regular hexagon, and two adjacent large regular hexagons share the small regular hexagon.

[0012] Furthermore, the catalyst carrier assembly is fixed in the shell by a flange.

[0013] Furthermore, the shell is divided into an inlet expansion section, an intermediate catalytic section and an outlet contraction section;

[0014] The inlet expansion section has an inclination angle of α, which is an acute angle less than 45°; the outlet contraction section has an inclination angle of β, α>β; and the middle catalytic section is a cylindrical structure.

[0015] Furthermore, the guide vanes include large guide vanes and small guide vanes, and both the large guide vanes and the small guide vanes have a streamlined structure and are arranged at intervals from each other along the circumferential direction.

[0016] Beneficial effects:

[0017] 1. The guide vanes provided in the expansion section of the present invention can cut and crush the low-energy fluid in the inner wall boundary layer, breaking the large-scale separation vortex into small-scale vortices, thereby delaying the separation of low-energy flow, reducing the flow loss caused by the separation vortex, and improving aerodynamic stability. The porous structure of the catalyst carrier assembly can improve the ozone catalytic efficiency.

[0018] Secondly, the wrapping material can provide a buffering protection and a certain degree of thermal insulation.

[0019] 2. The catalyst carrier assembly of the present invention is a combination of a combined carrier and one or more cylindrical carriers, which is composed of a plurality of carrier units, is easy to install, and can ensure the adhesion rate of the catalyst on each carrier unit; secondly, the catalyst carrier assembly of the present invention adopts a honeycomb beam cavity array porous structure, which has a larger catalyst adhesion area, stronger structural stability, and smaller air resistance than wave carriers and square hole carriers, thereby achieving a higher ozone catalytic removal effect.

[0020] 3. The inner carrier of the present invention is provided with a streamlined hemispherical structure, which protrudes from the outer ring carrier and faces the inlet direction, so as to be able to fully contact with the incoming flow and enhance the catalytic effect. Moreover, according to the ozone treatment capacity, the holes of the inner carrier are arranged as a cross-overlapping combination structure of large regular hexagons and small regular hexagons, which not only improves the strength and stability of the carrier structure, but also increases the specific surface area of ​​the catalyst attachment, thereby further improving the catalytic efficiency.

[0021] 4. The inclination angle of the inlet expansion section of the present invention is α, and the inclination angle of the outlet contraction section is β, α>β, which can reduce aerodynamic losses and improve flow efficiency.

[0022] 5. The large guide vanes and small guide vanes distributed in an array along the circumference of the inner wall of the present invention can smoothly guide the inlet flow, reduce the distortion of the flow, delay the separation of low-energy flow, improve the aerodynamic stability, and reduce the flow loss caused by the separation vortex. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the structure of the present invention (half of the housing is shown).

[0024] Figure 2 It is a front view of the shell section of the present invention.

[0025] Figure 3 This is an oblique cross-sectional view of the shell of the present invention.

[0026] Figure 4 It is the front view of the shell of the present invention.

[0027] Figure 5 It is a schematic diagram of the cylindrical carrier structure of the present invention.

[0028] Figure 6 It is a schematic diagram of the combined carrier structure of the present invention.

[0029] Figure 7 It is a front view and a partially enlarged schematic diagram of the combined carrier of the present invention.

[0030] Among them, 1-shell, 2-wrapping material, 3-cylindrical carrier, 4-outer ring carrier, 5-inner carrier, 6-flange, 7-large guide plate, 8-small guide plate, 9-grounding ring. DETAILED DESCRIPTION

[0031] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0032] The present invention provides an aircraft ozone converter, which is applied to a gas inerting system of an aircraft, such as Figure 1 As shown, the aircraft ozone converter includes a shell 1, a wrapping material 2, a catalyst, a catalyst carrier assembly and a guide vane.

[0033] The shell 1 is a structure with an expanded inlet and a contracted outlet. The inner wall of the expanded inlet section is provided with guide vanes distributed in the circumferential direction. The catalyst carrier assembly is a porous structure, which is fixed in the middle of the shell 1 by a flange 6 on the inner wall of the shell 1. The catalyst is attached to the inner surface of the porous structure of the catalyst carrier assembly to catalyze the chemical reaction of ozone in the airflow. The outer circumference of the catalyst carrier assembly is coated with a wrapping material 2. The shell 1 is also provided with a grounding ring 9, which is connected to the ground through a wire.

[0034] Specifically, Figure 2-4 As shown, the shell 1 is divided into an inlet expansion section, an intermediate catalytic section and an outlet contraction section; the inlet expansion section has an inclination angle of α, and α is an acute angle less than 45°; the outlet contraction section has an inclination angle of β, α>β; and the intermediate catalytic section is a cylindrical structure.

[0035] The guide vanes include large guide vanes 7 and small guide vanes 8. Both the large guide vanes 7 and the small guide vanes 8 present a streamlined structure and are arranged at intervals along the circumference of the inlet expansion section. The number of large guide vanes 7 and small guide vanes 8 is set according to the magnitude, direction and degree of distortion of the inlet flow velocity. Since the airflow enters the expansion channel immediately after entering the inlet of the ozone converter, the low-energy fluid on the inner wall surface of the inlet expansion section of the shell accumulates continuously with the development of the flow field, and eventually forms a larger flow separation under the adverse pressure gradient, causing flow loss. The large guide vanes 7 and small guide vanes 8 distributed in an array along the circumference of the inner wall can cut and crush the low-energy fluid in the boundary layer of the inner wall, breaking the large-scale separation vortex into small-scale vortices, thereby delaying the separation of low-energy flow, reducing the flow loss caused by the separation vortex, and improving the aerodynamic stability.

[0036] Silicone resin latex is used as an adhesive for the catalyst coating, which is arranged on the catalyst carrier assembly so that the catalyst 4 is attached to the inner surface of the porous structure of the catalyst carrier assembly. The catalyst carrier assembly includes a combined carrier and one or more cylindrical carriers 3; the combined carrier is located at the front end, facing the inlet, and one or more cylindrical carriers 3 are arranged in layers behind the combined carrier; the combined carrier includes an outer ring carrier 4 and an inner carrier 5, and the inner carrier 5 is fixed in the outer ring carrier 4. In this embodiment, three cylindrical carriers 3 are used.

[0037] Among them, Figure 5As shown, the cylindrical carrier 3 is a honeycomb beam cavity array porous structure, the holes are regular hexagons, and the diameter of the inscribed circle of the honeycomb holes is set according to the incoming flow aerodynamic conditions and ozone treatment capacity. The outer ring carrier 4 is a honeycomb beam cavity array porous structure, the holes are regular hexagons; the inner carrier 5 is a honeycomb beam cavity array porous structure, the holes can be regular hexagons, and can also be set to a large regular hexagon and a small regular hexagon combination structure according to the ozone treatment capacity, such as Figure 7 As shown, a circle of small regular hexagons is arranged outside the large regular hexagon, and the two adjacent large regular hexagons share the small regular hexagons. This cross-overlapping combination arrangement not only improves the strength and stability of the carrier structure, but also increases the catalyst attachment surface area and improves the catalytic efficiency. The honeycomb structure has strong stability and permeability, and can improve the structural strength of the catalyst carrier. Compared with the wave carrier and the square hole carrier, the "dihedral angles" of the porous structure of the honeycomb beam cavity array are all obtuse angles. The "dihedral angle" is the corner formed by the intersection of two solid wall surfaces. It is the intersection area of ​​the two solid wall boundary layers. Its distribution law is strongly related to the flow conditions. The intersection of the boundary layers in the corner area can cause flow separation. This is a common problem faced by the external flow and internal flow fields, and it is the main cause of the deterioration of the flow in the solid wall intersection area. The present invention adopts a honeycomb beam cavity array porous structure with all "dihedral angles" of 120°, which can effectively reduce the boundary layer flow resistance in the acute dihedral angle area of ​​the wave carrier, allowing the airflow to pass smoothly and efficiently.

[0038] As an improvement, it can be based on the aerodynamic conditions of the incoming flow, such as Figure 6 As shown, the inner carrier 5 is set as a combination of a hemispherical structure and a cylindrical structure. The cylindrical structure is consistent in size with the columnar notch inside the outer ring carrier 4. The hemispherical structure protrudes from the outer ring carrier 4, facing the inlet direction, and is in full contact with the airflow.

[0039] In summary, the above are only preferred embodiments of the present invention and are not intended to limit the protection scope of the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft ozone converter, characterized in that: It includes a shell, a guide vane, a catalyst, a catalyst carrier assembly, a wrapping material and a grounding ring; The shell has an expanded inlet and contracted outlet structure, and the inner wall of the expanded inlet section is provided with guide vanes distributed along the circumferential direction; the catalyst carrier assembly is a porous structure, fixed in the middle of the shell, and the catalyst is attached to the inner surface of the porous structure of the catalyst carrier assembly to catalyze a chemical reaction on ozone in the airflow; the outer circumference of the catalyst carrier assembly is coated with the wrapping material; and a grounding ring is provided on the shell.

2. An aircraft ozone converter according to claim 1, characterized in that The catalyst carrier assembly includes a combined carrier and one or more cylindrical carriers; The combined carrier is located at the front end, facing the inlet, and one or more cylindrical carriers are arranged in layers behind the combined carrier; the combined carrier includes an outer ring carrier and an inner carrier, and the inner carrier is fixed in the outer ring carrier.

3. An aircraft ozone converter according to claim 2, characterized in that The inner carrier is a combination of a hemispherical structure and a cylindrical structure. The cylindrical structure is consistent in size with the columnar notch inside the outer ring carrier. The hemispherical structure protrudes from the outer ring carrier toward the inlet direction.

4. An aircraft ozone converter according to claim 2 or 3, characterized in that The cylindrical carrier is a honeycomb beam cavity array porous structure, and the holes are regular hexagons; The outer ring carrier is a honeycomb beam cavity array porous structure, and the holes are regular hexagons; The inner carrier is a honeycomb beam cavity array porous structure, the holes are a combination structure of large regular hexagons and small regular hexagons, a circle of small regular hexagons is arranged outside the large regular hexagon, and two adjacent large regular hexagons share the small regular hexagon.

5. The aircraft ozone converter according to claim 1, characterized in that The catalyst carrier assembly is fixed in the shell by a flange.

6. An aircraft ozone converter according to claim 1, characterized in that The shell is divided into an inlet expansion section, an intermediate catalytic section and an outlet contraction section; The inlet expansion section has an inclination angle of α, which is an acute angle less than 45°; the outlet contraction section has an inclination angle of β, α>β; and the middle catalytic section is a cylindrical structure.

7. An aircraft ozone converter according to claim 1, characterized in that The guide vanes include large guide vanes and small guide vanes. Both the large guide vanes and the small guide vanes have a streamlined structure and are arranged at intervals from each other along the circumferential direction.

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