An aircraft ozone converter

Abstract

The application discloses an aircraft ozone converter, which comprises a shell, a guide vane, a catalyst, a catalyst carrier assembly, a wrapping material and a grounding ring; the shell is of an inlet expansion and outlet contraction structure, the inner wall of the inlet expansion section is provided with the guide vane distributed in the circumferential direction; the catalyst carrier assembly is of a porous structure and is fixed in the middle part of the shell; the catalyst is attached to the inner surface of the porous structure of the catalyst carrier assembly to catalyze the chemical reaction of the ozone in the airflow; the outer circumference of the catalyst carrier assembly is covered with the wrapping material; and the shell is provided with the grounding ring. The application can improve the ozone catalysis efficiency and reduce the aerodynamic resistance.

Description

Technical Field

[0001] This invention relates to the field of aviation technology, and more specifically to an aircraft ozone converter. Background Technology

[0002] In the stratosphere, Earth's atmosphere is characterized by stable airflow, few clouds, and high visibility. Aircraft cruising in the stratosphere are safer and consume less energy. During flight, the air inside the cabin needs to be purified and recirculated. Some exhaust gases are expelled outside the cabin, while a suitable amount of outside air is introduced to replenish it. The upper stratosphere contains a high concentration of ozone. Ozone absorbs a large amount of ultraviolet radiation, protecting life on Earth from the harmful effects of solar ultraviolet rays. However, when outside ozone enters the cabin, it becomes one of the main pollutants. Exceeding a certain dose can cause serious harm to human health. The International Civil Aviation Organization (ICAO) has established international standards, and aircraft flight certification standards strictly limit the concentration of ozone inside the cabin. The Aircraft Environmental Control (ESC) system, while controlling the bleed air volume, filters and purifies the introduced high-altitude air, thus providing a safe and comfortable atmospheric environment inside the cabin. An ozone converter, as part of the ESC system, incorporates a carrier with an attached catalyst to remove ozone and other pollutants. This device ensures that the ozone concentration inside the cabin does not exceed safe levels when the aircraft passes through airspace with high ozone concentrations. In environmental control systems, ozone converters introduce significant flow resistance, resulting in substantial flow losses to the internal airflow. Therefore, improving ozone catalytic efficiency while reducing aerodynamic drag is crucial for enhancing the overall performance of ozone converters in aircraft environmental control systems. Summary of the Invention

[0003] In view of this, the present invention provides an aircraft ozone converter that can improve ozone catalytic efficiency while reducing aerodynamic drag.

[0004] This 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 inlet expansion and an outlet contraction structure, and the inner wall of the inlet expansion section is provided with guide vanes distributed circumferentially; the catalyst carrier assembly has a porous structure and is 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 the ozone in the passing airflow; the outer circumference of the catalyst carrier assembly is covered with the encapsulating material; the shell is provided with a grounding ring.

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

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

[0008] Furthermore, the inner carrier is a combination of a hemispherical structure and a cylindrical structure. The cylindrical structure is the same size as the columnar notch inside the outer ring carrier, and the hemispherical structure protrudes from the outer ring carrier and faces the inlet direction.

[0009] Furthermore, the cylindrical carrier has a honeycomb cavity array porous structure with regular hexagonal pores;

[0010] The outer ring carrier is a porous structure with a honeycomb cavity array, and the pores are regular hexagonal.

[0011] The inner carrier is a honeycomb cavity array porous structure, with the holes being a combination of large and small regular hexagons. A ring of small regular hexagons is provided around the large regular hexagons, and adjacent large regular hexagons share the small regular hexagons.

[0012] Furthermore, the catalyst support assembly is fixed inside the housing 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, where α > β; and the intermediate catalytic section has a cylindrical structure.

[0015] Furthermore, the guide vane includes a large guide vane and a small guide vane, both of which have a streamlined structure and are arranged at intervals along the circumference.

[0016] Beneficial effects:

[0017] 1. The guide vanes in the expansion section of this invention can cut and break up the low-energy fluid in the inner wall boundary layer, breaking large-scale separation vortices into small-scale vortices, thereby delaying the separation of low-energy flows, reducing flow losses caused by separation vortices, and improving aerodynamic stability. The porous catalyst support assembly can improve ozone catalytic efficiency.

[0018] Secondly, the wrapping material can provide cushioning and protection, as well as a certain degree of 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 multiple carrier units. It 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 cavity array porous structure, which has a larger catalyst adhesion area, stronger structural stability and lower air resistance compared with wave carriers and square hole carriers, thereby achieving a higher ozone catalytic removal effect.

[0020] 3. The inner carrier of this invention is provided with a streamlined hemispherical structure that protrudes from the outer ring carrier and faces the inlet direction, so as to fully contact the incoming flow and improve the catalytic effect. Moreover, according to the ozone treatment capacity, the pores of the inner carrier are set as a combination of large regular hexagons and small regular hexagons, which not only improves the structural strength and stability of the carrier, but also increases the specific surface area for catalyst adhesion, thereby further improving the catalytic efficiency.

[0021] 4. The inlet expansion section of this invention has an inclination angle of α, and the outlet contraction section has an inclination angle of β. Since α>β, it can reduce aerodynamic losses and improve flow efficiency.

[0022] 5. The large and small guide vanes arranged in a circumferential array along the inner wall of this invention can smoothly guide the incoming flow, reduce flow distortion, delay the separation of low-energy flow, improve aerodynamic stability, and reduce flow losses caused by separation vortices. Attached Figure Description

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

[0024] Figure 2 This is a front view of the cross-section of the casing of the present invention.

[0025] Figure 3 This is a cross-sectional view of the casing of the present invention from two oblique angles.

[0026] Figure 4 This is a front view of the housing of the present invention.

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

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

[0029] Figure 7 This 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 vane, 8-small guide vane, 9-grounding ring. Detailed Implementation

[0031] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0032] This invention provides an aircraft ozone converter, which is applied to the aircraft's gas inerting system, such as... Figure 1 As shown, the aircraft ozone converter includes a housing 1, a wrapping material 2, a catalyst, a catalyst carrier assembly, and a flow guide plate.

[0033] The shell 1 has an inlet expansion and an outlet contraction structure. The inner wall of the inlet expansion section is provided with guide vanes distributed circumferentially. The catalyst carrier assembly has a porous structure and is fixed in the middle of the shell 1 by flanges 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 ozone in the passing gas flow. The outer circumference of the catalyst carrier assembly is covered with a wrapping material 2. The shell 1 is also provided with a grounding ring 9, which is connected to the ground by a wire.

[0034] Specifically, such as 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, and α>β; the intermediate catalytic section is a cylindrical structure.

[0035] The guide vanes include large guide vanes 7 and small guide vanes 8, both of which have streamlined structures 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 determined based on the magnitude, direction, and distortion of the inlet flow velocity. Since the airflow immediately enters the expansion channel after entering the ozone converter inlet, the low-energy fluid on the inner wall surface of the inlet expansion section of the shell accumulates continuously as the flow field develops, eventually forming significant flow separation under the adverse pressure gradient, resulting in flow losses. The large guide vanes 7 and small guide vanes 8, arranged in a circumferential array along the inner wall, can cut and break up the low-energy fluid in the inner wall boundary layer, breaking large-scale separation vortices into smaller-scale vortices, thereby delaying low-energy flow separation, reducing flow losses caused by separation vortices, and improving aerodynamic stability.

[0036] Silicone resin latex is used as the adhesive for the catalyst coating and is applied to the catalyst carrier assembly, allowing the catalyst 4 to adhere to the porous inner surface 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 foremost end, directly 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, with the inner carrier 5 fixed inside the outer ring carrier 4. In this embodiment, three cylindrical carriers 3 are used.

[0037] Among them, such as Figure 5As shown, the cylindrical carrier 3 has a honeycomb cavity array porous structure with regular hexagonal pores. The diameter of the inscribed circle of the honeycomb pores is set according to the incoming aerodynamic conditions and ozone treatment capacity. The outer ring carrier 4 has a honeycomb cavity array porous structure with regular hexagonal pores; the inner carrier 5 has a honeycomb cavity array porous structure, and the pores can be regular hexagonal, or, depending on the ozone treatment capacity, a combination of large and small regular hexagons can be used, such as... Figure 7 As shown, a ring of smaller regular hexagons surrounds the large regular hexagons, and adjacent large regular hexagons share the smaller regular hexagons. This overlapping arrangement improves the structural strength and stability of the carrier and increases the catalyst attachment surface area, thereby improving catalytic efficiency. The honeycomb structure possesses strong stability and permeability, enhancing the structural strength of the catalyst carrier. Compared to wave-shaped and square-pore carriers, the dihedrals of the honeycomb cavity array porous structure are all obtuse angles. A dihedral is the corner formed by the intersection of two solid walls, representing the convergence area of ​​two solid-wall boundary layers. Its distribution is strongly correlated with flow conditions. The convergence of boundary layers in the corner region can trigger flow separation, a common problem in both external and internal flow domains, and a major cause of flow deterioration in the solid-wall convergence area. This invention employs a honeycomb cavity array porous structure where all dihedrals are 120°, effectively reducing the flow resistance of the boundary layer in the acute dihedral region of the wave-shaped carrier, allowing for smooth and efficient airflow.

[0038] As an improvement, it can be adjusted according to the incoming aerodynamic conditions, such as Figure 6 As shown, the inner carrier 5 is a combination of a hemispherical structure and a cylindrical structure. The cylindrical structure is the same size as the columnar notch inside the outer ring carrier 4, and 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 merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An aircraft ozone converter, characterized in that, Includes the shell, guide vanes, catalyst, catalyst support assembly, wrapping material, and grounding ring; The shell has an inlet expansion and an outlet contraction structure, with guide vanes distributed circumferentially on the inner wall of the inlet expansion section; the catalyst carrier assembly has a porous structure and is fixed in the middle of the shell, with the catalyst attached to the inner surface of the porous structure of the catalyst carrier assembly to catalyze the ozone in the passing airflow; the outer circumference of the catalyst carrier assembly is covered with the encapsulating material; a grounding ring is provided on the shell; The catalyst support assembly includes a combined support and one or more cylindrical supports. The combined carrier is located at the foremost end, directly facing the inlet, with one or more cylindrical carriers arranged in layers behind it; the combined carrier includes an outer ring carrier and an inner carrier, with the inner carrier fixed inside the outer ring carrier; The inner carrier is a combination of a hemispherical structure and a cylindrical structure. The cylindrical structure is the same size as the columnar notch inside the outer ring carrier, and the hemispherical structure protrudes from the outer ring carrier and faces the inlet direction.

2. The aircraft ozone converter as described in claim 1, characterized in that, The cylindrical carrier has a honeycomb cavity array porous structure with regular hexagonal pores. The outer ring carrier is a porous structure with a honeycomb cavity array, and the pores are regular hexagonal. The inner carrier is a honeycomb cavity array porous structure, with the holes being a combination of large and small regular hexagons. A ring of small regular hexagons is provided around the large regular hexagons, and adjacent large regular hexagons share the small regular hexagons.

3. The aircraft ozone converter as described in claim 1, characterized in that, The catalyst support assembly is fixed inside the housing by a flange.

4. The aircraft ozone converter as described in 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, where α > β; and the intermediate catalytic section has a cylindrical structure.

5. The aircraft ozone converter as described in claim 1, characterized in that, The guide vanes include large guide vanes and small guide vanes, both of which have a streamlined structure and are arranged at intervals along the circumference.

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