An infrared observation device under high temperature and high humidity conditions

Abstract

The utility model discloses an infrared observation equipment under high temperature and high humidity conditions relates to aircraft fittings technical field, the utility model discloses a first shell and second shell are installed with infrared sensor transmitting end in the first shell inside, the second shell inside is installed with infrared sensor receiving end, and the first shell and second shell inside are installed with the lens, and the both sides of first shell and second shell are connected with the air hole through the connecting frame. The utility model discloses through the setting of first shell, second shell and lens, the first shell and second shell made of inconel718 alloy material all have excellent high temperature resistance, and the lens is fused quartz and also has excellent high temperature resistance, thereby being convenient for the protection of infrared sensor transmitting end and infrared sensor receiving end, reducing the influence that the high temperature of engine and tail gas causes infrared sensor transmitting end and infrared sensor receiving end, can resist high temperature and be installed in the engine tail end to carry out infrared observation to tail gas, and the precision is high and the service life is long.

Description

Technical Field

[0001] This utility model relates to the field of aircraft parts technology, specifically to an infrared observation device for high temperature and high humidity conditions. Background Technology

[0002] During flight, an aircraft primarily propels itself by burning fuel in its engine. This combustion produces exhaust gases. Observing the composition of these exhaust gases helps track engine combustion efficiency, optimize fuel consumption, reduce fuel usage, and mitigate environmental impact. Furthermore, an excess of a particular component can indicate engine malfunction. The detection method mainly involves irradiating the exhaust gases with infrared light using sensors. Gases such as carbon dioxide and carbon monoxide in the exhaust gases absorb infrared light of different wavelengths. The sensors then receive the remaining unabsorbed light, and the pollutant concentration is calculated by comparing the absorption spectrum data.

[0003] When infrared observation equipment is used to observe exhaust gas, if it is installed too close to the engine, the sensor is easily burned out by the engine's high temperature. If it is installed far away from the engine, although burning out can be avoided, the exhaust gas may mix with the outside air, thereby reducing the concentration of certain components and affecting the accuracy of the observation. Utility Model Content

[0004] Therefore, the purpose of this utility model is to provide an infrared observation device under high temperature and high humidity conditions to solve the technical problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: an infrared observation device under high temperature and high humidity conditions, comprising a first outer shell and a second outer shell, wherein an infrared sensor transmitter is installed inside the first outer shell, an infrared sensor receiver is installed inside the second outer shell, and lenses are installed inside the first and second outer shells. Air vents are connected to both sides of the first and second outer shells via connecting frames, and a second air groove is provided inside the connecting frames. A first air groove is provided on both sides of the first and second outer shells.

[0006] By adopting the above technical solution, when the infrared sensor transmitter and receiver are working, the first and second shells, made of Inconel alloy, have excellent high-temperature resistance, and the lens, made of fused silica, also has excellent high-temperature resistance. This facilitates the protection of the infrared sensor transmitter and receiver, reducing the impact of high engine and exhaust temperatures on them. Simultaneously, external air is introduced through vents extending to the outside of the engine or low-temperature airflow from the engine compressor is introduced into the aircraft. This airflow then contacts the first and second shells through the first and second air ducts, facilitating forced convection cooling of the shells and removing heat transferred from the engine interior. This further reduces the impact of high engine and exhaust temperatures on the infrared sensor transmitter and receiver. Furthermore, both the first and second shells are integrally formed through forging, turning, grinding, and polishing, resulting in good airtightness. This prevents humid air from entering the shells during external airflow cooling, thus preventing moisture-induced short circuits in the infrared sensor transmitter and receiver and improving structural stability.

[0007] Furthermore, both the connecting frame and the air vent are made of Inconel alloy material, and both the first outer shell and the second outer shell are integrally formed using Inconel alloy material.

[0008] By adopting the above technical solution, both the first and second shells are integrally formed by forging, turning, grinding and polishing, which has good airtightness and prevents the humid air at high altitude from entering the interior of the first and second shells when guiding the external airflow for heat dissipation. This avoids the infrared sensor transmitter and receiver from getting damp and short-circuiting, and improves the structural stability.

[0009] Furthermore, the lens is made of fused silica.

[0010] By adopting the above technical solution, when the infrared sensor transmitter and receiver are working, the first and second shells made of Inconel alloy material have excellent high temperature resistance, and the lens, made of fused silica, also has excellent high temperature resistance. This makes it easy to protect the infrared sensor transmitter and receiver, reducing the impact of high engine and exhaust temperatures on the infrared sensor transmitter and receiver.

[0011] Furthermore, both the connecting frame and the second air duct have ladder-shaped cross sections.

[0012] By adopting the above technical solution, the cross-sections of the connecting frame and the second air duct are both ladder-shaped to facilitate the guidance of airflow, allowing the airflow to enter from the outside or the compressor, with a smaller turning angle, thereby reducing airflow resistance.

[0013] Furthermore, multiple second air ducts are provided, and the multiple second air ducts are distributed at equal intervals.

[0014] By adopting the above technical solution and increasing the number of second air ducts, it is easier to divert the heat dissipation airflow in advance, so that the subsequent heat dissipation airflow can enter multiple first air ducts respectively.

[0015] Furthermore, the second air duct is connected to the first air duct.

[0016] By adopting the above technical solution, external air is introduced through the air vents extending to the outside of the engine or the low-temperature airflow from the engine compressor is introduced through the air vents extending into the aircraft, so that the airflow comes into contact with the first and second outer shells through the first and second air vents.

[0017] Furthermore, multiple first air ducts are provided, and the multiple first air ducts are distributed at equal intervals.

[0018] By adopting the above technical solution, by increasing the number of first air ducts, the contact area between the heat dissipation airflow and the first and second outer shells is increased, thereby improving the heat dissipation efficiency.

[0019] Furthermore, one side of the air vent is sloped.

[0020] By adopting the above technical solution, the vent is sloped on one side to facilitate air guidance and avoid the outside airflow colliding with the vent, which would generate greater resistance.

[0021] Furthermore, the inner walls of the connecting frame, the air vent, the first air duct, and the second air duct are all coated with a polytetrafluoroethylene coating.

[0022] By adopting the above technical solution and applying a coating to the areas where the cooling airflow comes into contact, the friction and resistance when the airflow changes direction can be reduced, thereby extending the service life of the structure.

[0023] Furthermore, multiple first shells, second shells, infrared sensor transmitters, infrared sensor receivers, lenses, connecting frames, and heat insulation plates are provided, and these multiple first shells, second shells, infrared sensor transmitters, infrared sensor receivers, lenses, connecting frames, and heat insulation plates are arranged in a ring array.

[0024] By adopting the above technical solution, redundancy is increased by increasing the number of infrared sensor transmitters and receivers and connecting them in parallel. This ensures that if one pair of infrared sensor transmitters and receivers fails, the remaining infrared sensor transmitters and receivers can continue to operate.

[0025] In summary, the present invention has the following main advantages:

[0026] 1. This utility model, through the arrangement of a first outer shell, a second outer shell, and a lens, features a first and second outer shell made of Inconel 718 alloy material, both of which have excellent high-temperature resistance. The lens, made of fused silica, also possesses excellent high-temperature resistance, thus facilitating the protection of the infrared sensor transmitter and receiver, reducing the impact of high engine and exhaust temperatures on them. It is also heat-resistant, easy to install at the engine tail for infrared observation of exhaust gases, and offers high accuracy and a long service life.

[0027] 2. This utility model, through the setting of a connecting frame, air vent, first air duct, and second air duct, allows for the introduction of external air through the air vent extending to the outside of the engine or the introduction of low-temperature airflow from the engine compressor inside the aircraft. This facilitates cooling of the first and second outer shells through forced convection, promptly removing heat transferred from the engine interior to the first and second outer shells. This further reduces the impact of high engine and exhaust temperatures on the infrared sensor transmitter and receiver, and improves heat dissipation, thereby enhancing the long-term operation of the infrared observation equipment in high-temperature environments.

[0028] 3. The present invention features a first outer shell and a second outer shell, both of which are integrally formed by forging, turning, grinding and polishing, resulting in good airtightness. This prevents humid air from entering the interior of the first and second outer shells when guiding external airflow for heat dissipation, thereby preventing the infrared sensor transmitter and receiver from short-circuiting due to moisture, improving structural stability, increasing moisture resistance and extending the service life of the structure. Attached Figure Description

[0029] Figure 1 This is a schematic diagram of the structure of Embodiment 1 of the present utility model;

[0030] Figure 2 This is a schematic diagram of the structure of Embodiment 2 of this utility model;

[0031] Figure 3 This is a schematic diagram of the first outer shell structure of this utility model;

[0032] Figure 4 This is a schematic diagram of the cross-sectional structure of the second outer shell of this utility model;

[0033] Figure 5 This is a schematic diagram of the first outer shell structure of this utility model in an explosion.

[0034] In the figure: 1. First outer shell; 2. Second outer shell; 3. Infrared sensor transmitter; 4. Infrared sensor receiver; 5. Lens; 6. Connecting frame; 7. Air outlet; 8. First air duct; 9. Second air duct. Detailed Implementation

[0035] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0036] The embodiments of this utility model will be described below based on its overall structure.

[0037] Example 1:

[0038] An infrared observation device for high temperature and high humidity conditions, such as Figure 1 , Figure 3 , Figure 4 and Figure 5 As shown, the system includes a first outer shell 1 and a second outer shell 2. Both the first and second outer shells 2 are integrally formed from Inconel 718 alloy material. An infrared sensor transmitter 3 is installed inside the first outer shell 1, and an infrared sensor receiver 4 is installed inside the second outer shell 2. Lenses 5 are installed inside both the first and second outer shells 1 and 2, and the lenses 5 are made of fused silica. Both the first and second outer shells made of Inconel 718 alloy material have excellent high-temperature resistance, and the lenses made of fused silica also have excellent high-temperature resistance. This facilitates the protection of the infrared sensor transmitter and receiver, reducing the impact of high engine and exhaust temperatures on the infrared sensor transmitter and receiver. Furthermore, both the first and second outer shells are integrally formed through forging, turning, grinding, and polishing, resulting in good airtightness. This prevents humid air from entering the interior of the first and second outer shells when guiding external airflow for heat dissipation, thereby preventing the infrared sensor transmitter and receiver from becoming damp and short-circuiting, and improving structural stability.

[0039] See Figure 1 , Figure 3 , Figure 4 and Figure 5In the above embodiment, both sides of the first outer shell 1 and the second outer shell 2 are connected to air vents 7 via connecting frames 6. One side of the air vent 7 is sloping. Both the connecting frame 6 and the air vent 7 are made of Inconel 718 alloy material. A second air duct 9 is opened inside the connecting frame 6. The cross-section of both the connecting frame 6 and the second air duct 9 is ladder-shaped. Multiple second air ducts 9 are provided and are distributed at equal intervals. Both sides of the first outer shell 1 and the second outer shell 2 are provided with first air ducts 8. The second air ducts 9 are connected to the first air ducts 8. Multiple first air ducts 8 are provided and are distributed at equal intervals. The air vents extend to the outside of the engine to introduce external air or extend to the inside of the aircraft to introduce the low-temperature airflow of the engine compressor. This facilitates the cooling of the first and second outer shells through forced convection, and promptly removes the heat transferred from the inside of the engine to the first and second outer shells. This further reduces the impact of the high temperature of the engine and exhaust gas on the infrared sensor transmitter and the infrared sensor receiver.

[0040] Example 2:

[0041] Based on the above embodiment one, the following settings are now adopted to reduce wind resistance.

[0042] See Figure 3 and Figure 4 In the above embodiments, the inner walls of the connecting frame 6, the air vent 7, the first air duct 8, and the second air duct 9 are all coated with polytetrafluoroethylene (PTFE). By setting the coating at the places where the heat dissipation airflow will come into contact, the friction and resistance when the airflow turns can be reduced, thereby extending the service life of the structure.

[0043] Example 3:

[0044] Based on the above embodiment one, the following settings are now implemented to increase stability.

[0045] See Figure 2 In the above embodiments, multiple first housings 1, second housings 2, infrared sensor transmitters 3, infrared sensor receivers 4, lenses 5, connecting frames 6, and heat insulation plates 10 are provided. Multiple first housings 1, second housings 2, infrared sensor transmitters 3, infrared sensor receivers 4, lenses 5, connecting frames 6, and heat insulation plates 10 are arranged in a ring array. By increasing the number of structures such as infrared sensor transmitters 3 and infrared sensor receivers 4 and allowing them to work in parallel, redundancy is increased. This ensures that if a pair of infrared sensor transmitters 3 and infrared sensor receivers 4 is damaged, the remaining infrared sensor transmitters 3 and infrared sensor receivers 4 can continue to work.

[0046] The implementation principle of this utility model is as follows: First, a broadband infrared light is emitted from the infrared sensor transmitter 3 to the infrared sensor receiver 4. The exhaust gas generated by the aircraft during flight passes through the broadband infrared light. Different components in the exhaust gas absorb different wavelengths of the infrared light. For example, CO2 absorbs infrared light with a wavelength of 4.2-4.3μm, NOx absorbs infrared light with a wavelength of 5.2-5.4μm, and CO absorbs infrared light with a wavelength of 4.6-4.8μm. Then, the infrared sensor receiver 4 receives the remaining light that has not been absorbed and compares the received remaining light with the database to calculate the concentration of each component in the exhaust gas.

[0047] Furthermore, when the infrared sensor transmitter 3 and the infrared sensor receiver 4 are working, the first housing 1 and the second housing 2, both made of Inconel 718 alloy, have excellent high-temperature resistance, and the lens 5, being made of fused silica, also has excellent high-temperature resistance. This facilitates the protection of the infrared sensor transmitter 3 and the infrared sensor receiver 4, reducing the impact of high engine and exhaust temperatures on them. Simultaneously, external air is introduced through the vent 7 to the outside of the engine, or the low-temperature airflow from the engine compressor is introduced to the interior of the aircraft. This airflow passes through the first air duct 8 and the second air duct 9 and interacts with the first housing. The first housing 1 and the second housing 2 are in contact, which facilitates the cooling of the first housing 1 and the second housing 2 by forced convection, and removes the heat transferred from the engine to the first housing 1 and the second housing 2 in time, thereby further reducing the impact of the high temperature of the engine and exhaust gas on the infrared sensor transmitter 3 and the infrared sensor receiver 4; and the first housing 1 and the second housing 2 are integrally formed by forging, turning, grinding and polishing, with good airtightness, which prevents the humid air at high altitude from entering the first housing 1 and the second housing 2 when guiding the external airflow to dissipate heat, thereby preventing the infrared sensor transmitter 3 and the infrared sensor receiver 4 from being short-circuited due to moisture, and improving the structural stability.

[0048] Although embodiments of the present invention have been shown and described, these specific embodiments are merely explanations of the present invention and are not intended to limit the invention. The specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. After reading this specification, those skilled in the art may make modifications, substitutions, and variations to the embodiments as needed without departing from the principles and spirit of the present invention, provided that such modifications, substitutions, and variations are within the scope of the claims of the present invention and are protected by patent law.

Claims

1. An infrared observation device for high temperature and high humidity conditions, comprising a first outer shell (1) and a second outer shell (2), characterized in that: An infrared sensor transmitter (3) is installed inside the first housing (1), an infrared sensor receiver (4) is installed inside the second housing (2), and a lens (5) is installed inside the first housing (1) and the second housing (2). Air vents (7) are connected to both sides of the first housing (1) and the second housing (2) via connecting brackets (6). A second air duct (9) is opened inside the connecting brackets (6), and a first air duct (8) is opened on both sides of the first housing (1) and the second housing (2).

2. The infrared observation device under high temperature and high humidity conditions according to claim 1, characterized in that: The connecting frame (6) and the air vent (7) are both made of Inconel 718 alloy material, and the first shell and the second shell (2) are both integrally formed using Inconel 718 alloy material.

3. The infrared observation device under high temperature and high humidity conditions according to claim 1, characterized in that: The lens (5) is made of fused silica.

4. The infrared observation device under high temperature and high humidity conditions according to claim 2, characterized in that: The cross-sections of the connecting frame (6) and the second air duct (9) are both ladder-shaped.

5. The infrared observation device under high temperature and high humidity conditions according to claim 4, characterized in that: The second air duct (9) is provided in multiple ways, and the multiple second air ducts (9) are distributed at equal intervals.

6. The infrared observation device under high temperature and high humidity conditions according to claim 5, characterized in that: The second air duct (9) is connected to the first air duct (8).

7. The infrared observation device under high temperature and high humidity conditions according to claim 6, characterized in that: Multiple first air ducts (8) are provided, and the multiple first air ducts (8) are distributed at equal intervals.

8. The infrared observation device under high temperature and high humidity conditions according to claim 2, characterized in that: The air vent (7) has a sloping side.

9. The infrared observation device under high temperature and high humidity conditions according to claim 8, characterized in that: The inner walls of the connecting frame (6), the air vent (7), the first air duct (8), and the second air duct (9) are all coated with polytetrafluoroethylene.

10. The infrared observation device under high temperature and high humidity conditions according to claim 9, characterized in that: The first shell (1), the second shell (2), the infrared sensor transmitter (3), the infrared sensor receiver (4), the lens (5), the connecting frame (6) and the heat insulation plate (10) are all provided in multiple ways, and the multiple first shells (1), second shells (2), infrared sensor transmitters (3), infrared sensor receivers (4), lenses (5), connecting frames (6) and heat insulation plates (10) are all arranged in a ring array.

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