A device and system for aircraft cabin warming

Abstract

The application discloses a device and system for heating an aircraft cabin, and relates to the technical field of aviation equipment. The device comprises a shell, a first joint fixedly connected to the shell for introducing hot bleed air, a cold air inlet pipe, a second joint for outputting mixed gas, a nozzle fixedly connected in the shell, a gas hole pipe, a partition plate, and a filling layer. The first joint is inserted into the shell and connected to the nozzle for conduction. The nozzle is located in one end of the gas hole pipe. The other end of the gas hole pipe is connected to the second joint for conduction. The gas hole pipe passes through the partition plate. The cold air inlet pipe is connected to a mixing cavity for conduction. The filling layer is sleeved and fixed on the gas hole pipe in a filling cavity. The system comprises the above-mentioned hot mixing device and an engine. The hot bleed air port of the engine is connected to the first joint for conduction. The device and system realize stable temperature of mixed air output gas through the shell, the first joint, the cold air inlet pipe, the second joint, the nozzle, the gas hole pipe, the partition plate, and the filling layer.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aviation equipment, and in particular to a device and system for heating a cockpit of an aircraft. BACKGROUND

[0002] For low-speed flying aircraft, the heating system is an important system. Because a large amount of heat is transferred to the outside by the cabin wall at low speed, a large amount of heating system is needed to compensate. Rapid heating of a cold and wet aircraft on the ground is also important.

[0003] The current heating method is specifically as follows: bypass system, electric heater, radiant panel, combustion heater, and waste gas heating. The Y5B aircraft is a typical example of using waste gas heating to heat the cockpit.

[0004] A device with temperature adjustment function, with the publication number CN 104019252 B, includes a shell, a connecting rod, a large rocker arm, a small rocker arm I, a small rocker arm II, a rotating shaft, a bolt, a valve piece I, a valve piece II, and a valve piece III. The connecting rod, the large rocker arm, the small rocker arm I, the small rocker arm II, and the rotating shaft on the shell form a parallel rocker connecting rod mechanism. When the large rocker arm is shaken, the valve pieces can be controlled to rotate around their respective rotating shafts in their respective pipelines through the parallel rocker connecting rod mechanism. When the valve piece I and the valve piece III have an angle of 10°<α<80° with the pipeline axis, the valve piece II has an angle of β=90°-α with the hot gas pipeline axis. The cold and hot air is in a mixed state. The size of the angle α can control the mixing ratio of the cold and hot air. The device improves the ventilation capacity of the aircraft ventilation system, expands the temperature adjustment range, improves the fresh air flow of the cockpit, and enhances the comfort of the cockpit environment.

[0005] However, the structure is not conducive to the mixing of cold and hot air, the temperature of the mixed air outlet is unstable, and the hot gas cannot be controlled to be turned off, so that the mixing cavity is in a high pressure state for a long time, which is prone to leakage. The technical solution of the present application adopts a gas hole type mixer, the air mixing is stable, the output hot gas temperature is stable, and the input of hot gas can be turned off. When the input of hot gas is turned off, the device also has the function of ventilating the cockpit.

[0006] The electric aircraft with the auxiliary heating device in a low-temperature environment includes power batteries and an auxiliary heating device. The power batteries include a plurality of power battery groups and are arranged in a power battery cabin to provide flight power for the electric aircraft. The auxiliary heating device heats the power batteries to ensure the endurance of the power batteries. The auxiliary heating device includes a heating device body, an oil supply system, a heat-conducting air transmission system, a combustion control system, and a central control system. The auxiliary heating device heats the power battery cabin, the cabin, and the aircraft defrosting system in a low-temperature environment, improves the range of the electric aircraft in a low-temperature environment, and improves the comfort and flight safety of the cabin.

[0007] However, the control system is complex, the supplied hot air mainly ensures the normal operation of the equipment, and the temperature stability control is poor. The heating destination of the technical scheme of the present application is to ensure the comfortable environment of the driver, and the temperature stability requirement is higher. The technical scheme of the present application adopts an air hole type mixer, the air mixing is stable, and the temperature of the output hot air is stable.

[0008] The aircraft cabin air conditioning system includes a dehumidifying device, a cold and hot device, and an air supply device connected in sequence. The dehumidifying device includes a primary membrane dehumidifying assembly, a gas compressor, and a secondary membrane dehumidifying assembly. The air inlet end of the primary membrane dehumidifying assembly is in communication with the atmosphere. The air outlet end of the primary membrane dehumidifying assembly is connected to the air inlet end of the gas compressor through a pipeline. The air inlet end of the secondary membrane dehumidifying assembly is connected to the air outlet end of the gas compressor through a pipeline. The gas compressor is used for pressurization and air suction from the atmosphere. By setting the gas compressor, the air suction from the atmosphere is used as the air source to replace the traditional air supply mode with the engine gas compressor as the power source, thereby reducing the power loss of the aircraft engine and improving the engine performance.

[0009] However, it belongs to the field of integrated air conditioners, and its structure is complex, and its principle is similar to that of a household air conditioning system. There is a principle difference between the technical scheme of the present application.

[0010] In combination with the above three patent documents and the existing technical scheme, the inventor finds that there are the following technical problems in the existing technical scheme.

[0011] The structure of the existing technical scheme is not conducive to the mixing of cold and hot air, the temperature of the mixed air outlet is unstable, and the shutdown of the hot air cannot be controlled, so that the mixed cavity is in a high-pressure state for a long time, and the risk of leakage is easy to occur.

[0012] The control system of the existing technical scheme is complex, and the supplied hot air mainly ensures the normal operation of the equipment, and the temperature stability control is poor.

[0013] The prior art problems and thinking:

[0014] How to solve the technical problem of unstable temperature of mixed output gas of air mixer. SUMMARY

[0015] The technical problem to be solved by the present application is to provide a device and system for heating the cabin of an aircraft to solve the technical problem of unstable temperature of mixed output gas of air mixer.

[0016] To solve the above technical problems, the technical solution adopted by the present application is: a device for heating the cabin of an aircraft comprises a shell, a first connector fixedly connected to the shell for introducing hot bleed air, a cold air inlet pipe and a second connector for outputting mixed gas, and a nozzle, a gas hole pipe, a partition and a filling layer fixedly connected in the shell, the first connector is located on one side of the shell, the second connector is located on the other side of the shell, the first connector is inserted into the shell and connected to the nozzle for conduction, the nozzle is located in one end of the gas hole pipe, the other end of the gas hole pipe is connected to the second connector for conduction, the gas hole pipe passes through the partition, the partition is located inside the shell on the side of the nozzle, a mixing cavity is formed between the partition and the inside of the shell on the side of the nozzle, a filling cavity is formed between the partition and the inside of the shell on the side of the second connector, the cold air inlet pipe is connected to the mixing cavity for conduction, and the filling layer is sleeved and fixed on the gas hole pipe in the filling cavity.

[0017] Further technical solutions are: the shell, the first connector, the cold air inlet pipe, the second connector, the nozzle, the gas hole pipe, the partition and the filling layer form a thermal mixer, and the shell is a cylindrical shell.

[0018] Further technical solutions are: the first connector is a first straight pipe connector, and the second connector is a second straight pipe connector.

[0019] Further technical solutions are: the nozzle is an air inlet cone pipe.

[0020] Further technical solutions are: the filling layer comprises a protective layer for preventing high-temperature burning and a heat preservation layer, the protective layer is located outside the gas hole pipe, and the heat preservation layer is located outside the protective layer.

[0021] Further technical solutions are: the protective layer is an asbestos layer made of asbestos cloth, and the heat preservation layer is a heat preservation cotton layer made of heat preservation cotton.

[0022] Further technical solutions are: further comprising a valve, and the valve is connected to the first connector for conduction.

[0023] Further technical solutions are as follows: the valve comprises a knife gate valve, a pull cable, a first rocker arm, a knife gate valve joint and a second rocker arm, the knife gate valve comprises a knife gate valve support and a knife gate valve body, the knife gate valve body is fixedly connected with the knife gate valve support, the knife gate valve body is provided with the knife gate valve joint, the knife gate valve body is connected with the first joint in a conductive mode, one end of the first rocker arm is rotationally connected with the knife gate valve support, the other end of the first rocker arm is rotationally connected with one end of the second rocker arm, the other end of the second rocker arm is connected with the pull cable, and the second rocker arm is rotationally connected with the knife gate valve joint.

[0024] Further technical solutions are as follows: the pull cable is movably connected with a pull cable support.

[0025] A system for heating an aircraft cabin comprises the above-mentioned hot mixing device, and further comprises an engine, the engine is provided with a hot bleed port, and the hot bleed port of the engine is connected with the first joint in a conductive mode.

[0026] Further technical solutions are as follows: the system further comprises a valve, the hot bleed port of the engine, the valve and the first joint are sequentially connected in a conductive mode.

[0027] Further technical solutions are as follows: the engine is a turboprop engine.

[0028] The above-mentioned technical solutions have the following beneficial effects:

[0029] A device for heating an aircraft cabin comprises a shell, a first joint fixedly connected to the shell for introducing hot bleed air, a cold air inlet pipe and a second joint for outputting mixed gas, a nozzle, a gas hole pipe, a partition plate and a filling layer fixedly connected in the shell, the first joint is located on one side of the shell, the second joint is located on the other side of the shell, the first joint is inserted into the shell and connected with the nozzle in a conductive mode, the nozzle is located in one end of the gas hole pipe, the other end of the gas hole pipe is connected with the second joint in a conductive mode, the gas hole pipe passes through the partition plate, the partition plate is located in the shell on the side of the nozzle, a mixing cavity is formed between the partition plate and the shell on the side of the nozzle, a filling cavity is formed between the partition plate and the shell on the side of the second joint, the cold air inlet pipe is connected with the mixing cavity in a conductive mode, and the filling layer is sleeved and fixed on the gas hole pipe in the filling cavity. The technical solution realizes stable temperature of output gas by the shell, the first joint fixedly connected to the shell, the cold air inlet pipe and the second joint, and the nozzle, the gas hole pipe, the partition plate and the filling layer fixedly connected in the shell.

[0030] A system for heating an aircraft cabin comprises the above-mentioned hot mixing device, and further comprises an engine, the engine is provided with a hot bleed port, and the hot bleed port of the engine is connected with the first joint in a conductive mode. The technical solution realizes stable temperature of output gas by the hot bleed port of the engine being connected with the first joint in a conductive mode.

[0031] For details, see the part of specific embodiments. BRIEF DESCRIPTION OF DRAWINGS

[0032] Figure 1 is a structural diagram of embodiment 1 of the present application;

[0033] Figure 2 is a sectional view of A-A of Figure 1

[0034] Figure 3 is an installation diagram of embodiment 2 of the present application;

[0035] Figure 4 is a view of A of Figure 3 DETAILED DESCRIPTION

[0036] The technical solutions in the embodiments of the present application will be clearly and completely described in the present application with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present application, but not all the embodiments. The following description of at least one exemplary embodiment is actually only illustrative, but not as any limitation on the present application and its application or use. 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 protection of the present application.

[0037] In the following description, many specific details are set forth in order to provide a thorough understanding of the present application, but the present application can also be implemented in other ways different from those described herein, and those skilled in the art can make similar generalizations without departing from the connotation of the present application, therefore the present application is not limited to the specific embodiments disclosed below.

[0038] Embodiment 1:

[0039] As shown in Figure 1 and Figure 2 , the present application discloses a device for heating the cockpit of an aircraft, which comprises a shell, a first joint fixedly connected to the shell for introducing hot bleed air, a cold air inlet pipe and a second joint for outputting mixed gas, and a nozzle, a gas hole pipe, a partition and a filling layer fixedly connected in the shell, the first joint is located on one side of the shell, the second joint is located on the other side of the shell, the first joint is inserted into the shell and connected with the nozzle in conduction, the nozzle is located in one end of the gas hole pipe, the other end of the gas hole pipe is connected with the second joint in conduction, the gas hole pipe passes through the partition, the partition is located inside the shell on the side of the nozzle, a mixing cavity is formed between the partition and the inside of the shell on the side of the nozzle, a filling cavity is formed between the partition and the inside of the shell on the side of the second joint, the cold air inlet pipe is connected with the mixing cavity in conduction, and the filling layer is sleeved and fixed on the gas hole pipe in the filling cavity.

[0040] ​​The filling layer comprises a protective layer for preventing high-temperature burning and a heat preservation layer, the protective layer is located outside the air hole pipe, and the heat preservation layer is located outside the protective layer.

[0041] As shown in the structural diagram of the hot mixer. Figure 1 The casing comprises an outer cover 20, the first joint is a first elbow joint 9, the second joint is a second elbow joint 12, the casing, the first joint, the cold air inlet pipe, the second joint, the nozzle, the air hole pipe, the partition plate and the filling layer form the hot mixer, and the casing is a cylindrical casing.

[0042] As shown in the structural diagram of the hot mixer. Figure 2 The nozzle is an air inlet cone pipe 25, the air hole pipe is an air hole speed reduction pipe 26, the partition plate is a separation fixing plate 21, the protective layer is an asbestos layer 23 made of asbestos cloth, the heat preservation layer is a heat preservation cotton layer 22 made of heat preservation cotton, the first end cover 19, the outer cover 20 and the second end cover 24 form the casing, and the port of the first elbow joint 9 is a hot air bleed inlet.

[0043] Example 2:

[0044] As shown in the structural diagram of the hot mixer. Figure 3 And Figure 4 As shown in the structural diagram of the hot mixer, the device for heating the cockpit of the aircraft based on the device of example 1, i.e. the hot mixer 11, further comprises a valve and a hot air bleed pipe, the valve is connected and conducted through the hot air bleed pipe and the first joint, the valve comprises a knife gate valve, a control cable, a control cable support 6, a first rocker arm 16, a knife gate valve joint 17 and a second rocker arm 18, the knife gate valve comprises a knife gate valve support 15 and a knife gate valve body 4, the control cable is a push-pull control cable 5, the control cable is sleeved with the control cable support 6, and the control cable is in sliding fit with the control cable support 6.

[0045] As shown in the structural diagram of the hot mixer. Figure 3 The hot air bleed pipe comprises a first hot air bleed pipe 3 and a second hot air bleed pipe 7, the first hot air bleed pipe 3, the knife gate valve body 4, the second hot air bleed pipe 7 and the first elbow joint 9 are sequentially connected and conducted, and the port of the cold air inlet pipe 10 is a cold air inlet.

[0046] As shown in the structural diagram of the hot mixer. Figure 4 The knife gate valve body 4 is fixedly connected with the knife gate valve support 15, the knife gate valve body 4 is provided with the knife gate valve joint 17, one end of the first rocker arm 16 is hingedly connected with the knife gate valve support 15, the other end of the first rocker arm 16 is hingedly connected with one end of the second rocker arm 18, the other end of the second rocker arm 18 is connected with the control cable, and the second rocker arm 18 is hingedly connected with the knife gate valve joint 17.

[0047] The knife gate valve body itself is a prior art which will not be described here.

[0048] Usage of example 2:

[0049] As shown in the structural diagram of the hot mixer. Figure 3As shown, the first hot bleed pipe 3 is fixed by the pipe fixing clamp 2, and the first hot bleed pipe 3 is connected with the engine through the third straight pipe joint 1.

[0050] As shown, Figure 3 As shown, the hot mixer 11 is fixed by the hot mixer fixing clamp 8, and the second straight pipe joint 12 is connected to the fourth straight pipe joint 14 through the warm air output pipe 13, and the port of the fourth straight pipe joint 14 is the outlet of the mixed hot air.

[0051] Embodiment 3:

[0052] The application discloses a system for heating the cabin of an airplane, based on the device of embodiment 2, further comprising an engine, the engine being a turboprop engine, the engine having a hot bleed port, the hot bleed port of the engine being connected to the first joint of the hot mixer through a hot bleed pipe and a valve.

[0053] The purpose of the present application is:

[0054] To provide stable hot air supply for the cabin of an airplane, so that the airplane can adapt to low temperature environment and provide a comfortable driving environment for the driver.

[0055] The idea of the present application is:

[0056] The present application relates to a heating system for the cabin of an airplane, comprising a porous hot mixer.

[0057] The prior art mixing is uneven, and the heating effect is greatly reduced during ground maintenance test run.

[0058] In order to obtain stable hot air and obvious heating effect during ground maintenance test run, it is found that the use of Venturi effect can ensure obvious heating effect during ground maintenance test run.

[0059] Through the multi-hole pipe, the flow rate of the hot air during the mixing process can be slowed down, and the effect of disturbing the flow can be achieved, so that the cold air and the hot bleed air can be mixed more uniformly.

[0060] After the use of the Y5B turboprop engine, stable and efficient heating effect can be achieved.

[0061] The cabin heating method of the Y5B airplane after replacing the turboprop engine is completely different from the original Y5B, and the hot bleed air of the engine can be used to heat the cabin.

[0062] The temperature of the hot bleed air of the engine is very high, which can reach more than 200 DEG C, and it is very important to reduce the temperature of the high-temperature hot bleed air to a suitable temperature, which is also the difficulty of this heating method.

[0063] Technical contribution:

[0064] It is located between the equipment cabin and the engine cabin, and uses the hot bleed air generated by the turboprop engine to supply the cabin with heat.

[0065] Specifically, the third elbow joint 1 is connected with the hot bleed air port of the engine, and the high-temperature hot bleed air of the engine is transported to the knife gate valve 4 through the first hot bleed air pipe 3.

[0066] The push-pull control of the control cable 5 controls the linkage of the first rocker arm 16, the knife gate valve joint 17, and the second rocker arm 18, thereby controlling the opening and closing of the knife gate valve 4 and the opening and closing of the hot bleed air.

[0067] The hot bleed air is transported into the hot mixer 11 through the second hot bleed air pipe 7 and the first elbow joint 9.

[0068] In the hot mixer 11, the cold air entering the hot mixer through the cold air inlet pipe 10 is preliminarily mixed with the hot bleed air entering the hot mixer through the second hot bleed air pipe 7 and the first elbow joint 9 in the cavity between the first end cover 19 and the separation fixed plate 21.

[0069] The preliminarily mixed gas is mixed again between the air hole speed reduction pipes 26, and the mixed gas enters the heating pipeline in the aircraft cabin through the second elbow joint 12 and the warm air output pipe 13, achieving the purpose of heating the cabin.

[0070] To ensure the heating efficiency, asbestos cloth 23 is wound on the air hole speed reduction pipe 26 to prevent the high-temperature hot bleed air from burning the outer layer of thermal insulation cotton 22. Moreover, thermal insulation cotton 22 is wound on the asbestos cloth to play a thermal insulation role.

[0071] Technical solution:

[0072] In Example 2, a push-pull cable is used to control the opening and closing of the knife gate valve, thereby controlling the opening and closing of the hot bleed air. This scheme is not limited by space and can be easily controlled in a large space.

[0073] In addition to the above examples, a hard control can also be used to control the opening and closing of the knife gate valve, thereby controlling the opening and closing of the hot bleed air, such as a pull rod rocker arm. This scheme has space limitations and is used in small-span spaces.

[0074] In addition to the above examples, an electromagnetic control valve can also be used to control the opening and closing of the hot bleed air and the size of the opening. This scheme has a higher cost and risk compared to a purely mechanical type.

[0075] In addition to the above examples, the preliminary mixing cavity of the gas, i.e., the mixing cavity, can be appropriately increased or decreased according to the pressure of the engine hot bleed air and the installation space limitations.

[0076] Compared with the above-mentioned embodiment, according to the pressure of the engine hot air and the limitation of the installation space, the length of the air hole speed reduction pipe can be appropriately lengthened or shortened. Or the diameter of the air hole speed reduction pipe is increased or decreased to control the heating effect of the mixed gas.

[0077] Compared with the above-mentioned embodiment, according to the heating effect, the asbestos cloth can be replaced with a fireproof thermal insulation material, and after replacing the fireproof material, the thermal insulation cotton can be cancelled.

[0078] The feedback of the on-site technical personnel after the application runs for a period of time is beneficial in that:

[0079] Compared with other inventions, the hot air and cold air of the technical scheme of the application are uniformly mixed, the output of the heated gas is stable, and the situation of hot and cold alternation does not occur.

[0080] The opening and closing of the knife gate valve are controlled by the push-pull steel cable, the structure layout is not limited by space, and the temperature of the cabin heating can be controlled by controlling the opening and closing size of the knife gate valve.

[0081] And in the design of the thermal mixer, the Venturi effect is used, so that when the aircraft is ground tested or maintained, without the propeller ram, the cold air can still enter the thermal mixer and still supply the cabin with hot air.

[0082] The air hole pipe, i.e. the air hole speed reduction pipe 26, is provided with air holes. In the air hole pipe part in the mixing cavity, the cold and hot gases can be more fully mixed through the air holes of this part, and the mixing efficiency is improved. In the air hole pipe part of the filling layer area, the filling layer is closely attached to the air hole pipe of this part, and the air holes of this part slightly hinder the airflow passing through. The airflow flow rate in the air hole pipe of the filling layer area is slightly slower than that in the ordinary pipe without air holes. The slightly slow flowing gas is more conducive to further mixing of the gas, so that the temperature of the output gas is more stable, and the flow rate of the output gas is more stable.

[0083] At present, the technical scheme of the application has been pilot tested, i.e. a small-scale test before mass production of the product; after the pilot test is completed, user use research is carried out in a small range, and the research result shows that the user satisfaction is high; now the preparation for formal production of the product for industrialization (including intellectual property risk early warning research) has been started.

Claims

1. A device for warming an aircraft cabin, characterized by: The device comprises a shell, a first joint fixedly connected to the shell for introducing hot bleed air, a cold air inlet pipe, a second joint for outputting mixed gas, a nozzle, a gas hole pipe, a partition and a filling layer fixedly connected in the shell, the first joint is located on one side of the shell, the second joint is located on the other side of the shell, the first joint is inserted into the shell and connected to the nozzle, the nozzle is located in one end of the gas hole pipe, the other end of the gas hole pipe is connected to the second joint, the gas hole pipe passes through the partition, the partition is located inside the shell on the side of the nozzle, a mixing cavity is formed between the partition and the inside of the shell on the side of the nozzle, a filling cavity is formed between the partition and the inside of the shell on the side of the second joint, the cold air inlet pipe is connected to the mixing cavity, and the filling layer is sleeved and fixed on the gas hole pipe in the filling cavity.

2. A device for warming the cockpit of an aircraft according to claim 1, characterized in that: The shell, the first joint, the cold air inlet pipe, the second joint, the nozzle, the gas hole pipe, the partition and the filling layer form a hot mixer, the shell is a cylindrical shell, the first joint is a first straight pipe joint, the second joint is a second straight pipe joint, and the nozzle is an inlet cone pipe.

3. A device for warming the cockpit of an aircraft according to claim 1, characterized in that: The filling layer comprises a protective layer for preventing high-temperature burning and a heat preservation layer, the protective layer is located outside the gas hole pipe, and the heat preservation layer is located outside the protective layer.

4. A device for warming the cockpit of an aircraft according to claim 3, characterized in that: The protective layer is an asbestos layer made of asbestos cloth, and the heat preservation layer is a heat preservation cotton layer made of heat preservation cotton.

5. A device for warming the cockpit of an aircraft according to claim 1, characterized in that: The device further comprises a valve connected to the first joint.

6. A device for warming the cockpit of an aircraft according to claim 5, characterized in that: The valve comprises a knife gate valve, a pull cable, a first rocker arm, a knife gate valve joint and a second rocker arm, the knife gate valve comprises a knife gate valve support and a knife gate valve body, the knife gate valve body is fixedly connected to the knife gate valve support, the knife gate valve body is provided with the knife gate valve joint, the knife gate valve body is connected to the first joint, one end of the first rocker arm is rotationally connected to the knife gate valve support, the other end of the first rocker arm is rotationally connected to one end of the second rocker arm, the other end of the second rocker arm is connected to the pull cable, and the second rocker arm is rotationally connected to the knife gate valve joint.

7. A device for warming the cockpit of an aircraft according to claim 6, characterized in that: The device further comprises a pull cable support, and the pull cable is movably connected to the pull cable support.

8. A system for cabin warming of an aircraft, characterized in that: The device of claim 1 further comprises an engine, the engine is provided with a hot bleed air port, and the hot bleed air port of the engine is connected to the first joint.

9. A system for warming an aircraft cabin according to claim 8, wherein: The device further comprises a valve, and the hot bleed air port of the engine, the valve and the first joint are sequentially connected.

10. A system for heating an aircraft cabin according to claim 8 or 9, characterized in that: The engine is a turboprop engine.

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