CN212514365U - Cabin wall heat transfer experiment simulation device under passenger plane cruising state - Google Patents
Cabin wall heat transfer experiment simulation device under passenger plane cruising state Download PDFInfo
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- CN212514365U CN212514365U CN202021380281.5U CN202021380281U CN212514365U CN 212514365 U CN212514365 U CN 212514365U CN 202021380281 U CN202021380281 U CN 202021380281U CN 212514365 U CN212514365 U CN 212514365U
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- 238000002474 experimental method Methods 0.000 title claims abstract description 16
- 238000004088 simulation Methods 0.000 title claims description 12
- 238000012360 testing method Methods 0.000 claims abstract description 15
- 238000010438 heat treatment Methods 0.000 claims abstract description 12
- 238000007664 blowing Methods 0.000 claims abstract description 5
- 230000017525 heat dissipation Effects 0.000 claims abstract description 5
- 239000000463 material Substances 0.000 claims description 12
- 239000000523 sample Substances 0.000 claims description 7
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- 108010066057 cabin-1 Proteins 0.000 description 4
- 238000004378 air conditioning Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
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- 229910000838 Al alloy Inorganic materials 0.000 description 1
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- 229920003023 plastic Polymers 0.000 description 1
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Abstract
The utility model discloses a passenger plane cruise state bulkhead heat transfer experiment analogue means down, including low pressure environment cabin, low pressure environment cabin is equipped with depressurization system, air conditioner and blowing system for simulate aircraft cruise state under cabin external pressure and the wind speed environment. The low-pressure environment cabin is internally provided with a pressurizing environment cabin used for simulating an airplane cabin, the pressurizing environment cabin is provided with a pressurizing system, a heating box and a fan and used for simulating the pressurization of an airplane cabin environment control system to enable the pressure and the temperature of the cabin to reach a human body comfortable state, and the human body heat dissipation and cabin airflow flowing building can also be simulated. The pressurized environment chamber is provided with a bulkhead heat transfer testing system and a data acquisition instrument. The utility model discloses can accurate test bulkhead convection heat transfer coefficient, bulkhead heat transfer capacity, bulkhead temperature under the low pressure condition, obtain experimental data and can be used for the interior environmental control system's of cabin optimal design, also can provide reliable boundary condition and high-quality contrast verification experimental data for the Computational Fluid Dynamics (CFD) numerical calculation of cabin air current.
Description
Technical Field
The utility model relates to a passenger plane passenger cabin thermal environment experimental study, concretely relates to passenger cabin bulkhead heat transfer characteristic is cabin wall heat transfer experiment analogue means under the passenger plane cruise status.
Background
With the rapid development of economy in China, people prefer convenient and rapid high-speed rails and airplanes for the selection of vehicles for traveling. In 2016, 4.9 million people in China travel by plane, and in 2019, the number of people increases to 6.6 million. At the same time, the thermal comfort of the cabin environment of an aircraft has also attracted considerable attention.
The environment in which the aircraft is in cruising conditions is very harsh and when the aircraft is at a height of ten thousand metres, the atmospheric pressure outside the cabin will be as low as 0.2 atm. In order to ensure the comfort and safety of passengers, the cabin needs to be pressurized under the cruising flight condition. However, due to cost, cabin wall tolerances, etc., the cabin volume is typically only 0.8atm (ASHRAE. ASHRAE Handbook HVAC Applications [ M ]. Atlanta: American Society of Heating, refining and Air-Conditioning Engineers, 2011.).
However, the real aircraft cannot perform related flow field and temperature field experiments in a cruising state; 1: 1 the simulation cabin is large in size, the cost of pressure in the control cabin is high, the experiment difficulty is very high, almost all experimental measurements of the thermal environment in the cabin are carried out by building an experiment table on the ground, and the pressure in the cabin is 1 atm. The cabin air temperature was controlled at 18-24 ℃ and the air flow rate was 0.2m/s (Hunt E, Reid D, Space D, et al. commercial air environmental control system [ C ]. Aerospace medical Association annular Meeting, 1995.). The Computational Fluid Dynamics (CFD) of cabin air flow directly specifies the cabin interior wall temperature as a computational boundary condition for the cabin Environment (Zhang Z, Chen X, Mazumdar S. Experimental and numerical interpretation of air flow and passenger transport in an air compressor cabin mounted [ J ]. Building and environmental, 2009,44(1): 85-94). However, as the pressure changes, the heat exchange capacity between the cabin air and the wall changes, and the cabin wall temperature changes. The change of the temperature of the inner wall surface of the cabin also influences the radiation heat exchange of human bodies and seats in the cabin, so that the heat transfer of the cabin wall of the airplane has very obvious influence on the temperature field in the cabin. The experiment table is built on the ground, the pressure of the inner surface and the outer surface of the cabin wall is ensured to be the same as the working condition of the cruise state of the airplane by simplifying experimental equipment and controlling boundary conditions, the convective heat transfer coefficient under the condition of low pressure of the surface of the cabin wall is accurately measured, the temperature change characteristic of the wall surface under the condition of the cruise state of the airplane is researched, and the experiment table has important significance on the thermal comfort design and the cabin wall structure design of the environment in the cabin of the.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to solve the aforesaid not enough and provide a passenger plane cruise state bulkhead heat transfer experiment analogue means down, this analogue means can not only adjust the change of the internal and external pressure of cabin, can also simulate human sensible heat dissipation in the cabin, also can adjust the inside and outside temperature in cabin, the research is under the aircraft cruise state, the temperature variation law of cabin inner wall to and the convection heat transfer coefficient of cabin inner wall and under-deck air, can optimize bulkhead structural design like this. In addition, because the air in the aircraft cabin and the external environment are continuously subjected to heat exchange, the related environment control system can make up for the loss of cold and heat caused by the heat exchange of the cabin wall, and provides guarantee for comfortable and healthy aircraft cabin environment, so that the design of the aircraft environment control system is also beneficial.
In order to achieve the purpose, the utility model relates to a cabin wall heat transfer experiment simulation device under the cruising state of an airliner, which comprises a low-pressure environment cabin and a pressurizing environment cabin arranged in the low-pressure environment cabin; the low-pressure environment cabin is characterized in that the main body of the low-pressure environment cabin is a closed space, the low-pressure environment cabin is provided with a pressure reducing system, an air conditioner and a blowing system, the pressure reducing system is composed of a vacuum pump, a compressor, a manometer and a pipeline, the pressure reducing system simulates the pressure state outside the cabin under the cruise state of the airplane by controlling the pressure of the low-pressure environment cabin, the air conditioner and the blowing system are composed of an air conditioner and a high-power fan, and the air conditioner and the blowing system are used for controlling the temperature and the humidity of the low-;
the pressurizing environment cabin is provided with a pressurizing system, a heating box, a fan, a cabin wall heat transfer testing system and a data acquisition instrument; the pressurization system comprises air compressor, pressure gauge, electromagnetism relief valve and pipeline, the pressurization system is through simulating aircraft cabin pressure environment for the pressurization of pressurization environment under-deck air, the case that generates heat with 75W's power and simulate human heat dissipation and provide the heat source for the pressurization environment under-deck, the fan builds the flow of pressurization environment under-deck air through rotating, monitors the cabin in-deck temperature of pressurization cabin through temperature probe.
The bulkhead heat transfer test system comprises the following bulkhead materials from inside to outside: the interior trim panel, the heat insulation layer, the skin and the bulkhead are made of real aircraft materials, and the types and the thicknesses of the materials can be adjusted according to experiments. The cabin wall heat transfer testing system is provided with a temperature and wind speed sensor which can test the temperature and the wind speed of the air above the surface of the cabin wall.
The obtained test data are transmitted into the data acquisition instrument through the data conversion module, and the data can be used for calculating the convective heat transfer coefficient and the bulkhead heat transfer capacity.
The beneficial effects of the utility model
In the design of aircraft cabins, the bulkhead structural design can be optimized. In addition, because the air in the cabin of the airplane and the external environment exchange heat continuously, the related environment control system can make up the cold/heat loss caused by the heat exchange of the cabin wall, so as to provide guarantee for the comfortable and healthy environment of the cabin of the airplane, and the experimental data obtained by the experimental simulation device for the heat transfer of the cabin wall, such as the convection heat exchange coefficient of the cabin wall, the heat transfer quantity of the cabin wall and the temperature of the cabin wall under the low-pressure condition, can be used for the optimal design of the environment control system in the cabin, and can also provide reliable boundary conditions and high-quality comparison verification experimental data for the Computational Fluid Dynamics (CFD) numerical calculation of the airflow.
Drawings
Fig. 1 is an exploded view of the experimental simulation device of the present invention;
FIG. 2 is a diagram of a bulkhead heat transfer test system:
Reference numerals: 1, a low-pressure environment chamber, 2, a bulkhead heat transfer testing system, 3, an air conditioner, 4, an air compressor a, 5, a vacuum pump, 6, a fan a, 7 pipelines, 8 electromagnetic pressure relief valves, 9, an air compressor b, 10, a pressurized environment chamber, 11, a fan b, 12 pressure gauges, 13 temperature probes, 14 a heating box, 15 pressure gauges, 16 data acquisition instruments and 17 data conversion modules;
2-1 interior trim panel, 2-2 heat insulation layer, 2-3 skin, 2-4 heat flow meter, 2-5 temperature sensor and 2-6 temperature and wind speed sensor.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings:
as shown in figure 1, the utility model relates to a passenger plane cruise state bulkhead heat transfer experiment analogue means down, low pressure environment cabin 1 when environment outside the cabin including simulation aircraft cruise state, low pressure environment cabin 1 is high confined space, low pressure environment cabin 1 has vacuum pump 5, air compressor a4, pipeline 7, pressure gauge 12 for create low pressure environment and monitor low pressure environment under-deck pressure, low pressure environment cabin 1 has air conditioner 3, fan a6, pressurization environment cabin 10, be used for adjusting low pressure environment under-deck air temperature and humidity, fan a6 is bloied to pressurization environment cabin 10 bulkhead, the outer surface of bulkhead is bloied the state when simulation aircraft is flown.
Further, the pressurization environment cabin 10 is used for simulating an aircraft cabin, the pressurization environment cabin 10 is a highly closed space, the pressurization environment cabin 10 is provided with an air compressor b9, a pipeline 7, an electromagnetic pressure release valve 8 and a pressure gauge 15 and is used for creating a pressure environment of the pressurization environment cabin 10, a pressurization control system of the simulation aircraft cabin boosts the pressure of the cabin to reach a comfortable pressure level of a human body, a heating box 14 is arranged in the pressurization environment cabin 10 and generates heat through the heating box 14 to simulate the heat dissipation of the human body in the cabin, a temperature probe 13 is arranged in the pressurization environment cabin 10 and is used for monitoring the air temperature in the pressurization environment cabin, a fan b11 is arranged in the pressurization environment cabin 10 and is used for creating airflow flowing, and the pressurization environment cabin 10 is provided with a cabin wall heat transfer testing system 2.
Further, the bulkhead heat transfer test system 2 has the following inner to outer bulkhead materials: the interior trim panel 2-1 can be a sandwich panel; the heat insulating layer 2-2 can be made of foam plastics, the skin 2-3 can be made of aluminum alloy, the bulkhead material is a real airplane material, and the type and the thickness of the material can be adjusted according to experiments. The heat transfer test system 2 of the bulkhead has heat flow meters 2-4 and temperature sensors 2-5, which are tightly attached to the bulkhead, and temperature and wind speed sensors 2-6, the temperature probe 13, the heat flow meters 2-4, the temperature sensors 2-5, and the temperature and wind speed sensors 2-6 all measure the obtained data through the sensors and are connected with a data acquisition instrument 16 through a data conversion module 17, the data conversion module 17 can adopt TTL to 485 conversion, the temperature probe 13 can adopt a K-type thermocouple, the heat flow meters 2-4 can adopt HFM-4H type multi-channel heat flow meters, and the temperature and wind speed sensors 2-5 can adopt hot wire anemometers or hot ball anemometers.
The utility model discloses an operating procedure as follows:
(1) checking the connection state of each component and line of the device to ensure that the device can work normally;
(2) and starting the vacuum pump, pumping air into the low-pressure environment cabin, observing the pressure gauge, and stopping pumping air when the pressure reaches 0.2 atm. Starting an air conditioning system to regulate the temperature and the humidity in the low-pressure environment cabin, starting a fan in the low-pressure environment cabin to blow the pressurized environment cabin wall, and monitoring the wind speed by using a temperature sensor and a wind speed sensor to simulate the flow of airflow outside the aircraft cabin;
(3) starting a pressurizing system to pressurize the low-pressure environment cabin to 0.8atm, stopping pressurizing, starting a heating box to simulate the heating of a dummy, and starting a fan to create airflow flow in the pressurizing environment cabin;
(4) when the temperature of the air inside the cabin in the pressurized environment reaches 20 ℃, the wind speed of the upper surface of the inner wall of the cabin is 0.2m/s, and the temperature t of the inner surface of the cabin wall is measuredw(. degree. C.), surface heat flow q (W/m)2) Near the temperature t of the air above the bulkhead surfacea(DEG C), calculating the convective heat transfer coefficient by the following formula:
(5) the thickness and the heat conductivity of the material of the bulkhead can be known according to the material of the bulkhead, so that the thermal resistance of the bulkhead can be calculated, and the heat transfer quantity of the bulkhead can be obtained by measuring the area of the bulkhead through the following formula. Wherein Q is the heat transfer amount (W) through the cabin wall surface, and K is the composite heat transfer coefficient (W.m) of the cabin wall surface-2·℃-1) And A is the cabin wall area (m)2)，taiIs the temperature (. degree. C.) of the air in the cabin, taoIs the temperature (. degree. C.) of the air outside the cabin, deltawiIs the thickness (m), lambda of the i-th layer of bulkhead materialwiIs the thermal conductivity (W.m) of the i-th bulkhead material-1·℃-1)，hiIs the convective heat transfer coefficient of air on the surface of the inner wall of the cabin, (W.m)-2·℃-1)，hoThe convective heat transfer coefficient of the air on the surface of the outer wall of the cabin can be obtained in the step 4;
Q＝KA(tai-tao)，
(6) after the experiment is finished, the heating box is closed, the fan is used, the electromagnetic pressure relief valve of the pressurizing environment cabin is opened, after the pressure of the pressurizing environment cabin is the same as that of the low-pressure environment cabin, the air compressor of the low-pressure environment cabin is opened to pressurize the low-pressure environment cabin, the pressure of the low-pressure environment cabin is the same as that of the atmosphere, and the power supply is cut off.
The above embodiments are merely illustrative of the preferred embodiments of the present invention, and are not intended to limit the scope of the present invention, and various modifications and improvements made by those skilled in the art without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.
Claims (3)
1. The cabin wall heat transfer experiment simulation device under the cruising state of the passenger plane is characterized in that: the low-pressure environment cabin is a highly closed space and is provided with a vacuum pump, an air compressor a, a pipeline and a pressure gauge and is used for creating a low-pressure environment and monitoring the pressure in the low-pressure environment cabin; the aircraft is also provided with an air conditioner, a fan a and a pressurized environment cabin, wherein the air conditioner, the fan a and the pressurized environment cabin are used for adjusting the temperature and the humidity of air in the low-pressure environment cabin, and the fan a blows air to the cabin wall of the pressurized environment cabin to simulate the air blowing state of the outer surface of the cabin wall when the aircraft flies;
the pressurization environment cabin is used for simulating an airplane cabin, is a highly closed space and is provided with an air compressor b, a pipeline, an electromagnetic pressure release valve and a pressure gauge, and is used for creating a pressure environment of the pressurization environment cabin and simulating an airplane cabin environment control system to boost the cabin to achieve a pressure level comfortable for a human body; a heating box is arranged in the pressurizing environment cabin, the heat dissipation of a human body in the cabin is simulated through the heating of the heating box, and a temperature probe is also arranged and used for monitoring the air temperature in the pressurizing environment cabin; a fan b is arranged in the pressurizing environment cabin and used for creating airflow; the pressurized environment chamber is provided with a bulkhead heat transfer testing system and a data acquisition instrument.
2. The experimental simulation apparatus for cabin wall heat transfer in cruising conditions of an airliner as defined in claim 1, wherein: the bulkhead heat transfer test system comprises the following bulkhead materials from inside to outside: the interior trim panel, the heat insulation layer, the skin and the bulkhead are made of real aircraft materials.
3. The experimental simulation apparatus for cabin wall heat transfer in cruising conditions of an airliner as defined in claim 1, wherein: the heat transfer testing system of the bulkhead is provided with a heat flow meter, a temperature sensor and a temperature and wind speed sensor which are tightly attached to the bulkhead, wherein the temperature probe, the heat flow meter, the temperature sensor and the temperature and wind speed sensor measure obtained data through the sensors and are connected with a data acquisition instrument through a data conversion module.
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| CN111830082A (en) * | 2020-07-14 | 2020-10-27 | 天津大学 | Cabin wall heat transfer experiment simulation device under passenger plane cruising state |
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