CN219475518U - Experimental system for plate fireproof test and temperature measurement under back high-speed air flow condition - Google Patents
Experimental system for plate fireproof test and temperature measurement under back high-speed air flow condition Download PDFInfo
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- CN219475518U CN219475518U CN202320794337.9U CN202320794337U CN219475518U CN 219475518 U CN219475518 U CN 219475518U CN 202320794337 U CN202320794337 U CN 202320794337U CN 219475518 U CN219475518 U CN 219475518U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
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Abstract
The utility model relates to the technical field of aviation fireproof tests, and discloses an experimental system for fireproof tests and temperature measurement of plates under the condition of high-speed airflow at the back, which comprises an air inlet section, a test section and an exhaust section, wherein an airflow compression section is arranged between the air inlet section and the test section; the area of the compression opening of the airflow compression section is smaller than the area of the air inlet of the airflow compression section, and the areas of the compression opening and the air inlet of the airflow compression section are in a preset ratio; the air inlet section is connected with the variable frequency fan; the test section is provided with a thermocouple socket; and the air inlet section, the air flow compression section, the test section and the exhaust section are detachably connected. The system provided by the utility model is suitable for fire tests of aviation boards, is convenient to operate, and is convenient to assemble, disassemble and debug.
Description
Technical Field
The utility model relates to the technical field of aviation fireproof tests, in particular to an experimental system for board fireproof tests and temperature measurement under the condition of high-speed airflow at the back.
Background
In order to ensure the operation safety of the aircraft, it is important to make aircraft fireproof measures. Except for setting up complete fire protection measures on the aircraft, the fireproof performance of each component on the aircraft is crucial, and is a basic protection checkpoint in aircraft fire. Among them, the aviation sheet material, as an important component of the aircraft body, has important importance in terms of fire resistance.
At present, a lot of fire resistance test systems are available for plates, the plates are mostly fixed and hoisted through fixing clamps and the like, an ignition gun and the like are used for directly spraying fire on the surfaces of the plates, and then the flame combustion degree and the flame spreading speed are observed, so that the fire resistance test and judgment are completed. However, such test systems are not suitable for use with aircraft panels. The operation environment of the aviation board is more complex than that of the ordinary board. The fire environment faced by the aviation sheet is more extreme, and the impact on the fire is more various; moreover, as an aviation component, the test standard requirements are more, which makes the existing test system unsuitable for testing aviation boards.
Disclosure of Invention
The utility model aims to provide an experimental system for fire resistance test and temperature measurement of boards under the condition of high-speed airflow at the back, which is suitable for fire resistance test of boards for aviation, and is convenient to operate, assemble, disassemble and debug.
The basic scheme provided by the utility model is as follows: the experimental system for fireproof test and temperature measurement of the plate under the high-speed back air flow condition comprises an air inlet section, a test section and an exhaust section, wherein an air flow compression section is arranged between the air inlet section and the test section; the area of the compression opening of the airflow compression section is smaller than the area of the air inlet of the airflow compression section, and the areas of the compression opening and the air inlet of the airflow compression section are in a preset ratio; the air inlet section is connected with the variable frequency fan; one side of the test section is provided with a thermocouple socket, and the opposite side of the test section is provided with an opening; and the air inlet section, the air flow compression section, the test section and the exhaust section are detachably connected.
Further, an anemometer is arranged at the inlet end of the test section; the anemometer is used for monitoring the test wind speed.
Further, the preset ratio is the area of the compression port of the airflow compression section: inlet area of air flow compression section = 1: (1.50-1.60).
Further, a plurality of guide plates which are arranged in parallel are arranged in the airflow compression section; a gap is reserved between the adjacent guide plates.
Further, the test section is a rectangular pipeline.
Further, the pipe wall of the test section is a high-temperature alloy steel pipe wall.
Further, an openable observation window is arranged on the side face of the test section.
Further, the thermocouple socket is arranged on an observation window of the test section.
Further, the exhaust section comprises a first exhaust section and a second exhaust section which are connected, and the connection angle of the first exhaust section and the second exhaust section is 120 degrees.
Further, the device also comprises a base bracket; the base support is fixedly connected with the bottom surface of the test section.
The working principle and the advantages of the utility model are as follows: the air inlet section, the air flow compression section, the test section and the exhaust section are assembled and connected with the variable speed fan; installing a plate to be tested in a test section, and arranging thermocouples through a thermocouple socket arranged to be used for measuring the temperature change condition of the back of the plate to be tested in the test; and then, a burner is adopted to spray flame to the plate to be tested, a variable speed fan is started, the wind speed condition required by the test is regulated, and further, the fire resistance test and the temperature measurement of the plate under the high-speed air flow condition at the back are carried out. In the process, the anemometer at the inlet end of the test section can detect the wind speed condition at the test section in real time, and is matched with the variable speed fan, so that the real-time detection and the adjustment of wind speed are facilitated; the fireproof condition of the plate can be observed in real time through the arranged openable and closable observation window; the thermocouple arranged through the thermocouple socket can measure the temperature in real time and collect sufficient experimental data.
The experimental system for the fire test and the temperature measurement of the plate under the high-speed back air flow condition can be used for constructing and obtaining the fire test environment suitable for the aviation plate, can synchronously finish the test and temperature measurement, has higher test efficiency, can truly simulate the environment of the aviation plate in a fire state, has higher test scene fidelity and reliable test result. In addition, each section of structure in the system can be detachably connected, so that the system is convenient to disassemble, assemble and maintain; the variable speed fan is adopted, and the anemometer is arranged, so that the wind speed can be flexibly adjusted and confirmed, and the adjustment is convenient; the thermocouple socket provides space for thermocouple installation, is convenient for temperature measurement in the experiment, and the controllability of the whole experiment system is stronger. In addition, the air flow compression section is specially arranged in the system, so that the wind speed can be greatly improved, and the wind speed requirement of a test can be effectively met; and in addition, by matching with the airflow compression section, a smaller fan can be selected, and the test cost is lower.
Drawings
FIG. 1 is a schematic diagram of the overall structure of a first embodiment of the system for testing fire resistance and measuring temperature of a board under a high-speed back air flow condition;
FIG. 2 is a front view of a system of an embodiment of the utility model for fire testing and temperature measurement of a board under high velocity back air flow conditions;
FIG. 3 is a left side view of a system of an embodiment of the present utility model for fire testing and thermometry of board materials under high velocity back air flow conditions;
FIG. 4 is a top view of a first embodiment of the system of the present utility model for testing and measuring fire of a panel under high velocity back air flow conditions.
Detailed Description
The following is a further detailed description of the embodiments:
the labels in the drawings of this specification include: the air flow compression section 1, the air inlet 11, the compression port 12, the guide plate 13, the test section 2, the anemometer 21, the observation window 22, the thermocouple socket 23, the test surface 24, the first exhaust section 31, the second exhaust section 32 and the base bracket 4.
Example 1
An example is substantially as shown in figure 1: the experimental system for fire resistance test and temperature measurement of the plate under the back high-speed air flow condition comprises an air inlet section, a test section 2, an air outlet section and a base support 4. An air flow compression section 1 is arranged between the air inlet section and the test section 2; the area of the compression opening 12 of the air flow compression section 1 is smaller than the area of the air inlet 11 of the air flow compression section 1, and the areas are in a preset ratio. Specifically, the preset ratio is the area of the compression port 12 of the air flow compression section 1: inlet 11 area of air flow compression section 1 = 1: (1.50-1.60). Under the preset ratio, the wind speed of the airflow compression section 1 is improved, and the wind speed can be rapidly improved.
And the air inlet section, the air flow compression section 1, the test section 2 and the exhaust section are detachably connected. In this embodiment, each section realizes firm detachable connection through the bolt, and the equipment is convenient. The air inlet section is connected with the variable frequency fan; specifically, in this embodiment, the air inlet section is a ventilation pipe, the air inlet end of the ventilation pipe is connected to the variable frequency fan, and the air outlet end of the ventilation pipe is connected to the air inlet 11 of the airflow compression section 1. The variable frequency fan is adopted to conveniently adjust the wind speed and the air inlet quantity, and can adapt to different test requirements.
As shown in fig. 2 and 3, a plurality of parallel flow deflectors 13 are arranged in the airflow compression section 1; a gap is left between adjacent deflectors 13. Specifically, the guide plates 13 are arranged parallel to the pipe wall of the air flow compression section 1, the gaps between the adjacent guide plates 13 are equal, the gap value is 30mm, the air flow entering the test section 2 in the follow-up process can be ensured to be stable, and the turbulence can be reduced.
As shown in fig. 4, an anemometer 21 is disposed at the inlet end of the test section 2 (corresponding to the outlet of the air flow compression section 1); the anemometer 21 is used to monitor the test wind speed. Specifically, in the embodiment, the pitot tube anemometer 21 is adopted by the anemometer 21, so that the installation is convenient, and the wind speed in the test section 2 can be accurately monitored in the test adjustment process and the formal test process.
The test section 2 is a rectangular pipeline. Specifically, the pipe wall of the test section 2 is a high-temperature alloy steel pipe wall, the heat resistance of the test section 2 is good, deformation is not easy, repeated tests can be carried out, and the service life of the test system is longer. One side of the test section 2 is provided with a thermocouple socket 23, and the opposite side is provided with an opening. Specifically, an openable observation window 22 is arranged on one side surface of the test section 2; the thermocouple sockets 23 are arranged on the observation window of the test section 2, and a plurality of thermocouple sockets 23 are arranged in a cross shape; thermocouples are arranged through the thermocouple sockets 23, so that the temperature change condition of the plate to be tested in the test section 2 can be observed conveniently. In this embodiment, the observation window 22 is an openable and closable observation window with high temperature resistant glass, and the thermocouple socket 23 is provided on the high temperature resistant glass, so that the arrangement condition of the thermocouples can be observed through the glass. The side opposite to the side provided with the observation window is a test surface 24 (i.e. the surface for mounting and matching the board to be tested), and an opening is arranged in the center of the test surface 24. The base support 4 is fixedly connected with the bottom surface of the test section 2.
The exhaust section includes a first exhaust section 31 and a second exhaust section 32 connected, and the connection angle of the first exhaust section 31 and the second exhaust section 32 is 120 °.
In a specific application, the test section 2 is firstly mounted on a workbench, preferably, the workbench can be a vibrating table, so that a vibration test environment can be constructed for the test, and the test section is more fit with the actual application environment of the aircraft panel. And then the air flow compression section 1 and the exhaust section are assembled (connected) with the test section 2, the air inlet section is assembled, the variable speed fan and the air flow compression section 1 are connected through the air inlet section, and the joint positions of the air inlet section, the variable speed fan and the air flow compression section 1 are fastened by adopting a clamp. The plate to be tested is vertically arranged at the test section 2, so that the back surface of the plate to be tested is attached to the test surface 24 and seals the opening, and the C-shaped clamp is used for locking the plate to be tested. The thermocouple is inserted into a thermocouple socket 23 arranged at the observation window 22 of the test section 2, the locking observation window 22 is closed, and the length of the thermocouple is adjusted, so that the end head of the thermocouple is attached to the back surface of the plate to be tested. The burner was positioned at test section 2 such that the flame injection direction of the burner was perpendicular to the sample surface. Preferably, the vibration table is restarted, and the amplitude and the frequency of the vibration table are adjusted according to the test requirement; and the variable speed fan is opened, and the wind speed is adjusted to reach the required test parameters. In this process, the thermocouple monitoring device can be set and turned on synchronously, and the burner is turned on and timed at the same time. And closing the burner, the vibrating table and the fan after the fire prevention test is finished according to the test requirement, and recording test data.
The experimental system for the fireproof test and the temperature measurement of the plate under the back high-speed air flow condition can simulate the air speed condition in the flight process of an airplane, form the back high-speed air flow condition, and synchronously measure the fireproof condition of the plate under the vibration condition and the flame impact condition and the temperature distribution and the change condition on the plate. All the sections of the system are detachably connected, can be detached independently for maintenance or replacement, and are convenient to disassemble, assemble and maintain. In addition, the system is specially provided with the airflow compression section 1 for adjusting the inlet wind speed, so that the wind speed can be rapidly increased, and the wind speed requirement required by the test can be efficiently met; the preset thermocouple socket 23 is matched with the openable observation window 22, so that thermocouple installation, arrangement and debugging are facilitated, and real-time observation of the plate condition is facilitated; the vibrating table can further assist in simulating the flight process of the aircraft, and can construct and obtain an experimental environment with high reality.
Example two
Based on the first embodiment, the preset ratio in this embodiment is taken as the area of the compression port 12 of the air flow compression section 1: inlet 11 area of air flow compression section 1 = 1:1.55.
according to the experimental system for the fireproof test and temperature measurement of the plate under the high-speed back airflow condition, the structural proportion of the airflow compression section 1 is optimally set, the higher wind speed lifting degree can be achieved, the high-speed lifting of the wind speed is realized, the requirement on testing the wind speed is met rapidly, and the testing efficiency is higher.
The foregoing is merely an embodiment of the present utility model, and a specific structure and characteristics of common knowledge in the art, which are well known in the scheme, are not described herein, so that a person of ordinary skill in the art knows all the prior art in the application day or before the priority date of the present utility model, and can know all the prior art in the field, and have the capability of applying the conventional experimental means before the date, so that a person of ordinary skill in the art can complete and implement the present embodiment in combination with his own capability in the light of the present application, and some typical known structures or known methods should not be an obstacle for a person of ordinary skill in the art to implement the present application. It should be noted that modifications and improvements can be made by those skilled in the art without departing from the structure of the present utility model, and these should also be considered as the scope of the present utility model, which does not affect the effect of the implementation of the present utility model and the utility of the patent.
Claims (10)
1. The experimental system for fireproof test and temperature measurement of the plate under the high-speed back air flow condition comprises an air inlet section, a test section and an exhaust section, and is characterized in that an air flow compression section is further arranged between the air inlet section and the test section; the area of the compression opening of the airflow compression section is smaller than the area of the air inlet of the airflow compression section, and the areas of the compression opening and the air inlet of the airflow compression section are in a preset ratio; the air inlet section is connected with the variable frequency fan; one side of the test section is provided with a thermocouple socket, and the opposite side of the test section is provided with an opening; and the air inlet section, the air flow compression section, the test section and the exhaust section are detachably connected.
2. The experimental system for fire testing and temperature measurement of boards under high-speed back air flow condition according to claim 1, wherein an anemometer is arranged at the inlet end of the test section; the anemometer is used for monitoring the test wind speed.
3. The experimental system for fire testing and temperature measurement of boards under the condition of high-speed airflow on the back of the board according to claim 1, wherein the preset ratio is the area of a compression opening of a compression section of the airflow: inlet area of air flow compression section = 1: (1.50-1.60).
4. The experimental system for fire testing and temperature measurement of boards under the condition of high-speed back air flow according to claim 1, wherein a plurality of parallel flow guide plates are arranged in the air flow compression section; a gap is reserved between the adjacent guide plates.
5. The system for fire testing and temperature measurement of board under high-speed back air flow condition of claim 1, wherein the test section is a rectangular pipeline.
6. The experimental system for fire testing and temperature measurement of boards under high-speed back air flow condition according to claim 5, wherein the pipe wall of the test section is a high-temperature alloy steel pipe wall.
7. The experimental system for fire testing and temperature measurement of boards under high-speed back air flow condition according to claim 5, wherein an openable observation window is arranged on the side surface of the test section.
8. The system for fire testing and temperature measurement of board under high-speed back air flow condition of claim 7, wherein the thermocouple socket is arranged on an observation window of the test section.
9. The system of claim 1, wherein the exhaust section comprises a first exhaust section and a second exhaust section connected to each other, and the connection angle between the first exhaust section and the second exhaust section is 120 °.
10. The experimental system for fire testing and temperature measurement of boards under high-speed back air flow condition of claim 1, further comprising a base bracket; the base support is fixedly connected with the bottom surface of the test section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320794337.9U CN219475518U (en) | 2023-04-11 | 2023-04-11 | Experimental system for plate fireproof test and temperature measurement under back high-speed air flow condition |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320794337.9U CN219475518U (en) | 2023-04-11 | 2023-04-11 | Experimental system for plate fireproof test and temperature measurement under back high-speed air flow condition |
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| Publication Number | Publication Date |
|---|---|
| CN219475518U true CN219475518U (en) | 2023-08-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320794337.9U Active CN219475518U (en) | 2023-04-11 | 2023-04-11 | Experimental system for plate fireproof test and temperature measurement under back high-speed air flow condition |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219475518U (en) |
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2023
- 2023-04-11 CN CN202320794337.9U patent/CN219475518U/en active Active
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