Building component air tightness testing device

Abstract

The application provides a kind of building component air tightness detection device, it is related to building component detection technical field, to solve the problem of excessive wind speed on the surface of test piece when component air tightness test.The building component air tightness detection device includes outer box body and the deceleration cavity body arranged in the outer box body, the deceleration cavity body is equipped with air inlet and air outlet;On the path of gas flowing from air inlet to air outlet, shunt part and confluence part are provided in the outer box body, the shunt part is arranged towards air inlet and is used to disperse the airflow entering from air inlet, the confluence part is arranged towards air outlet and is used to make the airflow confluence between confluence part and air outlet and then discharge the deceleration cavity body from air outlet.It can reduce the wind speed acting on the surface of test piece when component air tightness test, while maintaining the pressure difference between the inside and outside of test piece, reduce the wind speed on the inner surface of test piece.

Description

Technical Field

[0001] This invention relates to the field of building component testing technology, and more specifically, to a device for testing the airtightness of building components. Background Technology

[0002] Reducing air leakage through the building envelope is a key technical means to lower building energy consumption and reduce carbon emissions during building operation. Improving building airtightness is a crucial step in achieving the "dual carbon" goals in the construction industry. Therefore, accurate testing of the airtightness of buildings and their components is the foundation for the scientific evaluation of airtight products and structures.

[0003] Current methods for testing the airtightness of buildings or their components (such as doors, windows, and curtain walls) primarily utilize pressurization systems to create a specific pressure difference between the inside and outside of the building or across the sides of the component. The airtightness of the component is evaluated by measuring the amount of air leakage under this pressure difference. In daily use, the wind speed on the inner surfaces of a building is relatively low. However, airtightness tests require a significant pressure difference across the component. The pressurization system generates wind speeds on the inner surface of the component that are much higher than under normal usage conditions. This results in significant discrepancies between the test results and the actual leakage situation of the building components. Summary of the Invention

[0004] The first objective of this invention is to provide a device for testing the air tightness of building components, so as to solve the technical problem of high wind speed on the surface of the test piece during existing air tightness testing.

[0005] The first aspect of the present invention provides a building component airtightness testing device, comprising an outer casing and a deceleration chamber disposed in the outer casing, the deceleration chamber having an air inlet and an air outlet; on the path of gas flowing from the air inlet to the air outlet, the deceleration chamber having a diverting part and a converging part, the diverting part being disposed toward the air inlet and used to disperse the airflow entering from the air inlet, the converging part being disposed toward the air outlet and used to allow the airflow to merge between the converging part and the air outlet and then be discharged from the deceleration chamber through the air outlet.

[0006] The beneficial effects of the airtightness testing device for building components of this invention are:

[0007] By setting up a diversion section and a convergence section, the airflow entering from the air inlet can be diffused first, and then the diffused airflow can be merged again. When the airflows merge, the velocities of the merging airflows in the relative velocity directions will cancel each other out, thereby reducing or even eliminating the airflow velocity discharged from the air outlet. This makes the airflow velocity on the inner surface of the test specimen during the airtightness test of the building component closer to the wind speed under actual use conditions, thus improving the accuracy of the airtightness test.

[0008] In an optional technical solution, the deceleration cavity is provided with a flow divider, the flow divider having a first protrusion that protrudes toward the air inlet.

[0009] In an optional technical solution, the first protrusion has a pointed tip, which faces the air inlet.

[0010] In an optional technical solution, the diverter is provided with a tapered portion, and the tip of the tapered portion is the tip portion.

[0011] In an optional technical solution, the diverter has a second protrusion that protrudes toward the air outlet.

[0012] In an optional technical solution, along the flow direction of the airflow in the second protrusion, the angle between the surface of the second protrusion and the protrusion direction of the second protrusion gradually increases.

[0013] In an optional technical solution, the second protrusion is configured such that the airflow flows toward each other on the surface of the second protrusion.

[0014] In an optional technical solution, the deceleration chamber is provided with an outlet wall, the air outlet is disposed on the outlet wall, and the protrusion direction of the outlet wall is consistent with the protrusion direction of the second protrusion.

[0015] In an optional technical solution, the deceleration chamber includes an inlet wall, the air inlet is disposed on the inlet wall, and the inlet wall is parallel to the first protrusion.

[0016] In an optional technical solution, the flow divider and the deceleration chamber are symmetrically arranged along the line connecting the center of the air inlet to the center of the air outlet. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments or background art of the present invention, the drawings used in the description of the embodiments or background art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the structure of the airtightness testing device for building components provided in an embodiment of the present invention;

[0019] Figure 2 This is a schematic diagram of the structure of a building component airtightness testing device provided in another implementation of the present invention;

[0020] Figure 3This is a schematic diagram of the structure of a building component airtightness testing device provided in another implementation of the present invention.

[0021] Explanation of reference numerals in the attached figures:

[0022] 10-Outer box;

[0023] 20 - Deceleration chamber; 21 - Air inlet; 22 - Air outlet; 23 - Inlet wall; 24 - Outlet wall; 25 - Chamfered part;

[0024] 30 - Diverter; 31 - First protrusion; 32 - Second protrusion;

[0025] 40 - Test piece;

[0026] 50 - Sub-cavity; 51 - Sub-inlet. Detailed Implementation

[0027] To make the above-mentioned objects, features, and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

[0028] Example 1:

[0029] Figure 1 This is a schematic diagram of the structure of the airtightness testing device for building components provided in an embodiment of the present invention; as shown. Figure 1 As shown, the airtightness testing device for building components provided in Embodiment 1 of the present invention includes an outer casing 10 and a deceleration chamber 20 disposed in the outer casing 10. The deceleration chamber 20 is provided with an air inlet 21 and an air outlet 22. On the path of gas flowing from the air inlet 21 to the air outlet 22, a diversion section and a converging section are provided in the deceleration chamber 20. The diversion section is disposed towards the air inlet 21 and is used to disperse the airflow entering from the air inlet 21. The converging section is disposed towards the air outlet 22 and is used to make the airflow merge between the converging section and the air outlet 22 and then discharge from the deceleration chamber 20 through the air outlet 22.

[0030] By setting up a diversion section and a convergence section, the airflow entering from the air inlet 21 can be diffused first, and then the diffused airflow can be merged again. When the airflows merge, the velocities of the merged airflows in the relative velocity directions will cancel each other out, thereby reducing or even eliminating the airflow velocity discharged from the air outlet 22. This makes the airflow velocity on the inner surface of the test specimen during the airtightness test of the building component closer to the wind speed under actual use conditions, thus improving the accuracy of the airtightness test.

[0031] Specifically, in this embodiment, the outer casing 10 can be, for example, a rectangular cube or a cubic shape. The side of the outer casing 10 facing the wall has an opening to generate air pressure within the casing 10 to simulate specific test conditions for testing the test piece 40, such as doors, windows, or curtain walls. An air inlet 21 can be provided on the side of the outer casing 10 opposite or adjacent to the wall to accommodate a pressurizing device such as a fan (not shown). When gas is discharged from the air outlet 22 of the deceleration chamber 20, the air pressure inside the outer casing 10 can be maintained.

[0032] Of course, in this embodiment, a deceleration chamber 20 is set inside the outer casing 10 as an example for explanation. In fact, one or more deceleration chambers 20 can be set up in series as needed, for example, according to the gas flow rate of the gas discharged from the pressurizing device and the airflow speed required on the surface of the test piece 40.

[0033] like Figure 1 As shown, the deceleration chamber 20 is provided with a flow divider 30, which has a first protrusion 31 that protrudes toward the air inlet 21.

[0034] By providing a flow divider 30 in the deceleration chamber 20, and providing a first protrusion 31 protruding towards the air inlet 21 on the flow divider 30, the gas entering the deceleration chamber 20 through the air inlet 21 can be diverted in a timely manner using the first protrusion 31, so that the gas flows along the space between the first protrusion 31 and the deceleration chamber 20, forming a stable airflow, and then the dispersed airflows are reunited, thereby ultimately reducing the speed of the gas discharged from the deceleration chamber 20.

[0035] In this embodiment, the flow divider 30 and the deceleration chamber 20 can be connected by a fastener (not shown), and the deceleration chamber 20 can be connected to the outer casing 10 by welding or other means. Specifically, a mesh grille that does not affect gas flow can be provided between the flow divider 30 and the deceleration chamber 20 to fix the flow divider 30.

[0036] Figure 2 This is a schematic diagram of the structure of a building component airtightness testing device provided in another implementation of the present invention; as shown. Figure 2As shown, in another implementation, the flow divider 30 may not have a protrusion, and the inlet 21 and outlet 22 may be located on the same or adjacent sides of the deceleration chamber 20. Taking the inlet 21 and outlet 22 located on adjacent sides of the chamber as an example, for instance, the inlet 21 is located on the upper side of the deceleration chamber 20, and the outlet 22 is located on the right side of the deceleration chamber 20 as shown in the figure. This can change the distance between the corresponding parts of the deceleration chamber 20 and the flow divider 30 between the inlet 21 and the outlet 22, that is, reduce the distance between the chamber wall and the flow divider 30 in the area to the right of the inlet 21 and above the outlet 22, thereby reducing the cross-sectional size of the gas flow channel, controlling the flow rate of gas through this part of the flow channel, and increasing the width of the flow channel to the left of the inlet 21, below the left of the flow divider 30, and below the outlet 22 as shown in the figure. Although some flow channels are shorter and others are longer, the resistance is the same due to the different channel widths, resulting in identical flow rates. This allows the flow rates of the two airflows to be approximately the same, offsetting at least part of their velocities and reducing the velocity of the gas discharged from outlet 22.

[0037] Figure 3 This is a schematic diagram of the structure of a building component airtightness testing device provided in another implementation of the present invention; as shown below. Figure 3 As shown, in another implementation, a sub-cavity 50 is provided in the outer casing 10. The sub-cavity 50 can be a rectangular cavity, and sub-inlet ports 51 are respectively provided on opposite surfaces of the sub-cavity 50. The test piece 40 is located on the surface between these opposite surfaces. The inlet port 21 of the outer casing 10 can face the outside of the other surface between these opposite surfaces. When the airflow enters from the two sub-inlet ports 51, the velocities can be at least partially canceled, thereby reducing the gas velocity and increasing the gas pressure. The sub-cavity 50 can be the deceleration cavity mentioned above, and the flow splitting part is the side surface of the sub-cavity 50 facing the inlet port 21. The interior of the sub-cavity 50 is the confluence part, and the outlet port 22 of the deceleration cavity is located on the test piece.

[0038] like Figure 1 As shown, optionally, the first protrusion 31 is provided with a tip, which faces the air inlet 21.

[0039] By providing a pointed tip on the first protrusion 31 facing the air inlet 21, the airflow entering from the air inlet 21 can encounter the diverter 30 as early as possible, minimizing the resistance of the diverter 30 to the airflow entering from the air inlet 21. This allows the gas to be diverted in an organized manner as early as possible before the gas entering from the air inlet 21 can diffuse freely, increasing the length of the first protrusion 31 of the diverter 30 and the deceleration chamber 20 that together guide and disperse the airflow.

[0040] In other implementations not shown, the first protrusion 31 may not have a pointed tip, for example, it may be a spherical, olive-shaped, or teardrop-shaped front portion, which may also serve to disperse airflow. Alternatively, the cross-section of the first protrusion 31 may be the edge of the cross-section of the above shapes, and the first protrusion 31 may be a solid shape in which the cross-section extends in a direction perpendicular to the cross-section.

[0041] like Figure 1 As shown, optionally, the diverter 30 is provided with a tapered portion, the tip of which is a pointed portion.

[0042] By setting the first protrusion 31 of the diverter 30 into a conical part, and using the tip of the conical part as the tip, the airflow can be uniformly diffused in all circumferential directions at the same amount and speed after encountering the diverter 30, thereby improving the uniformity of the diffused airflow and reducing the airflow velocity at the outlet.

[0043] In this embodiment, the first protrusion 31 can be a conical part, which can be a cone in this embodiment. Of course, in other implementations, the conical part can also be a polygonal pyramid.

[0044] In another implementation, the first protrusion 31 can be a vertically symmetrical structure rather than an axisymmetric shape such as a cone, i.e., a triangular-cubic structure formed by extending the illustrated structure in a direction perpendicular to the paper. Alternatively, the first protrusion 31 can also be bullet-shaped or date-shaped.

[0045] like Figure 1 As shown, optionally, the diverter 30 has a second protrusion 32 that protrudes toward the air outlet 22.

[0046] By providing a second protrusion 32 on the side of the flow divider 30 facing the outlet 22, the airflow can flow along the surface of the second protrusion 32 under the influence of the Coanda effect, thereby reducing the vortex on the side of the flow divider 30 facing the outlet 22 and making the airflow distribution between the second protrusion 32 and the outlet wall 24 more uniform.

[0047] Of course, in another implementation, the side of the diverter 30 facing the air outlet 22 can also be a plane, which can also play the role of making the airflow converge, but the uniformity of the airflow is not as good as the case where the second protrusion 32 is provided.

[0048] like Figure 1 As shown, optionally, along the flow direction of the airflow in the second protrusion 32, the angle between the surface of the second protrusion 32 and the protrusion direction of the second protrusion 32 gradually increases.

[0049] By gradually increasing the angle between the surface of the second protrusion 32 and the protrusion direction, that is, the closer to the center of the second protrusion 32, the larger the angle between the surface and the protrusion direction, the larger the angle between the converging airflows can be, thereby better offsetting the velocity of the airflow itself, so as to form static pressure at the air outlet as much as possible.

[0050] like Figure 1 As shown, the second protrusion 32 protrudes to the right in the figure. The angle between the surface of the second protrusion 32 and the protrusion direction of the second protrusion 32 gradually increases. Along the flow direction of the airflow in the second protrusion 32, the angle between the surface of the second protrusion 32 and the protrusion direction gradually increases, that is, the surface of the second protrusion 32 becomes closer and closer to the vertical state.

[0051] Of course, in another implementation, for example, the surface of the second protrusion 32 can be made to form an angle that is the same as the protrusion direction of the second protrusion 32 along the airflow direction. For example, if the angle is 50° or 20°, the second protrusion 32 can be conical or triangular prism-shaped. This can also make the merging airflow partially cancel each other out, thereby reducing the velocity discharged from the air outlet 22.

[0052] like Figure 1 As shown, optionally, the second protrusion 32 is configured such that airflow flows toward each other on the surface of the second protrusion 32.

[0053] By making the airflow flow in opposite directions on the surface of the second protrusion 32, that is, the velocities of the relatively converging airflows are completely opposite, the velocities can be canceled out as much as possible, thereby significantly reducing the airflow velocity at the outlet 22 to be as close as possible to the airflow conditions during the airtightness test.

[0054] In this context, "relatively converging airflow" refers to airflows that converge, for example, a downward-moving airflow and an upward-moving airflow, or a forward-moving airflow and a backward-moving airflow. Obviously, a downward-moving airflow and a backward-moving airflow cannot constitute a relatively converging airflow.

[0055] In this embodiment, the velocity of the opposing airflows on the surface of the second protrusion 32 when they converge can be reduced as much as possible in the horizontal direction of the diagram. Then, the horizontal velocity component of the airflow after convergence can be reduced as much as possible, thereby reducing the wind speed on the inner surface of the specimen.

[0056] like Figure 1 As shown, optionally, the deceleration chamber 20 is provided with an outlet wall 24, and an air outlet 22 is provided on the outlet wall 24. The protrusion direction of the outlet wall 24 is consistent with the protrusion direction of the second protrusion 32.

[0057] By setting the outlet wall 24, the airflow can be restricted from converging at the center of the second protrusion 32, thereby reducing the velocity component of the air inlet 21 toward the air outlet 22, and thus reducing the air outlet velocity from the air outlet 22.

[0058] Specifically, in this embodiment, the outlet wall 24 can also be an arc surface.

[0059] In this embodiment, the first protrusion 31 and the inlet wall 23 belong to the diversion section, while the second protrusion 32 and the outlet wall 24 belong to the confluence section.

[0060] like Figure 1 As shown, optionally, the deceleration chamber 20 includes an inlet wall 23, an air inlet 21 is disposed on the inlet wall 23, and an airflow channel is formed between the inlet wall 23 and the first protrusion 31.

[0061] By setting the inlet wall 23 and the first protrusion 31, the space between the first protrusion 31 and the inlet wall 23 can be used to guide the airflow, thereby improving the stability of the airflow in each direction that converges at the outlet wall 24, and ultimately reducing the airflow velocity after converging at the outlet 22.

[0062] Specifically, in this embodiment, if the first protrusion 31 is conical, the inlet wall 23 can be a frustum of a cone with the same included angle and coaxially arranged; if the first protrusion 31 is a triangular pyramid, the two planes of the inlet wall 23 forming the included angle are parallel to the surface of the triangular pyramid. Furthermore, a chamfered portion 25 can be provided between the inlet wall 23 and the outlet wall 24 to guide the direction of airflow, and the chamfered portion 25 is provided corresponding to the intersection position of the first protrusion 31 and the second protrusion 32.

[0063] like Figure 1 As shown, optionally, the flow divider 30 and the deceleration chamber 20 are symmetrically arranged along the line connecting the center of the air inlet 21 to the center of the air outlet 22.

[0064] By symmetrically arranging the diverter 30 and the deceleration chamber 20 along the line connecting the center of the inlet 21 to the center of the outlet 22, the airflow dispersed by the diverter 30 can be symmetrical along the line connecting the center of the inlet 21 to the center of the outlet 22. The airflows that converge at the confluence section are also symmetrical, thereby achieving the goal of maximally canceling out the speed of the confluenced airflows and reducing the outlet speed of the outlet 22.

[0065] Specifically, in this embodiment, the first protrusion 31 of the flow divider 30 can be conical and the second protrusion 32 can be spherical, while the inlet wall 23 of the deceleration chamber 20 is frustoconical and the outlet wall 24 is spherical. That is, the axes of the conical, frustoconical, and spherical shapes are coaxially arranged and all point towards the center of the inlet 21 and the center of the outlet 22. In another implementation, if the flow divider 30 and the deceleration chamber 20 have a vertically symmetrical structure, then the center of the inlet 21 and the center of the outlet 22 are on the plane of symmetry.

[0066] The operating principle of this embodiment is as follows:

[0067] like Figure 1 As shown, when the airflow enters from the inlet 21, it is diverted by the first protrusion 31 of the diverter 30 and flows between the inlet wall 23 and the first protrusion 31. After the airflow passes the chamfered portion 25, it is guided by the second protrusion 32 and the outlet wall 24 to flow stably and converge in the space formed between the second protrusion 32 and the outlet wall 24. Since the inlet wall 23 and the first protrusion 31, the outlet wall 24 and the second protrusion 32 are all coaxially arranged, the airflow is also evenly dispersed, and the converging airflow is also relatively uniform. Thus, the airflow converging at the center of the second protrusion 32 is close to the airflow with equal velocity and opposite direction. The kinetic energy of the airflow in each direction will cancel each other out, thereby reducing the airflow velocity and increasing the pressure in the outer cavity 10, so as to form static pressure on the surface of the test piece 40 as close as possible to the actual use state of the test piece 40.

[0068] While the present invention has been disclosed above, it is not limited thereto. Any person skilled in the art can make various modifications and alterations without departing from the spirit and scope of the invention; therefore, the scope of protection of the present invention should be determined by the scope defined in the claims.

[0069] Finally, it should be noted that in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the term "comprising" or any other variations thereof is intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0070] In the above embodiments, descriptions of directions such as "up" and "down" are based on the accompanying drawings.

[0071] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention.

[0072] Therefore, the present invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A device for testing the airtightness of building components, characterized in that, The device includes an outer casing (10) and a deceleration chamber (20) disposed within the outer casing (10). The deceleration chamber (20) is provided with an air inlet (21) and an air outlet (22). The outer casing (10) is configured with an opening on one side facing the wall to generate air pressure simulation test conditions in the outer casing (10) and to test the test piece. In the path of gas flowing from the air inlet (21) to the air outlet (22), a diversion section and a confluence section are provided in the deceleration chamber (20). The diversion section is disposed facing the air inlet (21) and is used to disperse the airflow entering from the air inlet (21). The confluence section is disposed facing the air outlet (22) and is used to allow the airflow to merge between the confluence section and the air outlet (22) and then exit the deceleration chamber (20) from the air outlet (22). The deceleration chamber (20) is provided with a flow divider (30), which has a first protrusion (31) that protrudes toward the air inlet (21).

2. The airtightness testing device for building components according to claim 1, characterized in that, The first protrusion (31) has a pointed tip, which faces the air inlet (21).

3. The airtightness testing device for building components according to claim 2, characterized in that, The diverter (30) is provided with a tapered portion, the tip of which is the tip portion.

4. The airtightness testing device for building components according to any one of claims 1-3, characterized in that, The diverter (30) has a second protrusion (32) that protrudes toward the air outlet (22).

5. The airtightness testing device for building components according to claim 4, characterized in that, Along the flow direction of the airflow in the second protrusion (32), the angle between the surface of the second protrusion (32) and the protrusion direction of the second protrusion (32) gradually increases.

6. The airtightness testing device for building components according to claim 5, characterized in that, The second protrusion (32) is configured such that the airflow flows toward each other on the surface of the second protrusion (32).

7. The airtightness testing device for building components according to claim 4, characterized in that, The deceleration chamber (20) is provided with an outlet wall (24), and the air outlet (22) is provided on the outlet wall (24). The protrusion direction of the outlet wall (24) is consistent with the protrusion direction of the second protrusion (32).

8. The airtightness testing device for building components according to any one of claims 1-3 or any one of claims 5-7, characterized in that, The deceleration chamber (20) includes an inlet wall (23), and the air inlet (21) is disposed on the inlet wall (23). The inlet wall (23) is parallel to the first protrusion (31).

9. The airtightness testing device for building components according to any one of claims 1-3 or any one of claims 5-7, characterized in that, The flow divider (30) and the deceleration chamber (20) are symmetrically arranged along the line connecting the center of the air inlet (21) to the center of the air outlet (22).

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