Premix gas laminar combustion device and installation method thereof

Abstract

The present application relates to a kind of premixed gas laminar flow combustion device and its installation method, the device includes injection mechanism, first straight pipe and flow stabilizing mechanism, injection mechanism and flow stabilizing mechanism are respectively installed and communicated in the bottom end of first straight pipe and the top end of first straight pipe;The length of first straight pipe is 50cm-70cm;Injection mechanism at least includes second injection panel, the top end of second injection panel is provided with a plurality of first injection pipe and a plurality of second injection pipe in staggered arrangement, first injection pipe and second injection pipe are independently arranged, the gas outlet end of first injection pipe and second injection pipe is communicated with the bottom end of first straight pipe, the gas inlet end of first injection pipe and second injection pipe is used to pass into combustion agent and oxidant respectively.The present application can form stable laminar flame, avoids backfire phenomenon, ensures safety, also can avoid flame to be interfered by space airflow, guarantees the accuracy of laminar flow combustion test.

Description

Technical Field

[0001] This invention relates to the field of laminar flow combustion technology, and in particular to a premixed gas laminar flow combustion device and its installation method. Background Technology

[0002] Laminar combustion refers to the combustion process of combustible gases or gas mixtures under laminar flow conditions. Its characteristic is that the flow of fuel (fuel) and oxidizer exhibits a regular, stratified motion, without the disorderly disturbance of turbulence. Laminar combustion devices have advantages such as ease of operation, simple structure, and suitability for research. Therefore, they are frequently used in the field of combustion and in the study of the flame characteristics of various combustible gases, especially in the study of laminar combustion characteristics.

[0003] However, existing laminar flow combustion devices have at least the following drawbacks: 1. Existing laminar flow combustion devices cannot effectively mix the propellant and oxidant, which makes it easy for the flame pattern formed after combustion to have unclear stratification or pulsation, thus failing to form a stable laminar flow flame.

[0004] 2. In existing laminar flow combustion devices, the flame is easily disturbed by the airflow in the space during the test, which leads to instability of the flow field near the flame. This makes it difficult to observe the combustion phenomenon and thus cannot guarantee the accuracy of the laminar flow combustion test.

[0005] 3. Existing laminar flow combustion devices are prone to backfire after the test, which can cause popping and noise, and may even cause an explosion, thus failing to guarantee safety.

[0006] Therefore, how to fully mix the propellant and oxidizer to form a stable laminar flame, stabilize the flow field near the flame, and avoid backfire has become an urgent problem to be solved. Summary of the Invention

[0007] The purpose of this invention is to provide a premixed gas laminar flow combustion device and its installation method to solve the problems existing in the prior art.

[0008] To achieve the above objectives, the present invention provides the following solution: A first aspect of the present invention provides a premixed gas laminar flow combustion device, comprising an injection mechanism, a first straight pipe, and a flow stabilizing mechanism, wherein: The injection mechanism and the flow stabilizing mechanism are respectively installed and connected at the bottom end and the top end of the first straight pipe. The flow stabilizing mechanism is configured to allow the introduction of a flow stabilizing agent to stabilize the flow field near the flame. The length of the first straight pipe is 50cm-70cm; The injection mechanism includes at least a second injection panel. Several first injection pipes and several second injection pipes are installed on the top of the second injection panel in a staggered manner. The first injection pipes and the second injection pipes are set independently. The air outlets of the first injection pipes and the second injection pipes are connected to the bottom end of the first straight pipe. The air inlet ends of the first injection pipes and the second injection pipes are used to introduce the propellant and the oxidizer, respectively.

[0009] According to one embodiment of the present invention, the injection mechanism further includes a first injection panel, and the second injection panel is detachably mounted on the top of the first injection panel; The bottom end of the second injection panel is provided with a second injection annular groove that communicates with the air inlet end of the second injection pipe, and the second injection panel is provided with a second connecting hole that communicates with the second injection annular groove. The top of the first injection panel is provided with a first injection annular groove. When the second injection panel is installed on the top of the first injection panel, the first injection annular groove is connected to the air inlet end of the first injection pipe. The first injection annular groove and the second injection annular groove are independently set. The first injection panel is provided with a first connecting hole connected to the first injection annular groove. The first connecting hole and the second connecting hole are used to introduce the propellant and the oxidant, respectively.

[0010] According to one embodiment of the present invention, a first air inlet pipe and a second air inlet pipe are respectively installed on the first injection panel and the second injection panel. The first air inlet pipe and the second air inlet pipe are respectively connected to the first connecting hole and the second connecting hole. The first air inlet pipe and the second air inlet pipe are respectively used to introduce a propellant and an oxidant.

[0011] According to one embodiment of the present invention, there are several first injection annular grooves and several second injection annular grooves, the several first injection annular grooves are interconnected through the first connecting hole, and the several second injection annular grooves are interconnected through the second connecting hole.

[0012] According to one embodiment of the present invention, a high-temperature resistant sealing layer is provided between the first injection panel and the second injection panel.

[0013] According to one embodiment of the present invention, a connecting housing is installed and connected to the bottom end of the first straight pipe, the bottom end of the connecting housing is connected to the second injection panel, and the air outlet ends of the first injection pipe and the second injection pipe are both connected to the bottom end of the connecting housing.

[0014] According to one embodiment of the present invention, the current stabilizing mechanism includes a current stabilizing housing, a second straight pipe is coaxially mounted and communicated with the top end of the first straight pipe, the cross-sectional diameter of the second straight pipe is smaller than the cross-sectional diameter of the first straight pipe, a mounting hole is provided at the bottom end of the current stabilizing housing, and the second straight pipe is configured to be able to be inserted into the current stabilizing housing through the mounting hole and abut against the inner wall of the mounting hole; The top of the flow stabilizing shell is an open structure and a flow equalization plate is installed. A central through hole is opened at the center of the flow equalization plate, and the inner wall of the central through hole abuts against the outer wall of the second straight pipe. A third air inlet pipe is installed and connected to the side wall of the flow stabilizing housing, and the third air inlet pipe is used to introduce the flow stabilizing agent.

[0015] According to one embodiment of the present invention, the top end of the second straight pipe is flush with the top end of the flow equalization plate.

[0016] According to one embodiment of the present invention, a support mechanism is provided below the first injection panel. The support mechanism includes a support platform and a plurality of legs. The legs are installed at the bottom end of the support platform, and the top end of the support platform is used to place the first injection panel.

[0017] According to one embodiment of the present invention, the support mechanism further includes a placement platform mounted on the support leg.

[0018] A second aspect of the present invention provides a method for installing a premixed gas laminar flow combustion device, comprising the following steps: S1. Install the flow stabilizing mechanism at the top of the first straight pipe; S2. Install several first injection pipes and several second injection pipes on the top of the second injection panel in an alternating arrangement; S3. Install the injection mechanism at the bottom of the first straight pipe so that the air outlets of the first and second injection pipes are connected to the bottom of the first straight pipe.

[0019] This invention has at least the following technical effects: First, the present invention, through the setting of the injection mechanism and the first straight pipe with a length of 50cm-70cm, can make the propellant and oxidant fully mixed, thereby preventing the flame shape formed after combustion from having indistinct stratification or pulsation, thus forming a stable laminar flame.

[0020] Secondly, by using a first straight tube with a length of 50cm-70cm, the present invention can avoid backfire, as well as prevent popping sounds and noise, and thus prevent explosions, ensuring safety.

[0021] Finally, by setting up a flow stabilization mechanism, this invention can avoid the flame being disturbed by the airflow in the space, which would lead to an unstable flow field near the flame. This makes it easier to observe the combustion phenomenon and ensures the accuracy of the laminar combustion test. Attached Figure Description

[0022] To more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. Obviously, the drawings described below are merely some embodiments of the present invention, and those skilled in the art can obtain other drawings based on these drawings without creative effort.

[0023] Figure 1 This is an exemplary overall structural diagram of the present invention; Figure 2 This is a schematic diagram of the overall structure of the exemplary support, legs, and placement platform in this invention. Figure 3 This is a schematic diagram of the overall structure of an exemplary injection mechanism in this invention; Figure 4 This is a schematic diagram of the overall structure of the exemplary first injection panel in this invention; Figure 5 This is a schematic diagram of the overall structure of an exemplary second injection panel in this invention; Figure 6 for Figure 5 An exemplary overall structural diagram from another angle; Figure 7 for Figure 3 An exemplary cross-sectional view of the overall structure; Figure 8 for Figure 3 A schematic diagram of the overall structure in cross-section, as exemplary; Figure 9 This is a schematic diagram of the overall structure of an exemplary connecting housing in this invention; Figure 10 for Figure 9 An exemplary overall structural diagram from another angle; Figure 11 This is a schematic diagram of the overall structure of the exemplary first straight pipe and the second straight pipe in this invention; Figure 12 This is a schematic diagram of the overall structure of an exemplary current stabilizing mechanism in this invention; Figure 13 for Figure 12 An exemplary overall structural diagram from another angle; Figure 14 for Figure 12 An exemplary cross-sectional schematic diagram of the overall structure; Explanation of reference numerals in the attached figures: 1. Support; 2. Support leg; 3. Placement platform; 4. First injection panel; 5. First air inlet pipe; 6. First injection annular groove; 7. First connecting hole; 8. First injection pipe; 9. Second injection panel; 10. Second air inlet pipe; 11. Second injection annular groove; 12. Second connecting hole; 13. Second injection pipe; 14. Connecting housing; 15. First straight pipe; 16. Flow stabilizing housing; 17. Third air inlet pipe; 18. Flow equalization plate; 19. Second straight pipe; 20. Mounting hole; 21. Center through hole of flow equalization plate. Detailed Implementation

[0024] The features and exemplary embodiments of various aspects of the present invention will now be described in detail. To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention and to exemplify the principles of the present invention, and are not configured to limit the present invention. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or regions in the drawings may be enlarged for other structural components or regions to aid in the understanding of the embodiments of the present invention.

[0025] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise stated, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the present invention according to the specific circumstances.

[0026] Furthermore, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure or component that includes a list of elements includes not only those elements but also other structural elements that are not expressly listed or inherent to the structure or component. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the article or apparatus that includes the element.

[0027] Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for descriptive convenience to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device, in addition to those different from those shown in the figure. Furthermore, phrases such as "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first" and "second" are also used to describe individual elements, areas, parts, etc., without specifically indicating order or sequence, and should not be considered restrictive. Similar terms are used throughout the description to represent similar elements.

[0028] It will be apparent to those skilled in the art that the present invention can be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention.

[0029] For ease of description, the description in this embodiment may include terms such as "this device". Those skilled in the art should understand that "this device" refers to a premixed gas laminar flow combustion device provided by the present invention.

[0030] Reference Figure 1-14 In a first aspect, the present invention provides a premixed gas laminar flow combustion apparatus, the apparatus comprising at least an injection mechanism, a first straight pipe 15, and a flow stabilizing mechanism, wherein: Reference Figure 1 The injection mechanism and the flow stabilizing mechanism are respectively installed and connected to the bottom end and the top end of the first straight tube 15. The flow stabilizing mechanism is designed to allow the flow stabilizing agent to be introduced so as to stabilize the flow field near the flame, which in turn facilitates the observation of combustion phenomena and ensures the accuracy of the laminar combustion test.

[0031] In this embodiment, the flow stabilizer can be an inert gas known in the art, such as nitrogen, and is not particularly limited herein.

[0032] According to one embodiment of the present invention, the length of the first straight tube 15 is 50cm-70cm, preferably 60cm. The first straight tube 15 with a length of 50cm-70cm effectively avoids backfire after the test, and also avoids causing popping sounds and noise, thereby preventing explosion and ensuring safety.

[0033] In this embodiment, refer to Figure 11 The first straight tube 15 can be a cylindrical structure. The inner diameter of the first straight tube 15 can be 20cm ± 1cm, preferably 20cm; the wall thickness of the first straight tube 15 can be less than 2mm, preferably 2mm.

[0034] According to one embodiment of the present invention, referring to Figure 3 Specifically, the injection mechanism includes at least a second injection panel 9. Several first injection pipes 8 and several second injection pipes 13 are installed on the top of the second injection panel 9 in a staggered arrangement. The first injection pipes 8 and second injection pipes 13 are not interconnected; that is, the first injection pipes 8 and second injection pipes 13 are independently configured. The air outlets of the first injection pipes 8 and second injection pipes 13 (i.e.,...) Figure 3 The top ends of the first injection pipe 8 and the second injection pipe 13 are both connected to the bottom end of the first straight pipe 15. The air inlet ends of the first injection pipe 8 and the second injection pipe 13 are used to introduce the propellant and the oxidant, respectively.

[0035] In this embodiment, the propellant can be methane gas, which is known in the art, and the oxidant can be oxygen, which is known in the art; neither is particularly limited here.

[0036] In this embodiment, the staggered arrangement of several first injection pipes 8 and several second injection pipes 13 within the injection mechanism (that is, several first injection pipes 8 and several second injection pipes 13 installed at the top of the second injection panel 9 in a staggered manner) allows the propellant and oxidant to be fully mixed, thus preventing the flame pattern formed after combustion from exhibiting indistinct stratification or pulsation, and enabling the formation of a stable laminar flame.

[0037] In addition, the first straight tube 15, which is 50cm-70cm in length, allows the propellant and oxidant to be mixed more thoroughly within the first straight tube 15, thereby further ensuring the stability of the laminar flame.

[0038] According to one embodiment of the present invention, referring to Figures 3-6 The injection mechanism further includes a first injection panel 4, and a second injection panel 9 is detachably mounted on top of the first injection panel 4.

[0039] In this embodiment, refer to Figure 6 Four threaded holes are provided at the same angle on the edge of the second injection panel 9, and four threaded holes (not shown in the figure) can also be provided at the corresponding position of the first injection panel 4. Thus, the second injection panel 9 can be installed on the top of the first injection panel 4 by bolts known in the art.

[0040] In this embodiment, refer to Figure 5 and Figure 6 The first injection pipe 8 and the second injection pipe 13 are both installed vertically at the top of the second injection panel 9.

[0041] In this embodiment, the first injection panel 4 and the second injection panel 9 can both be flat cylindrical structures, and the cross-sectional diameters of the first injection panel 4 and the second injection panel 9 are the same.

[0042] In this embodiment, the installation method between the first injection pipe 8 and the second injection panel 9, and between the second injection pipe 13 and the second injection panel 9, can both be detachably connected by threads. For example, the bottom ends of the first injection pipe 8 and the second injection pipe 13 are provided with external threads (not shown in the figure), and the top end of the second injection panel 9 is provided with a plurality of internal threaded holes respectively corresponding to the first injection pipe 8 and the second injection pipe 13. Thus, the first injection pipe 8 and the second injection pipe 13 can be detachably connected to the second injection panel 9 by threads.

[0043] Furthermore, a high-temperature resistant sealant known in the art, such as polyimide sealant, is applied to the threaded connections between the first injection pipe 8 and the second injection panel 9, and between the second injection pipe 13 and the second injection panel 9. No particular limitation is made here. This improves the sealing performance between the first injection pipe 8 and the second injection panel 9, and between the second injection pipe 13 and the second injection panel 9.

[0044] According to one embodiment of the present invention, referring to Figure 6 The bottom end of the second injection panel 9 is provided with a second injection annular groove 11 that is connected to the air inlet end (i.e. the bottom end of the second injection pipe 13). The second injection panel 9 is provided with a second connecting hole 12 that is connected to the second injection annular groove 11, and the end of the second connecting hole 12 away from the second injection annular groove 11 is connected to the outside of the second injection panel 9.

[0045] Reference Figure 4 The top of the first injection panel 4 is provided with a first injection annular groove 6. When the second injection panel 9 is installed on the top of the first injection panel 4 (i.e., the first injection panel 4 and the second injection panel 9 are in the same position), the second injection panel 9 is in the same position. Figure 3 In the current state, the first injection annular groove 6 is connected to the air inlet end of the first injection pipe 8 (i.e., the bottom end of the first injection pipe 8), and the first injection annular groove 6 is not connected to the second injection annular groove 11. That is, the first injection annular groove 6 and the second injection annular groove 11 are independently set (refer to...). Figure 7 and Figure 8 The first injection panel 4 has a first connecting hole 7 that communicates with the first injection annular groove 6, and the end of the first connecting hole 7 away from the first injection annular groove 6 communicates with the outside of the first injection panel 4.

[0046] In this embodiment, the first connecting hole 7 and the second connecting hole 12 are used to introduce a propellant and an oxidant, respectively. Those skilled in the art should understand that the above description does not specifically limit the first connecting hole 7 to only allowing propellant to be introduced and the second connecting hole 12 to only allowing oxidant to be introduced. That is, the above content is merely one embodiment of the present invention; in other words, an oxidant can also be introduced into the first connecting hole 7 and a propellant into the second connecting hole 12.

[0047] In this embodiment, the cross-section of the first injection annular groove 6 and the second injection annular groove 11 can both be rectangular, and their overall structure can both be a perfect circular ring.

[0048] According to one embodiment of the present invention, referring to Figure 3-6 The first injection panel 4 and the second injection panel 9 are respectively equipped with a first air inlet pipe 5 and a second air inlet pipe 10. The first air inlet pipe 5 and the second air inlet pipe 10 are respectively connected to the first connecting hole 7 and the second connecting hole 12. The first air inlet pipe 5 and the second air inlet pipe 10 are respectively used to introduce the propellant and the oxidizer.

[0049] In this embodiment, refer to Figure 4 There can be two first air intake pipes 5, and the two first air intake pipes 5 can be arranged symmetrically on the side wall of the first injection panel 4. (Refer to...) Figure 6 The number of second air intake pipes 10 can also be two, and the two second air intake pipes 10 can be arranged symmetrically on the side wall of the second injection panel 9. (Refer to...) Figure 3 Viewed from the axial direction of the second injection panel 9, the two first air intake pipes 5 and the two second air intake pipes 10 form a cross-shaped structure.

[0050] In this embodiment, the arrangement of the first air inlet pipe 5 and the second air inlet pipe 10 facilitates the introduction of the propellant and oxidant into the device. Furthermore, the arrangement of two first air inlet pipes 5 and two second air inlet pipes 10 increases the intake volume of the propellant and oxidant.

[0051] According to one embodiment of the present invention, referring to Figure 4 and Figure 6 There are several first injection annular grooves 6 and several second injection annular grooves 11. The several first injection annular grooves 6 are interconnected through a first connecting hole 7, and the several second injection annular grooves 11 are interconnected through a second connecting hole 12.

[0052] In this embodiment, refer to Figure 4The number of first injection annular grooves 6 can be two, and one of the first injection annular grooves 6 is a larger annular structure, while the other first injection annular groove 6 is a smaller annular structure. At the same time, the two first injection annular grooves 6 are coaxially arranged.

[0053] In this embodiment, refer to Figure 6 The number of second injection annular grooves 11 can also be two, with one second injection annular groove 11 being a larger annular structure and the other second injection annular groove 11 being a smaller annular structure. At the same time, the two second injection annular grooves 11 are coaxially arranged.

[0054] In this embodiment, refer to Figure 6 Since the first injection annular groove 6 is connected to the first injection pipe 8, and the second injection annular groove 11 is connected to the second injection pipe 13, the two first injection annular grooves 6 and the two second injection annular grooves 11 can be configured as nested structures. For example, as... Figure 6 As shown, a larger second injection annular groove 11, a larger first injection annular groove 6, a smaller second injection annular groove 11, and a smaller first injection annular groove 6 can be sequentially arranged from the outside to the inside of the second injection panel 9. Wherein, as... Figure 6 As shown, since the first injection pipe 8 and the second injection pipe 13 are arranged alternately, the second connecting hole 12 will not connect with the first injection annular groove 6 even if it can connect the two second injection annular grooves 11.

[0055] In this embodiment, refer to Figure 5 The number of second injection pipes 13 in the larger circle can be 24, and the number of second injection pipes 13 in the smaller circle can be 12; the number of first injection pipes 8 in the larger circle can be 18, and the number of first injection pipes 8 in the smaller circle can be 6.

[0056] Furthermore, in this embodiment, reference is made to Figure 5 and Figure 6 A separate second injection pipe 13 can also be installed at the center of the second injection panel 9. In this case, the first injection pipe 8 and the second injection pipe 13 form a total of five layers (five rings) on the second injection panel 9, which constitutes the staggered arrangement mentioned above.

[0057] Furthermore, a high-temperature resistant sealing layer (not shown in the figure) is provided between the first injection panel 4 and the second injection panel 9.

[0058] Specifically, refer to Figure 6The high-temperature resistant sealing layer can be disposed between the first injection annular groove 6 and the second injection annular groove 11, and also at the edge of the outermost second injection annular groove 11. This improves the isolation between the first injection annular groove 6 and the second injection annular groove 11, and also improves the overall sealing performance of the injection mechanism. The material of the high-temperature resistant sealing layer can be any high-temperature resistant material known in the art that can provide a sealing function, such as fluororubber or silicone rubber, and is not particularly limited herein.

[0059] According to one embodiment of the present invention, referring to Figure 1 , Figure 9 and Figure 10 The bottom end of the first straight pipe 15 is installed and connected to a connecting housing 14. The bottom end of the connecting housing 14 is connected to the second injection panel 9. The air outlets of the first injection pipe 8 and the second injection pipe 13 (i.e., Figure 5 The top ends of the first injection pipe 8 and the second injection pipe 13 are both connected to the bottom end of the connecting housing 14.

[0060] In this embodiment, refer to Figure 9 The connecting shell 14 can be a hollow cylindrical structure with a conical top.

[0061] In this embodiment, refer to Figure 10 The outer diameter of the bottom end of the connecting housing 14 can be the same as the diameter of the second injection panel 9, and the connecting housing 14 can also be connected to the second injection panel 9 by bolts. At this time, the air outlets of the first injection pipe 8 and the second injection pipe 13 will be located inside the connecting housing 14, thereby realizing the connection between the air outlets of the first injection pipe 8 and the second injection pipe 13 and the connecting housing 14.

[0062] In this embodiment, refer to Figure 9 and Figure 11 Flanges are provided at the bottom end of the first straight pipe 15 and the top end of the connecting housing 14, so that the two can be connected by the flanges.

[0063] In addition, the aforementioned high-temperature resistant sealing layer can also be provided between the connecting housing 14 and the first straight pipe 15, and between the connecting housing 14 and the second injection panel 9, thereby improving the sealing performance of the device, which will not be elaborated here.

[0064] According to one embodiment of the present invention, referring to Figure 12-14 The flow stabilizing mechanism includes a flow stabilizing housing 16. (Refer to...) Figure 11The top end of the first straight pipe 15 is coaxially mounted and connected to a second straight pipe 19. The cross-sectional diameter of the second straight pipe 19 is smaller than that of the first straight pipe 15. The bottom end of the flow stabilizing housing 16 is provided with a mounting hole 20. The second straight pipe 19 is configured to be able to be inserted into the flow stabilizing housing 16 through the mounting hole 20 and abut against the inner wall of the mounting hole 20.

[0065] In this embodiment, both the flow-stabilizing housing 16 and the second straight pipe 19 can be hollow and cylindrical. (Refer to...) Figure 11 The second straight pipe 19 forms a stepped structure with the first straight pipe 15. When the first straight pipe 15 is connected to the flow stabilizing housing 16, the top end of the first straight pipe 15 abuts against the bottom end of the flow stabilizing housing 16. Preferably, the top end of the second straight pipe 19 is flush with the top end of the flow equalization plate 18 (not shown in the figure).

[0066] In this embodiment, the high-temperature resistant sealing layer described above can also be provided between the inner wall of the mounting hole 20 and the outer wall of the second straight pipe 19, and the first straight pipe 15 and the flow stabilizing housing 16 can also be connected by bolts, which will not be elaborated here.

[0067] Reference Figure 12 and Figure 14 The top of the flow stabilizing housing 16 is an open structure and a flow equalization plate 18 is installed. A flow equalization plate central through hole 21 is opened at the center of the flow equalization plate 18. The inner wall of the flow equalization plate central through hole 21 abuts against the outer wall of the second straight pipe 19. That is, after the second straight pipe 19 is inserted into the flow stabilizing housing 16, the outer wall of the second straight pipe 19 will also abut against the inner wall of the flow equalization plate central through hole 21.

[0068] In this embodiment, the flow stabilizing housing 16 and the flow equalizing plate 18 can also be connected by bolts, which will not be elaborated here. The specific structure of the flow equalizing plate 18 can be found in [reference needed]. Figure 14 It can be filled with an array of small holes (i.e., flow equalization holes), thereby achieving the effect of equalizing the flow of inert gas.

[0069] In this embodiment, the material of the flow equalization plate 18 can be sintered copper sheet known in the art, and is not particularly limited here.

[0070] In this embodiment, refer to Figure 14 The flow equalization plate 18 can be a three-layer structure.

[0071] According to one embodiment of the present invention, referring to Figure 14 A third air inlet pipe 17 is installed and connected to the side wall of the flow stabilizer housing 16. The third air inlet pipe 17 is used to introduce the flow stabilizer. Therefore, the third air inlet pipe 17 is not connected to the second straight pipe 19.

[0072] In this embodiment, there can be two third air intake pipes 17, which are arranged symmetrically on the side wall of the flow stabilizing housing 16.

[0073] In this embodiment, since the inner wall of the central through hole 21 of the flow equalization plate also abuts against the outer wall of the second straight pipe 19, the second straight pipe 19 will not be connected to the interior of the flow stabilizing housing 16, that is, the third air intake pipe 17 will not be connected to the second straight pipe 19.

[0074] During laminar flow combustion tests, the propellant (methane gas) inside the second straight pipe 19 can be ignited at the top of the second straight pipe 19 (i.e., at a position flush with the top of the flow equalization plate 18), while simultaneously introducing a flow stabilizer into the third inlet pipe 17. At this time, the flow stabilizer (nitrogen gas) introduced into the third inlet pipe 17 will be evenly distributed through the flow equalization plate 18 and then blown out from the flow equalization plate 18, forming a gas layer (i.e., a structure similar to a wind wall) around the flame burning at the top of the second straight pipe 19. This effectively blocks the airflow in the space, thereby preventing the airflow from interfering with the flow field near the flame and facilitating the observation of combustion phenomena. The method of igniting the propellant in the second straight pipe 19 is not particularly limited; any ignition method known in the art suitable for laminar flow combustion can be used.

[0075] According to one embodiment of the present invention, referring to Figure 1 and Figure 2 A support mechanism is provided below the first injection panel 4. The support mechanism includes a support platform 1 and several support legs 2. The support legs 2 are installed at the bottom of the support platform 1, and the top of the support platform 1 is used to place the first injection panel 4.

[0076] In this embodiment, the support 1 can be a flat cuboid structure, and the number of legs 2 can be four, which are bolted to the four corners at the bottom of the support 1 in sequence.

[0077] In this embodiment, the support 1 is preferably arranged horizontally, that is, the lengths of the four support legs 2 should be equal.

[0078] In this embodiment, the outrigger 2 can be fixed to the ground using an anchor bolt method known in the art.

[0079] In this embodiment, the bottom end of the first injection panel 4 can also be connected to the top end of the support 1 by means of bolts.

[0080] In one embodiment of the present invention, the device can be placed and supported by the support platform 1 and the support leg 2.

[0081] Furthermore, referring to Figure 2The support mechanism further includes a placement platform 3, which is mounted on the support leg 2, preferably at the middle position of the support leg 2.

[0082] In this embodiment, the placement platform 3 can also be a flat rectangular structure, and it can be bolted to the side wall of the support leg 2. Preferably, the placement platform 3 is arranged parallel to the support platform 1.

[0083] In this embodiment, by setting up the placement platform 3, temporary items needed in the laminar flow combustion test can be placed on the placement platform 3, which improves convenience.

[0084] A second aspect of the present invention provides a method for installing a premixed gas laminar flow combustion device, which includes at least the following steps: S1. Install the flow stabilizing mechanism at the top of the first straight pipe 15.

[0085] In step S1, specifically, firstly, the three flow equalization plates 18 are stacked, ensuring that the flow equalization holes in the three flow equalization plates 18 are all connected. After stacking, the three flow equalization plates 18 are bolted to the top of the inner sidewall of the flow stabilizing housing 16. Then, two third air inlet pipes 17 are installed on the sidewall of the flow stabilizing housing 16, and the third air inlet pipes 17 are connected to the interior of the flow stabilizing housing 16. Finally, the second straight pipe 19 is inserted into the interior of the flow stabilizing housing 16 through the mounting hole 20; the two can also be connected by bolts, thereby installing the flow stabilizing mechanism at the top of the first straight pipe 15.

[0086] S2. Several first injection pipes 8 and several second injection pipes 13 are installed on the top of the second injection panel 9 in an alternating arrangement.

[0087] In step S2, specifically, firstly, 24 second injection pipes 13 are evenly threaded in a circular manner onto the top of the second injection panel 9, forming the first circle from the outside to the inside. Then, 18 first injection pipes 8 are evenly threaded in a circular manner onto the top of the second injection panel 9, forming the second circle from the outside to the inside. Next, 12 second injection pipes 13 are evenly threaded in a circular manner onto the top of the second injection panel 9, forming the third circle from the outside to the inside. Then, 6 first injection pipes 8 are evenly threaded in a circular manner onto the top of the second injection panel 9, forming the fourth circle from the outside to the inside. Finally, one second injection pipe 13 is threaded onto the center of the top of the second injection panel 9, thus completing the installation between the first injection pipes 8, the second injection pipes 13, and the second injection panel 9 (the specific structure after installation can be found in [reference needed]). Figure 5 ).

[0088] After completing the above steps, the first injection panel 4 is bolted to the bottom of the second injection panel 9, and two first air inlet pipes 5 and two second air inlet pipes 10 are installed on the side walls of the first injection panel 4 and the second injection panel 9, respectively.

[0089] S3. Install the injection mechanism at the bottom end of the first straight pipe 15, so that the air outlets of the first injection pipe 8 and the second injection pipe 13 are both connected to the bottom end of the first straight pipe 15.

[0090] In step S3, specifically, firstly, the connecting housing 14 is installed at the bottom end of the first straight pipe 15 by means of a flange connection. Then, the second injection panel 9 and the first injection panel 4, which were assembled in step S2, are installed at the bottom end of the connecting housing 14 by bolts. At this time, the air outlets of the first injection pipe 8 and the second injection pipe 13 (i.e., the top ends of the first injection pipe 8 and the second injection pipe 13) will be located inside the bottom end of the connecting housing 14, thereby realizing that the air outlets of the first injection pipe 8 and the second injection pipe 13 are connected to the bottom end of the first straight pipe 15.

[0091] S4. Propellant and oxidant are introduced into the air inlet ends of the first injection pipe 8 and the second injection pipe 13, respectively.

[0092] In step S4, specifically, a pipe (not shown in the figure) for introducing propellant can be connected to the first air intake pipe 5, and then a pipe (not shown in the figure) for introducing oxidant can be connected to the second injection pipe 13, thereby realizing the introduction of propellant and oxidant.

[0093] S5. Introduce a flow stabilizer into the flow stabilizing mechanism.

[0094] In step S5, specifically, a pipe (not shown in the figure) that can introduce a flow stabilizer can be connected to the third air inlet pipe 17, thereby realizing the introduction of the flow stabilizer.

[0095] The testing process of this device will be briefly described below in conjunction with the above embodiments: First, after the device is installed, install the following components in sequence on the first air inlet pipe 5: a fuel flow meter, a fuel pressure transmitter, a fuel pressure reducing valve, a fuel solenoid valve, a fuel manual shut-off valve, and a fuel storage cylinder (not shown in the figure and all of which are known in the art).

[0096] Then, an oxidant flow meter, an oxidant pressure transmitter, an oxidant pressure reducing valve, an oxidant solenoid valve, an oxidant manual shut-off valve, and an oxidant storage gas cylinder (not shown in the figure and all of which are known in the art) are installed sequentially on the second air inlet pipe 10.

[0097] Then, the following components are installed sequentially on the third air inlet pipe 17: a flow stabilizer flow meter, a flow stabilizer pressure transmitter, a flow stabilizer pressure reducing valve, a flow stabilizer solenoid valve, a flow stabilizer manual shut-off valve, and a flow stabilizer storage gas cylinder (not shown in the figure and all are known in the art).

[0098] Next, a laminar flow combustion test can be conducted, which can be roughly divided into the following steps: Step 1: Open the manual shut-off valves for the oxidizer, propellant, and flow stabilizer.

[0099] Step 2: Open the oxidizer solenoid valve and the fuel solenoid valve.

[0100] Step 3: Based on the theoretical calculation results, adjust the opening of the oxidizer pressure reducing valve and the propellant pressure reducing valve in sequence, while observing the values ​​of the oxidizer flow meter and the propellant flow meter until the theoretical calculation results are achieved.

[0101] Step 4: Ignite the mixture of oxidant and propellant at the top of the second straight pipe 19 and observe the combustion phenomenon.

[0102] Step 5: Open the flow stabilizer solenoid valve.

[0103] Step six: Adjust the pressure reducing valve of the flow stabilizer until the flow field near the flame is uniform and the combustion is stable. Then observe the combustion phenomenon again to complete the laminar flow combustion test.

[0104] Finally, after the test, first close the propellant solenoid valve, then close the oxidizer solenoid valve, and finally close the flow stabilizer solenoid valve to stop all gas from entering the device. After the device temperature drops to room temperature, disconnect all power to completely complete the laminar flow combustion test.

[0105] The above embodiments of the present invention can be combined with each other and have corresponding technical effects.

[0106] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A premixed gas laminar flow combustion device, characterized in that, Includes an injection mechanism, a first straight pipe (15), and a flow stabilizing mechanism, wherein: The injection mechanism and the flow stabilizing mechanism are respectively installed and connected to the bottom end and the top end of the first straight pipe (15). The flow stabilizing mechanism is configured to allow the flow stabilizing agent to be introduced so as to stabilize the flow field near the flame. The length of the first straight tube (15) is 50cm-70cm; The injection mechanism includes at least a second injection panel (9). Several first injection pipes (8) and several second injection pipes (13) are installed on the top of the second injection panel (9) in an alternating manner. The first injection pipes (8) and the second injection pipes (13) are set independently. The air outlets of the first injection pipes (8) and the second injection pipes (13) are connected to the bottom end of the first straight pipe (15). The air inlet ends of the first injection pipes (8) and the second injection pipes (13) are used to introduce the propellant and the oxidant, respectively.

2. The premixed gas laminar flow combustion device according to claim 1, characterized in that, The injection mechanism further includes a first injection panel (4), and a second injection panel (9) is detachably mounted on the top of the first injection panel (4); The bottom end of the second injection panel (9) is provided with a second injection annular groove (11) that is connected to the air inlet end of the second injection pipe (13), and the second injection panel (9) is provided with a second connecting hole (12) that is connected to the second injection annular groove (11). The top of the first injection panel (4) is provided with a first injection annular groove (6). When the second injection panel (9) is installed on the top of the first injection panel (4), the first injection annular groove (6) is connected to the air inlet end of the first injection pipe (8), and the first injection annular groove (6) and the second injection annular groove (11) are independently set. The first injection panel (4) is provided with a first connecting hole (7) connected to the first injection annular groove (6). The first connecting hole (7) and the second connecting hole (12) are used to introduce the combustion agent and the oxidant, respectively.

3. The premixed gas laminar flow combustion device according to claim 2, characterized in that, The first injection panel (4) and the second injection panel (9) are respectively equipped with a first air inlet pipe (5) and a second air inlet pipe (10). The first air inlet pipe (5) and the second air inlet pipe (10) are respectively connected to the first connecting hole (7) and the second connecting hole (12). The first air inlet pipe (5) and the second air inlet pipe (10) are respectively used to introduce the propellant and the oxidant.

4. The premixed gas laminar flow combustion device according to claim 2, characterized in that, The number of the first injection annular groove (6) and the second injection annular groove (11) are both several. The several first injection annular grooves (6) are interconnected through the first connecting hole (7), and the several second injection annular grooves (11) are interconnected through the second connecting hole (12).

5. The premixed gas laminar flow combustion device according to claim 2, characterized in that, A high-temperature resistant sealing layer is provided between the first injection panel (4) and the second injection panel (9).

6. The premixed gas laminar flow combustion device according to claim 2, characterized in that, The bottom end of the first straight pipe (15) is installed and connected to a connecting housing (14). The bottom end of the connecting housing (14) is connected to the second injection panel (9). The air outlets of the first injection pipe (8) and the second injection pipe (13) are both connected to the bottom end of the connecting housing (14).

7. The premixed gas laminar flow combustion device according to claim 1, characterized in that, The flow stabilizing mechanism includes a flow stabilizing housing (16), a second straight pipe (19) is coaxially mounted and connected to the top end of the first straight pipe (15), the cross-sectional diameter of the second straight pipe (19) is smaller than the cross-sectional diameter of the first straight pipe (15), the bottom end of the flow stabilizing housing (16) is provided with a mounting hole (20), and the second straight pipe (19) is configured to be able to be inserted into the flow stabilizing housing (16) through the mounting hole (20) and abut against the inner wall of the mounting hole (20); The top of the flow stabilizing housing (16) is an open structure and a flow equalization plate (18) is installed. A flow equalization plate central through hole (21) is opened at the center of the flow equalization plate (18). The inner wall of the flow equalization plate central through hole (21) abuts against the outer wall of the second straight pipe (19). A third air inlet pipe (17) is installed and connected to the side wall of the flow stabilizer housing (16), and the third air inlet pipe (17) is used to introduce the flow stabilizer.

8. The premixed gas laminar flow combustion device according to claim 7, characterized in that, The top end of the second straight pipe (19) is flush with the top end of the flow equalization plate (18).

9. The premixed gas laminar flow combustion device according to claim 2, characterized in that, A support mechanism is provided below the first injection panel (4). The support mechanism includes at least a support platform (1) and several legs (2). The legs (2) are installed at the bottom of the support platform (1), and the top of the support platform (1) is used to place the first injection panel (4). The support mechanism further includes a placement platform (3) which is mounted on the support leg (2).

10. The installation method of the premixed gas laminar flow combustion device according to any one of claims 1-9, characterized in that, Includes the following steps: S1. Install the flow stabilizing mechanism at the top of the first straight pipe (15); S2. Install several first injection pipes (8) and several second injection pipes (13) on the top of the second injection panel (9) in an alternating arrangement; S3. Install the injection mechanism at the bottom end of the first straight pipe (15) so that the air outlets of the first injection pipe (8) and the second injection pipe (13) are connected to the bottom end of the first straight pipe (15).

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