An annular combustion chamber device for studying high-altitude ignition mechanism

Abstract

The application discloses a kind of high-altitude ignition mechanism research annular combustion chamber device, it is related to the field of aero-engine test device, including support assembly, gas distribution chamber component, annular combustion chamber component, low pressure extraction component and oil supply component, the gas distribution chamber component, annular combustion chamber component and low pressure extraction component are sequentially combined from bottom to top Installation is fixedly connected at the top of the support assembly, the oil supply component is connected in the outside of the gas distribution chamber component, and the working end of the oil supply component extends to the inside of the gas distribution chamber component.The application changes the oil supply flow in fuel manifold and the air flow in annular inlet manifold, realizes the ignition performance test of annular combustion chamber under different working conditions, based on visual quartz glass window, the flame propagation characteristics under different working conditions can be clearly photographed, which is of great significance for analyzing the annular combustion chamber flame-spreading process and flame propagation characteristics.

Description

Technical Field

[0001] This invention relates to the field of aero-engine testing equipment, and more particularly to an annular combustion chamber device for studying high-altitude ignition mechanisms. Background Technology

[0002] High-altitude ignition and restart are common requirements for aero-engine combustion chambers. At high altitudes, due to significantly reduced air pressure, temperature, and density, engine shutdown necessitates rapid ignition to restore power. Numerous factors can cause aero-engines to shut down at high altitudes, including strong turbulence in the combustion chamber inlet airflow, unstable combustion, insufficient instantaneous fuel supply, rain or hail ingestion, and exhaust gas intake. Severe high-altitude engine shutdowns can lead to aircraft crashes; therefore, simulating high-altitude operations is of great significance for the development of aero-engines.

[0003] The high-altitude environment deteriorates flow and spray conditions, making combustion chamber ignition more difficult. The ignition process in an engine combustion chamber involves complex mechanisms, including turbulent flow, chemical combustion, and the coupling of multiple factors. In spray ignition, the atomization, evaporation, and subsequent chemical reactions of the liquid fuel complicate the entire process, making it crucial to predict ignition stability limits and understand flame propagation mechanisms for combustion chamber design.

[0004] To better simulate engine startup at high altitudes and plateau airports, it is necessary to verify the ignition performance of the annular combustor under high-altitude conditions, simulating low-pressure and low-temperature air, and to determine its impact on the ignition performance of the main combustor.

[0005] Therefore, how to provide an annular combustion chamber device for high-altitude ignition mechanism research, and how to achieve ignition performance tests of the annular combustion chamber under different operating conditions by changing the fuel supply flow rate and air flow rate, has become a problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0006] The purpose of this invention is to provide an annular combustion chamber device for studying high-altitude ignition mechanisms. By changing the fuel supply flow rate and air flow rate, the ignition performance of the annular combustion chamber under different operating conditions can be tested.

[0007] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0008] The present invention discloses an annular combustion chamber device for studying high-altitude ignition mechanism, comprising a support assembly, a gas distribution chamber assembly, an annular combustion chamber assembly, a low-pressure extraction assembly, and a fuel supply assembly. The gas distribution chamber assembly, the annular combustion chamber assembly, and the low-pressure extraction assembly are assembled and installed sequentially from bottom to top and fixedly connected to the top of the support assembly. The fuel supply assembly is fitted onto the outside of the gas distribution chamber assembly, and the working end of the fuel supply assembly extends into the interior of the gas distribution chamber assembly.

[0009] Preferably, the support assembly includes a support platform, a bellows support, and a gas distribution chamber support. The gas distribution chamber support is located at the center of the top of the support platform. The top of the gas distribution chamber support is provided with an anti-slip pad. Multiple bellows supports are arranged symmetrically in a circle around the gas distribution chamber support on the top of the support platform. The top of the bellows support is provided with a bellows fixing threaded hole.

[0010] Preferably, the gas distribution chamber assembly includes a first gas distribution chamber, a second gas distribution chamber, an annular intake manifold, a honeycomb plate, and a fourth flange. The first gas distribution chamber is placed on the gas distribution chamber support, and the bottom of the first gas distribution chamber is tightly fitted with the anti-slip pad on the top of the gas distribution chamber support. The annular intake manifold is sleeved on the outside of the first gas distribution chamber and communicates with the inner cavity of the first gas distribution chamber through multiple branch pipes. A first flange is provided on the top of the first gas distribution chamber. A second flange and a third flange are respectively provided at both ends of the second gas distribution chamber. The second gas distribution chamber is fixedly connected to the top of the first gas distribution chamber through the first flange and the second flange. The plate has a placement groove, the honeycomb panel is placed in the placement groove, and is clamped between the first and second gas distribution chambers by the second flange. The second and first gas distribution chambers are interconnected. The fourth flange is fastened to the top of the third flange by bolts. The fourth flange has a plurality of swirl cup interfaces evenly distributed in a circle. The swirl cup interfaces are connected to the inner cavity of the second gas distribution chamber. The top of the fourth flange is also provided with an inner groove, an outer groove, and an oil drain groove. The oil drain groove is connected to the inner groove and the outer groove of the fourth flange, respectively, and extends outward.

[0011] Preferably, a drain valve is provided at the bottom of the first air distribution chamber; a pressure sensor interface for installing a pressure sensor is provided on the periphery of the second air distribution chamber, and the pressure sensor interface is connected to the inner cavity of the second air distribution chamber.

[0012] Preferably, the annular combustion chamber assembly includes an outer combustion chamber wall, an inner combustion chamber wall, a conical guide, and a two-stage swirl cup. The bottom end of the outer combustion chamber wall is snapped into the outer groove of the fourth flange, and the top end of the outer combustion chamber wall is used to support the low-pressure extraction assembly. A spark plug hole is provided on the side wall of the outer combustion chamber wall. The inner combustion chamber wall is disposed in the inner cavity of the outer combustion chamber wall, and the bottom end of the inner combustion chamber wall is snapped into the inner groove of the fourth flange. The top end of the inner combustion chamber wall is sealed with the conical guide. Multiple two-stage swirl cups are respectively installed on the swirl cup interface, and the two-stage swirl cups are connected to the working end of the fuel supply assembly.

[0013] Preferably, the two-stage cyclone cup includes a first-stage cyclone, a second-stage cyclone, a venturi tube, and a sleeve. A nozzle retaining sleeve is provided at the bottom inlet of the first-stage cyclone, and the working end of the oil supply assembly is connected to the nozzle retaining sleeve. The top outlet of the first-stage cyclone is connected to the inlet of the venturi tube. The second-stage cyclone is arranged around the outside of the venturi tube. The bottom of the sleeve is threaded to the top of the second-stage cyclone, and the top of the sleeve is provided with a funnel-shaped opening with an angle of 30° to 90°.

[0014] Preferably, the low-pressure extraction assembly includes a transparent quartz glass plate, a low-pressure extraction tee, a bellows, an I-beam quick-connect fitting, and double-ended bolts. The bellows has a fifth flange and a sixth flange at its two ends, respectively. The fifth flange has an external groove at its bottom and is located on the top of the outer wall of the combustion chamber. It is fastened to the fourth flange by the double-ended bolts. The external groove of the fifth flange is snap-fitted into the top of the outer wall of the combustion chamber. The sixth flange at the top of the bellows is fastened to the bellows support by bolts and the bellows fixing threaded hole. The bottom end of the low-pressure extraction tee is installed on the top end of the bellows. The transparent quartz glass plate is fixedly connected to the top of the main pipe of the low-pressure extraction tee by the I-beam quick-connect fitting. The branch pipes of the low-pressure extraction tee are used to connect to the low-pressure pipeline.

[0015] Preferably, the I-shaped quick connector includes an I-shaped quick connector body, a first clamp, and a second clamp. Both the upper and lower ends of the I-shaped quick connector body are provided with snap-fit ​​protrusions that cooperate with the first clamp and the second clamp. The bottom of the I-shaped quick connector body is fixedly connected to the top of the low-pressure tee main pipe through the first clamp, and the transparent quartz glass plate is fastened to the top of the I-shaped quick connector body through the second clamp.

[0016] Preferably, the fuel supply assembly includes a fuel main pipe, a fuel sub-pipe, a cover plate, and an atomizing nozzle. The fuel main pipe is sleeved on the outside of the second valve distribution chamber. One end of the fuel sub-pipe is connected to the fuel main pipe, and the other end of the fuel sub-pipe passes through the side wall of the second valve distribution chamber and is connected to the nozzle fixing sleeve through the atomizing nozzle. The cover plate fixed on the side wall of the second valve distribution chamber is used to fix the fuel sub-pipe.

[0017] Preferably, the system also includes a shooting assembly, which includes a mirror bracket, a camera bracket, a camera mounting platform, a camera, and a mirror. The mirror bracket is fixedly installed on the top of the support platform, the mirror is installed at a certain angle on the top of the mirror bracket, the camera bracket is mounted on one side of the support platform, and the camera is fixedly installed on the camera mounting platform on the top of the camera bracket, with the camera's imaging end facing the reflective surface of the mirror.

[0018] Compared with the prior art, the beneficial technical effects of the present invention are as follows:

[0019] 1) The annular combustion chamber device for high-altitude ignition mechanism research provided by the present invention uses a two-stage reverse swirl cup to atomize the fuel, which can ensure that the fuel droplets entering the combustion chamber are small in size, which is conducive to fuel evaporation, full mixing with air and combustion.

[0020] 2) The branch pipe of the low-pressure tee is set at a 30-degree angle to the axis of the main pipe. This can not only remove the oil mist inside the test chamber in time, but also prevent the top transparent quartz glass plate from being contaminated by oil mist.

[0021] 3) The materials of the transparent quartz glass plate, the outer wall of the combustion chamber, and the inner wall of the combustion chamber are all made of transparent quartz glass, which enables the visualization of the flame and allows for the exploration of the cold flow field, spray field, ignition and flame connection process, and flame propagation characteristics between adjacent heads under different working conditions.

[0022] 4) The position of the spark plug hole can be rotated circumferentially according to the position of the outer wall of the combustion chamber, which can be used for experimental research on the influence of the relative position of the spark plug and the cyclone on the ignition performance.

[0023] 5) The sleeve of the two-stage swirling cup and the second-stage swirling device are connected by threads for easy disassembly. The outlet angle at the top of the sleeve is set between 30 and 90 degrees, which allows for the study of the influence mechanism of the swirling device outlet angle on ignition performance.

[0024] In summary, this invention enables ignition performance testing of the annular combustion chamber under different operating conditions by changing the fuel supply flow rate in the fuel main and the air flow rate in the annular intake main. Based on the visualization quartz glass window, the flame propagation characteristics under different operating conditions can be clearly captured, which is of great significance for analyzing the flame connection process and flame propagation characteristics of the annular combustion chamber. Attached Figure Description

[0025] The present invention will be further described below with reference to the accompanying drawings.

[0026] Figure 1 This is a schematic diagram of the overall structure of the annular combustion chamber device for studying the high-altitude ignition mechanism according to the present invention;

[0027] Figure 2 This is a schematic diagram of the structure of the support component of the present invention;

[0028] Figure 3 This is a schematic diagram of the structure of the gas distribution chamber assembly of the present invention;

[0029] Figure 4 This is a half-sectional structural schematic diagram of the gas distribution chamber assembly of the present invention;

[0030] Figure 5 This is a schematic cross-sectional view of the annular combustion chamber assembly of the present invention;

[0031] Figure 6 This is a schematic cross-sectional view of the two-stage vortex cup of the present invention;

[0032] Figure 7 This is a schematic diagram of the connection structure between the low-pressure tee and the I-shaped quick-connect fitting of the present invention;

[0033] Figure 8 This is a schematic diagram of the connection structure between the annular combustion chamber assembly and the bellows of the present invention;

[0034] Figure 9 This is a schematic diagram of the oil supply assembly of the present invention;

[0035] Figure 10 This is a schematic diagram of the connection structure between the imaging component and the support component of the present invention.

[0036] Explanation of reference numerals in the attached figures:

[0037] 1. Support components; 101. Support platform; 102. Bellows support; 103. Gas distribution chamber support; 104. Bellows fixing threaded hole; 105. Anti-slip pad;

[0038] 2. Gas distribution chamber assembly; 201. First gas distribution chamber; 202. Second gas distribution chamber; 203. Annular intake manifold; 204. Honeycomb panel; 205. Fourth flange; 206. Pressure sensor interface; 207. First flange; 208. Second flange; 209. Third flange; 210. Swirl cup interface; 211. Inner groove of the fourth flange; 212. Outer groove of the fourth flange; 213. Oil drain groove; 214. Drain valve;

[0039] 3. Annular combustion chamber assembly; 301. Outer wall of combustion chamber; 302. Inner wall of combustion chamber; 303. Conical guide; 304. Two-stage swirl cup; 3041. First-stage swirler; 3042. Second-stage swirler; 3043. Venturi tube; 3044. Sleeve; 3045. Nozzle retaining sleeve; 305. Spark plug hole;

[0040] 4. Low-pressure extraction assembly; 401. Transparent quartz glass plate; 402. Low-pressure extraction tee; 403. Corrugated pipe; 404. I-beam quick-connect fitting; 4041. I-beam quick-connect fitting body; 4042. First clamp; 4043. Second clamp; 405. Double-ended bolt; 406. Fifth flange; 407. Sixth flange;

[0041] 5. Fuel supply assembly; 501. Main fuel line; 502. Sub-fuel line; 503. Cover plate; 504. Atomizing nozzle;

[0042] 6. Shooting components; 601. Mirror bracket; 602. Camera bracket; 603. Camera mount; 604. Camera; 605. Mirror. Detailed Implementation

[0043] To make the technical problems to be solved, the technical solutions, and the beneficial effects of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0044] like Figure 1-10 As shown, an annular combustion chamber device for studying high-altitude ignition mechanism includes a support assembly 1, a gas distribution chamber assembly 2, an annular combustion chamber assembly 3, a low-pressure extraction assembly 4, and a fuel supply assembly 5. The gas distribution chamber assembly 2, the annular combustion chamber assembly 3, and the low-pressure extraction assembly 4 are assembled and installed sequentially from bottom to top and fixedly connected to the top of the support assembly 1. The fuel supply assembly 5 is fitted onto the outside of the gas distribution chamber assembly 2, and the working end of the fuel supply assembly 5 extends into the interior of the gas distribution chamber assembly 2.

[0045] Specifically, such as Figure 2 As shown, the support assembly 1 includes a support platform 101, a corrugated pipe support 102, and a gas distribution chamber support 103. The gas distribution chamber support 103 is located at the center of the top of the support platform 101. An anti-slip pad 105 is provided on the top of the gas distribution chamber support 103. A plurality of corrugated pipe supports 102 are arranged symmetrically in a circle around the gas distribution chamber support 103 on the top of the support platform 101. A corrugated pipe fixing threaded hole 104 is provided on the top of the corrugated pipe support 102.

[0046] Specifically, such as Figure 3-4As shown, the gas distribution chamber assembly 2 includes a first gas distribution chamber 201, a second gas distribution chamber 202, an annular intake manifold 203, a honeycomb panel 204, and a fourth flange 205. The first gas distribution chamber 201 is placed on the gas distribution chamber support 103, and the bottom of the first gas distribution chamber 201 is tightly fitted with the anti-slip pad 105 on the top of the gas distribution chamber support 103, which can effectively prevent relative displacement between the first gas distribution chamber 201 and the gas distribution chamber support 103. The annular intake manifold 203 is sleeved on the outside of the first gas distribution chamber 201 and is connected to the inner cavity of the first gas distribution chamber 201 through multiple branch pipes. A first flange 207 is provided on the top of the first gas distribution chamber 201. A second flange 208 and a third flange 209 are respectively provided at both ends of the second gas distribution chamber 202. The second gas distribution chamber 202 is fixedly connected to the first gas distribution chamber 201 through the first flange 207 and the second flange 208. At the top, the first flange 207 has a placement groove, the honeycomb plate 204 is placed in the placement groove, and is sandwiched between the first gas distribution chamber 201 and the second gas distribution chamber 202 by the second flange 208. The number of honeycomb plates 204 is set to at least one. The second gas distribution chamber 202 is interconnected with the first gas distribution chamber 201. The fourth flange 205 is fastened to the top of the third flange 209 by bolts. The fourth flange 205 has a plurality of swirl cup interfaces 210 evenly distributed in a circle. The swirl cup interfaces 210 are connected to the inner cavity of the second gas distribution chamber 202. The top of the fourth flange 205 is also provided with a fourth flange inner groove 211, a fourth flange outer groove 212 and an oil drain groove 213. The oil drain groove 213 is connected to the fourth flange inner groove 211 and the fourth flange outer groove 212 respectively, and extends outward.

[0047] Specifically, the honeycomb panel 204 can effectively improve the uniformity of the airflow entering the second air distribution chamber 202.

[0048] Specifically, a sealing ring is provided between the first flange 207 and the second flange 208, and they are fastened together by bolts. The airtightness of the connection between the first flange 207 and the second flange 208 is ensured by compressing the sealing ring.

[0049] Specifically, a drain valve 214 is provided at the bottom of the first air distribution chamber 201; a pressure sensor interface 206 for installing a pressure sensor is provided on the periphery of the second air distribution chamber 202, and the pressure sensor interface 206 is connected to the inner cavity of the second air distribution chamber 202.

[0050] Specifically, such as Figure 5As shown, the annular combustion chamber assembly 3 includes an outer combustion chamber wall 301, an inner combustion chamber wall 302, a conical guide 303, and a two-stage swirl cup 304. The bottom end of the outer combustion chamber wall 301 is snapped into the outer groove 212 of the fourth flange, and the top end of the outer combustion chamber wall 301 is used to support the low-pressure extraction assembly 4. A spark plug hole 305 is provided on the side wall of the outer combustion chamber wall 301. The inner combustion chamber wall 302 is disposed in the inner cavity of the outer combustion chamber wall 301, and the bottom end of the inner combustion chamber wall 302 is snapped into the inner groove 211 of the fourth flange. The top end of the inner combustion chamber wall 302 is sealed with the conical guide 303. Multiple two-stage swirl cups 304 are respectively installed on the swirl cup interface 210, and the two-stage swirl cups 304 are connected to the working end of the fuel supply assembly 5.

[0051] Specifically, both the outer wall of the combustion chamber 301 and the inner wall of the combustion chamber 302 are made of transparent quartz glass.

[0052] Specifically, the conical guide 303 is installed at the top of the combustion chamber wall 302 via a sealing gasket, which can prevent oil mist or flame from entering the inner side of the combustion chamber wall 302.

[0053] Specifically, the position of the spark plug hole 305 can be rotated circumferentially according to the position of the outer wall 301 of the combustion chamber, which can be used for experimental research on the influence of the relative position of the spark plug and the swirl generator on the ignition performance.

[0054] Specifically, such as Figure 6 As shown, the two-stage swirling cup 304 includes a first-stage swirling device 3041, a second-stage swirling device 3042, a venturi tube 3043, and a sleeve 3044. A nozzle retaining sleeve 3045 is provided at the bottom inlet of the first-stage swirling device 3041. The working end of the oil supply assembly 5 is connected to the nozzle retaining sleeve 3045. The top outlet of the first-stage swirling device 3041 is connected to the inlet of the venturi tube 3043. The second-stage swirling device 3042 is arranged around the outside of the venturi tube 3043. The bottom of the sleeve 3044 is threaded to the top of the second-stage swirling device 3042. The top of the sleeve 3044 is provided with a trumpet-shaped opening with an angle of 30° to 90°.

[0055] Specifically, the outlet of the first-stage cyclone separator 3041 is connected to the inlet of the venturi tube 3043 via a transition section or directly to ensure that the high-speed rotating airflow from the first-stage cyclone separator 3041 can directly act on the oil film on the inner wall of the venturi tube 3043 to achieve preliminary fuel atomization; the second-stage cyclone separator 3042 is arranged around the outside of the venturi tube 3043, and the airflow generated by its rotating blades interacts with the airflow generated by the first-stage cyclone separator 3041 to form a complex vortex structure around the venturi tube 3043. The outlet of the second-stage cyclone separator 3042 guides the airflow into the sleeve 3044 through a specific flow channel structure.

[0056] Specifically, such as Figure 7-8 As shown, the low-pressure extraction assembly 4 includes a transparent quartz glass plate 401, a low-pressure extraction tee 402, a bellows 403, an I-beam quick-connect fitting 404, and a double-ended bolt 405. The bellows 403 has a fifth flange 406 and a sixth flange 407 at its two ends, respectively. The bottom of the fifth flange 406 has an external groove. The fifth flange 406 is located on the top of the outer wall 301 of the combustion chamber and is fastened to the fourth flange 205 by the double-ended bolt 405. The outer groove of the flange is snapped into the top of the outer wall 301 of the combustion chamber. The sixth flange 407 at the top of the bellows 403 is fastened to the bellows support 102 by bolts and the bellows fixing threaded hole 104. The bottom end of the low-pressure tee 402 is installed at the top of the bellows 403. The transparent quartz glass plate 401 is fixedly connected to the top of the main pipe of the low-pressure tee 402 by the I-shaped quick connector 404. The branch pipe of the low-pressure tee 402 is used to connect with the low-pressure pipeline.

[0057] Specifically, graphite gaskets are placed in the inner groove 211, outer groove 212, and outer groove of the fourth flange, respectively. The fifth flange 406 and the fourth flange 205 are fastened together by double-ended bolts 405 to achieve a tight fit between the outer wall 301 and the inner wall 302 of the combustion chamber and the graphite gaskets. At the same time, the inner groove 211, outer groove 212, and outer groove of the fourth flange and the outer groove of the fifth flange are respectively fitted with the inner wall 302 and the outer wall 301 of the combustion chamber with millimeter-level clearance, which can meet the thermal expansion and contraction deformation requirements of the quartz glass flame tube.

[0058] Specifically, the branch pipe of the low-pressure tee 402 is preferably set at a 30-degree angle to the axial direction, which can promptly remove the oil mist in the annular combustion chamber assembly 3 and prevent the transparent quartz glass plate 401 from being contaminated by the oil mist.

[0059] Specifically, the bellows 403 can effectively compensate for the additional stress caused by temperature difference and mechanical vibration, ensuring the stable operation of the test device.

[0060] Specifically, the I-shaped quick connector 404 includes an I-shaped quick connector body 4041, a first clamp 4042, and a second clamp 4043. Both the upper and lower ends of the I-shaped quick connector body 4041 are provided with snap-fit ​​protrusions that cooperate with the first clamp 4042 and the second clamp 4043. The bottom of the I-shaped quick connector body 4041 is fixedly connected to the top of the main pipe of the low-pressure tee 402 through the first clamp 4042. The transparent quartz glass plate 401 is fastened to the top of the I-shaped quick connector body 4041 through the second clamp 4043.

[0061] Specifically, the materials of the transparent quartz glass plate 401, the outer wall of the combustion chamber 301, and the inner wall of the combustion chamber 302 are all made of transparent quartz glass, which enables the visualization of the flame and allows for the exploration of the cold flow field, spray field, ignition and flame connection process, and flame propagation characteristics between adjacent heads under different operating conditions.

[0062] Specifically, such as Figure 9 As shown, the fuel supply assembly 5 includes a fuel main pipe 501, a fuel sub-pipe 502, a cover plate 503, and an atomizing nozzle 504. The fuel main pipe 501 is sleeved on the outside of the second air distribution chamber 202. One end of the fuel sub-pipe 502 is connected to the fuel main pipe 501, and the other end of the fuel sub-pipe 502 passes through the side wall of the second air distribution chamber 202 and is connected to the nozzle fixing sleeve 3045 through the atomizing nozzle 504. The cover plate 503, which is fixed on the side wall of the second air distribution chamber 202, is used to fix the fuel sub-pipe 502.

[0063] Specifically, such as Figure 10 As shown, it also includes a shooting component 6, which includes a mirror bracket 601, a camera bracket 602, a camera mounting platform 603, a camera 604, and a mirror 605. The mirror bracket 601 is fixedly installed on the top of the support platform 101. The mirror 605 is installed at a certain angle on the top of the mirror bracket 601. The camera bracket 602 is mounted on one side of the support platform 101. The camera 604 is fixedly installed on the camera mounting platform 603 on the top of the camera bracket 602, and the camera end of the camera 604 faces the reflective surface of the mirror 605.

[0064] Specifically, a filter is installed in front of the 604 lens of the camera to filter infrared and ultraviolet light near the flame during the combustion process;

[0065] Specifically, the user should adjust the height of the camera bracket 602 according to the actual situation so that the camera 604 can capture the combustion situation inside the annular combustion chamber assembly 3 below the transparent quartz glass plate 401 through the reflection of the mirror 605. During the adjustment process, the camera bracket 602 should always ensure that the camera 604 is horizontal with respect to the ground.

[0066] This invention achieves ignition performance testing of the annular combustion chamber under different operating conditions by changing the fuel supply flow rate in the fuel main 501 and the air flow rate in the annular intake main 203. Based on the visualization quartz glass window, the flame propagation characteristics under different operating conditions can be clearly captured, which is of great significance for analyzing the flame connection process and flame propagation characteristics of the annular combustion chamber.

[0067] The usage process of this invention is as follows:

[0068] First, the ignition needle is inserted into the spark plug hole 305 on the side wall of the combustion chamber 301. The gas enters the inner cavity of the first gas distribution chamber 201 through multiple branch pipes set on the annular intake manifold 203. After passing through several small holes on the multi-layer honeycomb plate 204, the uniformity of the airflow entering the second gas distribution chamber 202 is improved.

[0069] Secondly, the pressure sensor is threaded onto the pressure sensor interface 206 to achieve real-time monitoring of the gas pressure in the second gas distribution chamber 202;

[0070] Then, once the required low-pressure air is reached in the second air distribution chamber 202, the ignition needle is turned on and fuel is immediately introduced. The fuel flows sequentially through the fuel main pipe 501, fuel sub-pipe 502, and atomizing nozzle 504 into the two-stage swirl cup 304. After being atomized by the two-stage swirl cup 304, it is sprayed into the annular combustion chamber assembly 3. The user can observe the flame status through the outer wall 301 of the combustion chamber and the transparent quartz glass plate 401. Some unburned fuel during the test will be discharged through the fuel drain 213.

[0071] Finally, after the test is completed, open the drain valve 214 to drain the residual fuel inside the valve train assembly 2.

[0072] 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 terms "comprising," "including," or any other variations thereof are 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 process, method, article, or apparatus.

[0073] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. An annular combustion chamber device for studying high-altitude ignition mechanisms, characterized in that: The system includes a support assembly (1), a valve train assembly (2), an annular combustion chamber assembly (3), a low-pressure extraction assembly (4), and a fuel supply assembly (5). The valve train assembly (2), the annular combustion chamber assembly (3), and the low-pressure extraction assembly (4) are assembled and installed sequentially from bottom to top and fixedly connected to the top of the support assembly (1). The fuel supply assembly (5) is fitted onto the outside of the valve train assembly (2), and the working end of the fuel supply assembly (5) extends into the interior of the valve train assembly (2). The support assembly (1) includes a support platform (101), a bellows support (102), and a gas distribution chamber support (103). The gas distribution chamber support (103) is located at the center of the top of the support platform (101). The top of the gas distribution chamber support (103) is provided with an anti-slip pad (105). Multiple bellows supports (102) are arranged symmetrically in a circle around the gas distribution chamber support (103) on the top of the support platform (101). The top of the bellows support (102) is provided with a bellows fixing threaded hole (104). The gas distribution chamber assembly (2) includes a first gas distribution chamber (201), a second gas distribution chamber (202), an annular intake manifold (203), a honeycomb panel (204), and a fourth flange (205). The first gas distribution chamber (201) is placed on the gas distribution chamber support (103), and the bottom of the first gas distribution chamber (201) is tightly fitted with the anti-slip pad (105) on the top of the gas distribution chamber support (103). The annular intake manifold (203) is sleeved on the first gas distribution chamber. The second air distribution chamber (202) is located on the outside of the first air distribution chamber (201) and is connected to the inner cavity of the first air distribution chamber (201) through multiple branch pipes. The top of the first air distribution chamber (201) is provided with a first flange (207). The two ends of the second air distribution chamber (202) are respectively provided with a second flange (208) and a third flange (209). The second air distribution chamber (202) is fixedly connected to the top of the first air distribution chamber (201) through the first flange (207) and the second flange (208). The first flange (207) has a placement groove. The honeycomb plate (204) is placed in the placement groove and sandwiched between the first air distribution chamber (201) and the second air distribution chamber (202) through the second flange (208). The second air distribution chamber (202) and the first air distribution chamber (201) are interconnected. The fourth flange (205) is fastened to the top of the third flange (209) by bolts. The upper part of the fourth flange (205) is uniformly provided with multiple swirl cup interfaces (210) in a circular shape. The swirl cup interfaces (210) are connected to the inner cavity of the second gas distribution chamber (202). The top of the fourth flange (205) is also provided with a fourth flange inner groove (211), a fourth flange outer groove (212) and an oil drain groove (213). The oil drain groove (213) is connected to the fourth flange inner groove (211) and the fourth flange outer groove (212) respectively, and extends outward. A drain valve (214) is provided at the bottom of the first gas distribution chamber (201); a pressure sensor interface (206) for installing a pressure sensor is provided on the periphery of the second gas distribution chamber (202). The pressure sensor interface (206) is connected to the inner cavity of the second gas distribution chamber (202), and the pressure sensor is threadedly connected to the pressure sensor interface (206) to realize real-time monitoring of the gas pressure in the second gas distribution chamber (202); The annular combustion chamber assembly (3) includes an outer combustion chamber wall (301), an inner combustion chamber wall (302), a conical guide (303), and a two-stage swirl cup (304). The bottom end of the outer combustion chamber wall (301) is snapped into the outer groove (212) of the fourth flange. The top end of the outer combustion chamber wall (301) is used to support the low-pressure extraction assembly (4). Spark plug holes (305) are provided on the side walls of the outer combustion chamber wall (301). (302) is disposed in the inner cavity of the outer wall of the combustion chamber (301), and the bottom end of the inner wall of the combustion chamber (302) is snapped into the groove (211) of the fourth flange. The top end of the inner wall of the combustion chamber (302) is sealed with the conical guide (303). Multiple dual-stage swirl cups (304) are respectively installed on the swirl cup interface (210), and the dual-stage swirl cups (304) are connected to the working end of the fuel supply assembly (5). The dual-stage swirling cup (304) includes a first-stage swirling device (3041), a second-stage swirling device (3042), a venturi tube (3043), and a sleeve (3044). A nozzle fixing sleeve (3045) is provided at the bottom inlet of the first-stage swirling device (3041). The working end of the oil supply assembly (5) is connected to the nozzle fixing sleeve (3045). The top outlet of the first-stage swirling device (3041) is connected to the inlet of the venturi tube (3043). The second-stage swirling device (3042) is arranged around the outside of the venturi tube (3043). The bottom of the sleeve (3044) is threaded to the top of the second-stage swirling device (3042). The top of the sleeve (3044) is provided with a trumpet-shaped opening with an angle of 30° to 90°. The low-pressure extraction assembly (4) includes a transparent quartz glass plate (401), a low-pressure extraction tee (402), a bellows (403), an I-shaped quick-connect fitting (404), and double-ended bolts (405). The bellows (403) has a fifth flange (406) and a sixth flange (407) at its two ends, respectively. The fifth flange (406) has an external groove at its bottom. The fifth flange (406) is located at the top of the outer wall of the combustion chamber (301) and is fastened to the fourth flange (205) by the double-ended bolts (405). The fifth flange outer groove is snapped into the top of the outer wall of the combustion chamber (301). The sixth flange (407) at the top of the bellows (403) is fastened to the bellows support (102) by bolts and the bellows fixing threaded hole (104). The bottom end of the low-pressure tee (402) is installed at the top of the bellows (403). The transparent quartz glass plate (401) is fixedly connected to the top of the main pipe of the low-pressure tee (402) by the I-shaped quick connector (404). The branch pipe of the low-pressure tee (402) is used to connect with the low-pressure pipeline.

2. The annular combustion chamber device for studying high-altitude ignition mechanism according to claim 1, characterized in that: The I-shaped quick connector (404) includes an I-shaped quick connector body (4041), a first clamp (4042), and a second clamp (4043). Both the upper and lower ends of the I-shaped quick connector body (4041) are provided with snap-fit ​​protrusions that cooperate with the first clamp (4042) and the second clamp (4043). The bottom of the I-shaped quick connector body (4041) is fixedly connected to the top of the main pipe of the low-pressure tee (402) through the first clamp (4042). The transparent quartz glass plate (401) is fastened to the top of the I-shaped quick connector body (4041) through the second clamp (4043).

3. The annular combustion chamber device for studying high-altitude ignition mechanism according to claim 1, characterized in that: The fuel supply assembly (5) includes a fuel main pipe (501), a fuel sub-pipe (502), a cover plate (503), and an atomizing nozzle (504). The fuel main pipe (501) is sleeved on the outside of the second air distribution chamber (202). One end of the fuel sub-pipe (502) is connected to the fuel main pipe (501), and the other end of the fuel sub-pipe (502) passes through the side wall of the second air distribution chamber (202) and is connected to the nozzle fixing sleeve (3045) through the atomizing nozzle (504). The cover plate (503) fixed on the side wall of the second air distribution chamber (202) is used to fix the fuel sub-pipe (502).

4. The annular combustion chamber device for studying high-altitude ignition mechanism according to claim 1, characterized in that: It also includes a shooting component (6), which includes a mirror bracket (601), a camera bracket (602), a camera mounting platform (603), a camera (604), and a mirror (605). The mirror bracket (601) is fixedly installed on the top of the support platform (101). The mirror (605) is installed at a certain angle on the top of the mirror bracket (601). The camera bracket (602) is mounted on one side of the support platform (101). The camera (604) is fixedly installed on the camera mounting platform (603) on the top of the camera bracket (602), and the camera end of the camera (604) faces the reflective surface of the mirror (605).

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