A type of vortex-pre-evaporation combustion chamber

Abstract

This invention provides a vortex-pre-evaporation combustion chamber, comprising a casing assembly, a flame tube assembly, a fuel supply assembly, and an evaporator tube. The casing assembly has an air inlet; the flame tube assembly communicates with the air inlet of the casing assembly; an ignition nozzle is installed inside the flame tube assembly; a vortex structure is formed within the flame tube assembly; the fuel supply assembly is mounted on the casing assembly; the inlet end of the evaporator tube communicates with the outlet end of the fuel supply assembly, and the outlet end of the evaporator tube communicates with the interior of the flame tube assembly; the evaporator tube is adapted to evaporate fuel and mix with air to form a fuel-air mixture; the air entering from the air inlet and the fuel-air mixture form a mixed airflow within the flame tube assembly, and the mixed airflow forms a vortex flow field as it flows over the vortex structure; under the action of the vortex flow field, the mixed airflow makes multiple contacts with the ignition nozzle. In this invention, by setting the above structure, the probability of ignition of the fuel-air mixture can be greatly increased, improving the ignition performance and combustion efficiency of the combustion chamber.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and specifically to a vortex-pre-evaporation combustion chamber. Background Technology

[0002] With the rapid development of the aviation industry, the operating environment of aero engines is becoming increasingly complex, requiring combustion chambers to adapt to different operating conditions. Under some harsh conditions, combustion chambers need higher ignition and starting characteristics and operating performance. Existing combustion chambers are divided into evaporator tube annular combustion chambers and multi-swirling annular combustion chambers. Evaporator tube annular combustion chambers require heating of the fuel-air mixture in the evaporator tube, mainly relying on the aerodynamic atomization of air to form droplets, which then enter the flame tube and evaporate and burn under the heating effect of the residual gas in the flame tube. However, under some harsh conditions, the fuel evaporation rate in the evaporator tube is low, which will affect the ignition and starting characteristics of the combustion chamber. Multi-swirling annular combustion chambers mainly generate multiple independent swirles in the entire circumference of the combustion chamber through vortex generators, and use the structure of multi-stage vortex generators to stabilize and organize combustion. Then, centrifugal nozzles atomize liquid fuel, and the tiny droplets are further atomized under the action of swirling. After entering the flame tube, they evaporate rapidly under the action of the igniter and mix with air for combustion. However, this type of combustion chamber often requires the use of complex swirlers and dual-oil-path centrifugal nozzles, which increases the design and manufacturing cost of the combustion chamber. Summary of the Invention

[0003] Therefore, the technical problem to be solved by the present invention is to overcome the defects in the prior art, such as slow combustion chamber ignition and failure of combustion chamber ignition under harsh conditions, which affect the use of the engine.

[0004] Therefore, the present invention provides a vortex-pre-evaporation combustion chamber, comprising:

[0005] The casing assembly has an inner cavity with an air inlet.

[0006] A flame tube assembly is disposed within the inner cavity and communicates with the air inlet of the casing assembly; an ignition nozzle is disposed within the flame tube assembly; a vortex structure is formed within the flame tube assembly;

[0007] A fuel supply assembly is disposed on the casing assembly; the fuel supply assembly is used to supply fuel.

[0008] An evaporator tube is provided, with its inlet end connected to the outlet end of the fuel supply assembly and its outlet end connected to the interior of the flame tube assembly. The evaporator tube evaporates liquid fuel to form gaseous fuel, and then mixes the gaseous fuel with air to form an oil-gas mixture.

[0009] The air entering from the air inlet and the oil-gas mixture form a mixed airflow in the flame tube assembly. When the mixed airflow flows on the annular vortex structure, it forms an annular vortex flow field. Under the action of the annular vortex flow field, the mixed airflow comes into contact with the ignition nozzle multiple times.

[0010] Optionally, the flame tube assembly includes:

[0011] A flame tube outer shell is disposed in the inner cavity and connected to the casing assembly; the flame tube outer shell is provided with the evaporation tube.

[0012] A flame tube head is disposed on the outer shell of the flame tube and is connected to the air inlet of the casing assembly; an ignition nozzle is disposed inside the flame tube head; the flame tube head has a vortex structure.

[0013] The inner shell of the flame tube is connected at one end to the head of the flame tube and at the other end to the casing assembly.

[0014] Optionally, the flame tube head is provided with annular vortex blades, which are arranged in multiple rows, and the multiple rows of annular vortex blades form the annular vortex structure.

[0015] Optionally, the annular vortex vane covers a portion of the flame tube head.

[0016] Optionally, the annular vortex vanes cover only half of the head area of ​​the flame tube, with some annular vortex vanes close to the outer shell of the flame tube and others close to the inner shell of the flame tube, so that all the annular vortex vanes are arranged in an alternating pattern.

[0017] Optionally, the ratio of the arc length of a single annular vortex vane to the arc length of the flame tube head is less than 60%.

[0018] Optionally, the flame tube head is also provided with an air inlet, which is connected to the air inlet of the casing assembly; the air inlet is provided in multiple rows, which are staggered; the air inlet is provided in correspondence with the annular vortex.

[0019] Optionally, the evaporator tube is divided into multiple evaporator branches, which are obliquely inserted into the flame tube assembly, so that the oil-gas mixture ejected from the evaporator tube enters the flame tube assembly along the tangential direction of the annular vortex structure; the multiple evaporator branches are evenly distributed around the outer shell of the flame tube.

[0020] Optionally, the inner shell of the flame tube is provided with an inner shell main combustion hole and an inner shell mixing hole. The inner shell main combustion hole is located at one end of the inner shell of the flame tube near the head of the flame tube, and the inner shell mixing hole is located at one end of the inner shell of the flame tube away from the head of the flame tube.

[0021] Optionally, an outer shell air film hole is provided at the connection between the outer shell of the flame tube and the head of the flame tube, and an inner shell air film hole is provided at the connection between the inner shell of the flame tube and the head of the flame tube. The outer shell air film hole and the inner shell air film hole are adapted to form an air film on the wall surface of the outer shell of the flame tube and the inner shell of the flame tube to prevent the flame tube wall surface from being burned.

[0022] Optionally, the flame tube assembly further includes:

[0023] An exhaust bend is provided on the outer shell and inner shell of the flame tube, and the exhaust bend is adapted to discharge the fuel-gas mixture after combustion.

[0024] Optionally, the exhaust bend includes:

[0025] The first bend is disposed on the outer shell of the flame tube and connected to the casing assembly;

[0026] The second bend is disposed on the inner shell of the flame tube and is connected to the casing assembly.

[0027] Optionally, the casing assembly includes:

[0028] Combustion of the outdoor unit casing;

[0029] The combustion chamber casing is connected to the combustion chamber outer casing.

[0030] A diffuser housing is disposed on the outer combustion chamber housing and the inner combustion chamber housing, the diffuser housing being adapted to mount a diffuser.

[0031] Optionally, the oil supply assembly includes:

[0032] An oil supply nozzle is installed on the outer casing of the combustion chamber, and the outlet end of the oil supply nozzle extends into the inlet of the evaporator pipe;

[0033] A starting nozzle is disposed on the outer casing of the combustion chamber, and the outlet end of the starting nozzle extends through the outer casing of the flame tube into the flame tube.

[0034] Optionally, the oil supply nozzle includes:

[0035] Mounting bracket is provided on the outdoor combustion chamber casing;

[0036] The oil supply line is installed on the mounting base;

[0037] An oil supply nozzle is located at the outlet end of the oil supply pipeline, and the oil supply nozzle is located at the inlet end of the evaporator pipe;

[0038] A heat insulation sleeve is disposed outside the oil supply pipeline, and a gap is provided between the heat insulation sleeve and the oil supply pipeline.

[0039] Optionally, the ignition nozzle extends through the combustion chamber and the flame tube head into the flame tube assembly and is positioned near the starting nozzle at the flame tube head.

[0040] The technical solution of this invention has the following advantages:

[0041] 1. This invention provides a vortex-pre-evaporation combustion chamber, comprising a casing assembly, a flame tube assembly, a fuel supply assembly, and an evaporator tube. The casing assembly has an inner cavity with an air inlet. The flame tube assembly is disposed within the inner cavity and communicates with the air inlet of the casing assembly. An ignition nozzle is disposed within the flame tube assembly. A vortex structure is formed within the flame tube assembly. The fuel supply assembly is disposed on the casing assembly and is used to supply fuel. The inlet end of the evaporator tube communicates with the outlet end of the fuel supply assembly, and the outlet end of the evaporator tube communicates with the interior of the flame tube assembly. The evaporator tube evaporates liquid fuel to form gaseous fuel, then mixes the gaseous fuel with air to form a fuel-air mixture. Air entering from the air inlet and the fuel-air mixture form a mixed airflow within the flame tube assembly. When the mixed airflow flows on the vortex structure, it forms a vortex flow field. Under the action of the vortex flow field, the mixed airflow comes into multiple contact with the ignition nozzle.

[0042] Existing combustion chambers are divided into evaporator-tube annular combustion chambers and multi-swirling annular combustion chambers. For evaporator-tube annular combustion chambers, the fuel evaporation rate within the evaporator tube is low, which affects the ignition and starting characteristics of the combustion chamber. For multi-swirling annular combustion chambers, complex structures such as swirlers and dual-oil-path centrifugal nozzles are often required, increasing the design and manufacturing costs of the combustion chamber. In this embodiment of the invention, by placing the evaporator tube on the flame tube assembly, the air entering through the intake port can form a mixed airflow with the fuel-air mixture within the evaporator tube. This mixed airflow then forms a vortex flow field within the flame tube assembly. As the vortex flow field moves, it makes multiple contacts with the ignition nozzle, significantly increasing the probability of ignition of the fuel-air mixture and improving the ignition performance and combustion efficiency of the combustion chamber.

[0043] 2. This invention provides a vortex-pre-evaporation combustion chamber. By setting the evaporation tube, fuel can be atomized and evaporated as it passes through the evaporation tube to form an oil-gas mixture. Compared with the existing complex centrifugal nozzles for atomizing and evaporating fuel, this method has a lower cost for evaporating fuel. At the same time, the combustion chamber structure under this method is simpler, thereby reducing the structural complexity of the combustion chamber and the cost of evaporating fuel.

[0044] 3. This invention provides a vortex-pre-evaporation combustion chamber, wherein the evaporator tube is divided into multiple evaporator branches, which are obliquely inserted into the flame tube assembly, so that the oil-gas mixture ejected from the evaporator tube enters the flame tube assembly tangentially along the vortex structure. In this embodiment, by obliquely inserting the evaporator branches into the flame tube assembly, the oil-gas mixture can form a vortex flow field within the flame tube assembly under the influence of airflow. This also allows the oil-gas mixture to enter the vortex flow field more smoothly, thereby improving the oil-gas mixing effect and avoiding uneven combustion caused by airflow. Furthermore, the atomization and evaporation of the oil-gas mixture under circumferential shearing can compensate for the insufficient atomization performance of the evaporator tube, thus achieving better combustion chamber ignition performance.

[0045] 4. This invention provides a vortex-pre-evaporation combustion chamber. The fuel injection nozzle includes a mounting base, a fuel supply line, a fuel injection port, and a heat insulation sleeve. The mounting base is disposed on the outer casing of the combustion chamber; the fuel supply line is disposed on the mounting base; the fuel injection port is disposed at the outlet end of the fuel supply line and at the inlet end of the evaporation pipe; the heat insulation sleeve is disposed outside the fuel supply line, and a gap is provided between the heat insulation sleeve and the fuel supply line. In this embodiment of the invention, by providing the heat insulation sleeve, the temperature of the fuel inside the fuel injection nozzle can be effectively reduced, avoiding the problem of fuel coking and carbon deposits caused by the fuel injection nozzle under high temperature conditions, thereby avoiding the problem of fuel injection port blockage and improving fuel injection characteristics. Attached Figure Description

[0046] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0047] Figure 1 This is a schematic diagram of the overall cross-sectional structure of the present invention;

[0048] Figure 2 This is a schematic diagram of the flame tube assembly and fuel supply assembly of the present invention;

[0049] Figure 3 This is a schematic diagram of the annular vortex blade and air inlet structure of the present invention;

[0050] Figure 4 This is a schematic diagram of the annular vortex plate and air inlet from another angle of the present invention;

[0051] Figure 5 This is a schematic diagram of the oil supply nozzle structure of the present invention;

[0052] Figure 6 This is a schematic diagram of the ignition nozzle structure of the present invention;

[0053] Figure 7 This is a schematic diagram of the circumferential arrangement structure of the evaporator tubes of the present invention;

[0054] Figure 8 This is a schematic diagram of the oil supply pipeline structure of the present invention.

[0055] Explanation of reference numerals in the embodiments:

[0056] 1. Casing assembly; 2. Flame tube assembly; 3. Fuel supply assembly; 4. Evaporator tube; 5. Ignition nozzle;

[0057] 11. Combustion chamber outer casing; 12. Combustion chamber inner casing; 13. Diffuser casing;

[0058] 21. Flame tube outer shell; 22. Flame tube head; 23. Flame tube inner shell; 24. Exhaust bend;

[0059] 211. Outer shell film vent; 212. Outer shell mixing vent;

[0060] 221. Circular vortex vane; 222. Air inlet;

[0061] 231. Main combustion port in the inner shell; 232. Mixing port in the inner shell; 233. Film combustion port in the inner shell;

[0062] 241. First bend; 242. Second bend;

[0063] 31. Fuel supply nozzle; 32. Starting nozzle; 33. Main fuel supply line; 34. Starting fuel supply line;

[0064] 311. Mounting base; 312. Oil supply line; 313. Oil supply nozzle; 314. Heat insulation sleeve;

[0065] 331. Oil supply pipe joint. Detailed Implementation

[0066] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0067] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0068] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" 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 mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0069] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0070] Example

[0071] like Figures 1 to 8 As shown, this embodiment provides a vortex-pre-evaporation combustion chamber, including a casing assembly 1, a flame tube assembly 2, a fuel supply assembly 3, and an evaporator pipe 4. The casing assembly 1 has an inner cavity with an air inlet. The flame tube assembly 2 is disposed within the inner cavity and communicates with the air inlet of the casing assembly 1. An ignition nozzle 5 is disposed within the flame tube assembly 2. A vortex structure is formed within the flame tube assembly 2. The fuel supply assembly 3 is disposed on the casing assembly 1 and is used to supply fuel. The inlet end of the evaporator pipe 4 communicates with the outlet end of the fuel supply assembly 3, and the outlet end of the evaporator pipe 4 communicates with the interior of the flame tube assembly 2. The evaporator pipe 4 evaporates liquid fuel to form gaseous fuel, and then mixes the gaseous fuel with air to form a fuel-air mixture. The air entering from the air inlet and the fuel-air mixture form a mixed airflow within the flame tube assembly 2. When the mixed airflow flows on the vortex structure, it forms a vortex flow field. Under the action of the vortex flow field, the mixed airflow comes into contact with the ignition nozzle 5 multiple times.

[0072] In this embodiment of the invention, air first enters the flame tube assembly 2 through the air inlet, and then fuel is sprayed out through the outlet end of the fuel supply assembly 3. The fuel enters the evaporator 4 through the inlet end of the evaporator 4. Through the atomization and evaporation of the evaporator 4, the fuel becomes an oil-gas mixture and enters the flame tube assembly 2. The oil-gas mixture mixes and flows with the air, thereby forming a vortex flow field. Under the action of the vortex flow field, the mixed airflow comes into contact with the ignition nozzle 5 multiple times, and then is ignited by the ignition nozzle 5, so that the mixed airflow is fully burned in the flame tube assembly 2.

[0073] Existing combustion chambers are divided into evaporator-tube annular combustion chambers and multi-swirling annular combustion chambers. For evaporator-tube annular combustion chambers, the fuel evaporation rate within the evaporator tube is low, which affects the ignition and starting characteristics of the combustion chamber. For multi-swirling annular combustion chambers, complex structures such as swirlers and dual-oil-path centrifugal nozzles are often required, increasing the design and manufacturing costs of the combustion chamber. In this embodiment of the invention, by inserting the evaporator tube 4 into the flame tube assembly 2, the air entering through the intake port can form a mixed airflow with the fuel-air mixture within the evaporator tube. This mixed airflow then forms a vortex flow field within the flame tube assembly. As the vortex flow field moves, it makes multiple contacts with the ignition nozzle 5, significantly increasing the probability of ignition of the fuel-air mixture and improving the ignition performance and combustion efficiency of the combustion chamber.

[0074] Specifically, such as Figure 1 As shown, the flame tube assembly 2 includes a flame tube outer shell 21, a flame tube head 22, and a flame tube inner shell 23. The flame tube outer shell 21 is disposed in the inner cavity and connected to the casing assembly 1. The evaporator pipe 4 is disposed on the flame tube outer shell 21. The flame tube head 22 is disposed on the flame tube outer shell 21 and communicates with the air inlet of the casing assembly 1. An ignition nozzle 5 is disposed inside the flame tube head 22. The flame tube head 22 has a vortex structure. One end of the flame tube inner shell 23 is connected to the flame tube head 22, and the other end is connected to the casing assembly 1. Air enters the flame tube assembly 2 through the air inlet and the flame tube head 22. After passing through the vortex structure, the air mixes with the oil-gas mixture ejected from the evaporator pipe 4, continuously flowing within the flame tube head 22 to form a vortex flow field.

[0075] Furthermore, such as Figure 3 and Figure 4As shown, the flame tube head 22 is provided with annular vortex blades 221. The annular vortex blades 221 are arranged in multiple rows, and the multiple rows of annular vortex blades 221 form the annular vortex structure. The annular vortex blades 221 are L-shaped and welded to the flame tube head 22. A space is provided between the annular vortex blades 221 and the flame tube head 22, and an opening is provided at one end of the space. The direction of the opening is consistent with the direction of the inlet airflow of the combustion chamber. That is to say, the guiding direction of the annular vortex blades 221 is consistent with the direction of the inlet airflow of the combustion chamber.

[0076] Furthermore, the annular vortex vanes 221 partially cover the flame tube head 22. Specifically, the annular vortex vanes 221 cover only half of the flame tube head 22, with some vanes closer to the outer shell 21 and others closer to the inner shell 23, so that all the annular vortex vanes 221 are arranged in an alternating pattern. By staggering the annular vortex vanes 221 on the flame tube head 22 and covering half of the flame tube head 22, more space can be provided in the flame tube head 22 for installing the ignition nozzle 5, and the problem of insufficient circumferential coverage of the cooling airflow in the flame tube head 22 can also be compensated.

[0077] Furthermore, the ratio of the arc length of a single annular vortex vane 221 to the arc length of the flame tube head 22 is less than 60%. By setting the ratio of the arc length of a single annular vortex vane 221 to the arc length of the flame tube head 22 to less than 60%, sufficient flow space can be ensured for the airflow at the outlet of the annular vortex vane 221, and the processing and assembly complexity of the annular vortex vane 221 can be reduced, thereby saving costs. When combustion occurs in the combustion chamber, the ignition nozzle 5 generates an ignition source. Under the action of the annular vortex flow field, the oil-gas mixture flows to the ignition source position and repeatedly contacts the ignition source, thereby achieving combustion of the oil-gas mixture, and the flame is transmitted along the annular vortex flow field.

[0078] Furthermore, such as Figure 3 and Figure 4 As shown, the flame tube head 22 is also provided with an air inlet 222, which communicates with the air inlet of the casing assembly 1; the air inlet 222 is provided in multiple rows, which are staggered; the air inlet 222 is correspondingly provided with the annular vortex plate 221. The air entering from the air inlet passes through the air inlet 222, and then enters the flame tube assembly 2 through the action of the annular vortex plate 221, forming an annular vortex flow field in the circumferential direction at the flame tube head 22.

[0079] Furthermore, such as Figure 7As shown, the evaporator tube 4 is divided into multiple evaporator branches, which pass through the outer shell 21 of the flame tube and are obliquely inserted into the flame tube assembly 2. This allows the oil-gas mixture ejected from the evaporator tube 4 to enter the flame tube assembly 2 tangentially along the annular vortex structure. In this embodiment of the invention, by obliquely inserting the evaporator branches through the outer shell 21 of the flame tube into the flame tube assembly 2, the oil-gas mixture can be tangentially injected into the flame tube assembly 2. This allows the oil-gas mixture to form an annular vortex flow field within the flame tube assembly 2 under the influence of the airflow. Simultaneously, it allows the oil-gas mixture to enter the annular vortex flow field more smoothly, thereby improving the oil-gas mixing effect and avoiding uneven combustion caused by airflow. Furthermore, the atomization and evaporation of the oil-gas mixture under circumferential shearing can compensate for the insufficient atomization performance of the evaporator tube, thus achieving better combustion chamber ignition performance.

[0080] In this embodiment of the invention, there are 6 evaporator pipes 4, and each evaporator pipe 4 is divided into four evaporator branches. That is, there are 24 outlet ends of evaporator branches arranged in the circumferential direction of the flame tube shell 21. By dividing the evaporator pipe 4 into several evaporator branches, the turbulence of the oil-gas mixture flow in the evaporator pipe 4 can be enhanced, thereby enhancing the mixing of air and fuel. At the same time, it also promotes the collision and breaking of fuel walls and atomization and evaporation, thereby improving the combustion effect of the oil-gas mixture.

[0081] Furthermore, multiple evaporator branches are evenly distributed around the outer shell 21 of the flame tube. This even distribution increases the contact area between the evaporator branches and the outer shell 21, thereby increasing the heating effect of the evaporator branches, improving the evaporation efficiency of the fuel within the evaporator tubes 4, and further promoting the mixing of high-temperature air and fuel vapor. This allows the fuel-air mixture ejected from the evaporator branch outlet to rapidly diffuse throughout the combustion zone under the influence of the annular vortex flow field, achieving uniform combustion of the fuel-air mixture. Additionally, by evenly distributing multiple evaporator branches around the outer shell 21, the evaporator branches can absorb heat from the outer shell 21 to evaporate the fuel inside. Furthermore, by controlling the outlet direction of the evaporator tubes 4, fuel can be injected into the flame tube from different positions within the outer shell 21, further achieving multi-point injection and uniform combustion in the combustion chamber.

[0082] In this embodiment of the invention, the evaporation tube 4 is disposed outside the flame tube assembly 2, or inside the flame tube assembly 2, or integrally disposed with the flame tube outer shell 21. This embodiment does not limit the arrangement of the evaporation tube 4. Those skilled in the art can change the arrangement of the evaporation tube 4 according to the actual situation, as long as the same technical effect can be achieved.

[0083] In this embodiment of the invention, by setting the evaporator tube 4, fuel and fresh air can be pre-mixed and pre-evaporated in the evaporator tube 4. Then, by utilizing the controllable position and adjustable direction of the outlet of the evaporator tube 4, the fuel-air mixture is injected into the flame tube in the circumferential direction in the form of a jet, which drives the surrounding airflow to form a ring vortex flow field.

[0084] Furthermore, such as Figure 2 As shown, the inner shell 23 of the flame tube is provided with an inner shell main combustion port 231 and an inner shell mixing port 232. The inner shell main combustion port 231 is located at the end of the inner shell 23 near the flame tube head 22, and the inner shell mixing port 232 is located at the end of the inner shell 23 away from the flame tube head 22. The outer shell 21 of the flame tube is also provided with an outer shell mixing port 212, which is located at the end of the outer shell 21 near the flame tube head 22. By providing the inner shell main combustion port 231, the inner shell mixing port 232, and the outer shell mixing port 212, the outlet temperature field of the combustion chamber can be controlled, thereby extending the service life of the combustion chamber and the turbine.

[0085] Furthermore, an outer shell gas film hole 211 is provided at the connection between the outer shell 21 and the head 22 of the flame tube, and an inner shell gas film hole 233 is provided at the connection between the inner shell and the head 22 of the flame tube. The outer shell gas film hole 211 and the inner shell gas film hole 233 are adapted to form an air film on the wall surface of the outer shell 21 and the inner shell 23 of the flame tube, preventing the flame tube wall from being ablated. The air passing through the outer shell gas film hole 211 and the inner shell gas film hole 233 can form an air film on the wall surface of the outer shell 21, the head 22, and the inner shell 23 of the flame tube, so that the air film protects the wall surface of the flame tube assembly 2, preventing the oil-gas mixture from contacting the wall surface and starting to burn under the flow action of the annular vortex field, thus preventing the wall surface of the flame tube assembly 2 from being ablated.

[0086] Furthermore, the flame tube assembly 2 also includes an exhaust bend 24, which is disposed on the outer shell 21 and the inner shell 23 of the flame tube, and is adapted to discharge the fuel-gas mixture after combustion.

[0087] Furthermore, such as Figure 1As shown, the exhaust bend 24 includes a first bend 241 and a second bend 242. The first bend 241 is disposed on the outer shell 21 of the flame tube and connected to the casing assembly 1; the second bend 242 is disposed on the inner shell 23 of the flame tube and connected to the casing assembly 1. Air entering from the intake port passes through the intake hole 222 into the flame tube assembly 2, and then passes through the channel formed by the first bend 241 and the second bend 242, that is, through the exhaust bend 24, and is discharged from the outlet of the flame tube assembly 2 to the turbine (not shown), which then drives the turbine to rotate and do work, driving the engine to run.

[0088] Furthermore, such as Figure 1 As shown, the casing assembly 1 includes an outdoor combustion chamber casing 11, an indoor combustion chamber casing 12, and a diffuser casing 13. The indoor combustion chamber casing 12 is connected to the outdoor combustion chamber casing 11. The diffuser casing 13 is disposed on the outdoor combustion chamber casing 11 and the indoor combustion chamber casing 12, and the diffuser casing 13 is adapted to install a diffuser (not shown).

[0089] Furthermore, such as Figure 2 As shown, the fuel supply assembly 3 includes a fuel supply nozzle 31 and a starting nozzle 32. The fuel supply nozzle 31 is disposed on the combustion chamber 11, and the outlet end of the fuel supply nozzle 31 extends into the inlet of the evaporator pipe 4. The starting nozzle 32 is disposed on the combustion chamber 11, and the outlet end of the starting nozzle 32 passes through the flame tube outer shell 21 and extends into the flame tube.

[0090] In this embodiment of the invention, the starting nozzle 32 is configured as a single-path centrifugal nozzle with a small nozzle size. It mainly utilizes its internal cyclone separator to achieve fuel rotation and centrifugal atomization, improving the fuel atomization and evaporation performance of the combustion chamber under harsh conditions, and thus improving ignition performance by reducing the size of fuel droplets. In addition, the starting nozzle 32 is provided with a heat insulation sleeve with several cooling holes. When the combustion chamber operates under high temperature conditions, the heat insulation sleeve can protect the tiny oil passages inside the centrifugal nozzle, thereby preventing fuel from coking inside the pipes. When the combustion chamber operates under normal conditions, the starting nozzle 32 still supplies a portion of fuel, forming an axial staged fuel supply effect together with the fuel supply from the evaporator pipe 4. At the same time, maintaining fuel flow inside the starting nozzle 32 also helps to dissipate fuel heat and prevent fuel from coking inside the centrifugal nozzle.

[0091] In this embodiment of the invention, four starting nozzles 32 are provided, which are evenly distributed around the flame tube shell 21. The main function of the starting nozzles 32 is to provide the combustion chamber with smaller fuel droplets under harsh operating conditions, thereby improving the fuel atomization and evaporation effect and improving the ignition performance of the combustion chamber. Therefore, the number of nozzles is small, which ensures that the combustion chamber can work normally while minimizing structural complexity and design and manufacturing costs.

[0092] Furthermore, such as Figure 5 As shown, the fuel nozzle 31 includes a mounting base 311, a fuel supply line 312, a fuel injection port 313, and a heat insulation sleeve 314. The mounting base 311 is disposed on the outer casing 11 of the combustion chamber; the fuel supply line 312 is disposed on the mounting base 311; the fuel injection port 313 is disposed at the outlet end of the fuel supply line 312 and at the inlet end of the evaporator pipe 4; the heat insulation sleeve 314 is disposed outside the fuel supply line 312, and a gap is provided between the heat insulation sleeve 314 and the fuel supply line 312. In this embodiment of the invention, by providing the heat insulation sleeve 314, the temperature of the fuel inside the fuel nozzle 31 can be effectively reduced, avoiding the problem of fuel coking and carbon deposits caused by the fuel nozzle 31 at high temperatures, thereby avoiding the problem of clogging of the fuel injection port 313 and improving the fuel injection characteristics. In addition, an annular gap is provided between the heat insulation sleeve 314 and the oil supply line 312 to form an air gap, which can achieve better heat insulation effect. Furthermore, the length of the gap is set between 0.1mm and 0.5mm.

[0093] In this embodiment of the invention, the number of fuel injection nozzles 313 is between 2 and 6, respectively arranged radially on the fuel supply line 312. The opening direction of the fuel injection nozzles 313 is set in the axial direction, or it can be set at an angle to the axial direction. Multiple fuel injection nozzles 313 can also be arranged in different directions. This embodiment does not limit the arrangement direction of the fuel injection nozzles 313. Those skilled in the art can change the arrangement direction of the fuel injection nozzles 313 according to actual conditions, as long as the same technical effect can be achieved. By using multiple fuel injection nozzles 313 and multiple injection directions, a uniform distribution of the oil film on the inner surface of the evaporator tube 4 can be achieved, while preventing fuel from splashing out from the inlet of the evaporator tube 4, thereby improving the fuel distribution characteristics within the evaporator tube 4, simplifying the design, and reducing costs.

[0094] In this embodiment of the invention, the fuel supply nozzle 31 is configured as a simple direct-injection nozzle. The outlet end of the direct-injection nozzle is connected to the inlet of the evaporator tube 4 for supplying fuel to the evaporator tube 4. Fuel is injected into the evaporator tube 4 through the fuel supply nozzle 313, forming an oil film on the inner surface of the evaporator tube 4. Multiple fuel supply nozzles 313 can form multiple oil films around the inlet end of the evaporator tube 4, ultimately forming a uniform oil film on the inner surface of the evaporator tube 4. The fuel is then distributed through multiple evaporator branch pipes, making the oil film thinner. This causes fuel droplets to splash and mix with air inside the evaporator tube 4, and then evenly distributed to the outlet ends of multiple evaporator branch pipes and sprayed out in the form of an oil-gas mixture. Under harsh operating conditions, this can further improve the atomization and evaporation performance of the oil-gas mixture, thereby improving ignition performance.

[0095] This invention supplies fuel to the combustion chamber primarily through the evaporator pipe 4, supplemented by the fuel supply from the starting nozzle 32. Combined with a vortex flow field, the fuel-air mixture in the combustion chamber is ignited and burned. This method enables the fuel-air mixture to have a better atomization effect under harsh operating conditions. Under normal operating conditions of the combustion chamber, the working state of the combustion chamber can be controlled by adjusting the fuel supply ratio of the centrifugal nozzle, the direct injection nozzle, and the evaporator pipe, thereby reducing pollution emissions, increasing the adjustability of the combustion chamber, and directly improving the ignition performance of the combustion chamber.

[0096] Furthermore, such as Figure 6 As shown, the ignition nozzle 5 passes through the combustion chamber outer casing 11 and the flame tube head 22, extending into the flame tube assembly 2, and is positioned on the flame tube head 22 near the starting nozzle 32. In this embodiment of the invention, two ignition nozzles 5 are provided, respectively positioned circumferentially on the combustion chamber outer casing 11. By positioning the ignition nozzles 5 on the flame tube head 22 near the starting nozzle 32, the propagation distance of the ignition energy of the ignition nozzle 5 can be effectively shortened, thereby achieving rapid ignition and combustion. When the ignition nozzle 5 is installed, it passes through the combustion chamber outer casing 11 and the flame tube head 22, snaps onto the mounting base of the combustion chamber outer casing 11 and the mounting base of the flame tube head 22, and extends into the flame tube assembly 2 to provide ignition energy for the oil-gas mixture.

[0097] Furthermore, the ignition nozzle 5 is configured with a double-layer structure, with the inner layer being the electrode of the ignition nozzle 5 and the outer layer being the protective sleeve of the ignition nozzle 5. The protective sleeve is provided with several cooling holes, and the airflow through the cooling holes can protect the ignition nozzle 5.

[0098] In this embodiment of the invention, the ignition nozzle 5 and the starting nozzle 32 are provided with an angle. The ignition nozzle 5 sprays inward along the radial direction of the flame tube, and at the same time, it is close to the flow direction of the circumferential vortex flow field along the combustion chamber. It sprays from the outer shell 21 of the flame tube to the head 22 of the flame tube at a certain angle. By controlling the three-dimensional angle, the injection direction and mist cone distribution of the starting nozzle 32 are restricted, thereby making the ignition nozzle 5 and the starting nozzle 32 provide a certain angle, and further enabling the ignition nozzle 5 to quickly ignite the fuel sprayed by the starting nozzle 32.

[0099] Furthermore, such as Figure 8 As shown, the fuel supply nozzle 31 supplies fuel through the main fuel supply line 33, and the starting nozzle 32 supplies fuel through the starting fuel supply line 34. The main fuel supply line 33 has six fuel supply nozzles 31, each matching the inlet end of one of the six evaporator pipes 4, injecting fuel into the inlet ends of the six evaporator pipes 4 through the six fuel supply nozzles 31. The starting fuel supply line 34 has four outlet ends, each cooperating with one of the four starting nozzles 32. Furthermore, the main fuel supply line 33 is also equipped with a fuel supply pipe connector 331, which allows for segmented processing of the main fuel supply line 33, thereby reducing the design and manufacturing cost of the combustion chamber. In this embodiment of the invention, the number of fuel supply nozzles 31, starting nozzles 32, and evaporator pipes 4 is not limited. Those skilled in the art can change the number of fuel supply nozzles 31, starting nozzles 32, and evaporator pipes 4 according to actual conditions, as long as the same technical effect is achieved.

[0100] This invention combines the evaporator tube 4 with the annular vortex flow field, utilizing the pre-evaporation and pre-mixing characteristics of the evaporator tube 4 and its low cost, and further combining the beneficial characteristics of the annular vortex flow field on the combustion chamber ignition performance and fuel combustion performance, to achieve low cost, high performance and reliable ignition characteristics of the combustion chamber.

[0101] The specific working process of the annular vortex-pre-evaporation combustion chamber provided by this invention is as follows:

[0102] First, air enters the channel between the outer casing 11 of the combustion chamber and the outer shell 21 of the flame tube through the air intake, and then enters the flame tube assembly 2 through the air intake hole 222 on the flame tube head 22. At the same time, the air is guided by the annular vortex vane 221 to form an annular vortex flow field. In addition, the fuel injected by the fuel supply nozzle 31 enters the inlet end of the evaporator pipe 4, and then is atomized and evaporated by the evaporator pipe 4 to generate a fuel-air mixture. The fuel-air mixture is discharged from the outlet of the evaporator pipe 4 and enters the flame tube assembly 2. At the same time, the fuel-air mixture injected by the starter nozzle 32 enters the flame tube assembly 2. Under the action of the annular vortex flow field, the fuel-air mixture moves the position of the ignition electrode 5. The fuel-air mixture is ignited by the ignition electrode 5 and then burned. It is then discharged through the exhaust bend 24, driving the turbine to rotate and do work, driving the engine to run, and thus completing the combustion process of the fuel-air mixture in the combustion chamber.

[0103] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. A vortex-pre-evaporation combustion chamber, characterized in that, include: The casing assembly (1) is provided with an inner cavity, and the inner cavity is provided with an air inlet; The flame tube assembly (2) is disposed in the inner cavity and communicates with the air inlet of the casing assembly (1); the flame tube assembly (2) is provided with an ignition nozzle (5); the flame tube assembly (2) forms a vortex structure. A fuel supply assembly (3) is disposed on the casing assembly (1); the fuel supply assembly (3) is used to supply fuel. Evaporator (4), the inlet end of the evaporator (4) is connected to the outlet end of the fuel supply assembly (3), and the outlet end of the evaporator (4) is connected to the interior of the flame tube assembly (2); the evaporator (4) evaporates the liquid fuel to form gaseous fuel, and then mixes the gaseous fuel with air to form an oil-gas mixture; The air entering from the air inlet and the oil-gas mixture form a mixed airflow in the flame tube assembly (2). When the mixed airflow flows on the vortex structure, it forms a vortex flow field. Under the action of the vortex flow field, the mixed airflow comes into contact with the ignition nozzle (5) multiple times. The flame tube assembly (2) includes: The flame tube housing (21) is disposed in the inner cavity and connected to the casing assembly (1), and the flame tube housing (21) is provided with the evaporation tube (4). The flame tube head (22) is disposed on the flame tube outer shell (21), and the flame tube head (22) is connected to the air inlet of the casing assembly (1); an ignition nozzle is disposed inside the flame tube head (22); the flame tube head (22) has a ring vortex structure. The inner shell of the flame tube (23) is connected at one end to the head of the flame tube (22) and at the other end to the casing assembly (1); The flame tube head (22) is provided with annular vortex plates (221), and the annular vortex plates (221) are arranged in multiple rows, and the multiple rows of annular vortex plates (221) form the annular vortex structure; The annular vortex (221) covers only half of the flame tube head (22), and a portion of the annular vortex (221) is close to the outer shell (21) of the flame tube, while another portion is close to the inner shell (23) of the flame tube, so that all the annular vortex (221) are arranged in an alternating pattern. The evaporator tube (4) is divided into multiple evaporator branches, which are obliquely inserted into the flame tube assembly (2), so that the oil-gas mixture ejected from the evaporator tube (4) enters the flame tube assembly (2) along the tangential direction of the vortex structure; the multiple evaporator branches are evenly distributed around the flame tube shell (21).

2. The annular vortex-pre-evaporation combustion chamber according to claim 1, characterized in that, The annular vortex plate (221) covers part of the flame tube head (22).

3. The annular vortex-pre-evaporation combustion chamber according to claim 1, characterized in that, The ratio of the arc length of a single annular vortex vane (221) to the arc length of the flame tube head (22) is less than 60%.

4. The annular vortex-pre-evaporation combustion chamber according to claim 1, characterized in that, The flame tube head (22) is also provided with an air inlet (222), which is connected to the air inlet of the casing assembly (1); the air inlet (222) is provided in multiple rows, and the multiple rows of air inlets (222) are staggered; the air inlet (222) is provided in correspondence with the annular vortex plate (221).

5. The annular vortex-pre-evaporation combustion chamber according to any one of claims 2 to 4, characterized in that, The inner shell (23) of the flame tube is provided with an inner shell main combustion hole (231) and an inner shell mixing hole (232). The inner shell main combustion hole (231) is located at one end of the inner shell (23) near the flame tube head (22), and the inner shell mixing hole (232) is located at one end of the inner shell (23) away from the flame tube head (22).

6. The annular vortex-pre-evaporation combustion chamber according to any one of claims 2 to 4, characterized in that, An outer shell air film hole (211) is provided at the connection between the outer shell (21) and the head (22) of the flame tube, and an inner shell air film hole (233) is provided at the connection between the inner shell (23) and the head (22) of the flame tube. The outer shell air film hole (211) and the inner shell air film hole (233) are adapted to form an air film on the wall surface of the outer shell (21) and the inner shell (23) of the flame tube to prevent the flame tube wall surface from being burned.

7. The annular vortex-pre-evaporation combustion chamber according to any one of claims 2 to 4, characterized in that, The flame tube assembly (2) also includes: An exhaust bend (24) is provided on the outer shell (21) of the flame tube and the inner shell (23) of the flame tube, and the exhaust bend (24) is adapted to discharge the oil-gas mixture after combustion.

8. The annular vortex-pre-evaporation combustion chamber according to claim 7, characterized in that, The exhaust bend (24) includes: The first bend (241) is disposed on the outer shell (21) of the flame tube and is connected to the casing assembly (1); The second bend (242) is disposed on the inner shell (23) of the flame tube and is connected to the casing assembly (1).

9. The annular vortex-pre-evaporation combustion chamber according to any one of claims 2 to 4, characterized in that, The casing assembly (1) includes: Combustion outdoor unit casing (11); The combustion chamber housing (12) is connected to the combustion chamber housing (11); A diffuser housing (13) is disposed on the outer combustion chamber housing (11) and the inner combustion chamber housing (12), the diffuser housing (13) being adapted to mount a diffuser.

10. The annular vortex-pre-evaporation combustion chamber according to claim 9, characterized in that, The oil supply component (3) includes: An oil supply nozzle (31) is provided on the outer casing (11) of the combustion chamber, and the outlet end of the oil supply nozzle (31) extends into the inlet of the evaporator pipe (4); A starting nozzle (32) is provided on the outer casing (11) of the combustion chamber, and the outlet end of the starting nozzle (32) extends into the flame tube through the outer casing (21) of the flame tube.

11. The annular vortex-pre-evaporation combustion chamber according to claim 10, characterized in that, The oil supply nozzle (31) includes: Mounting bracket (311) is provided on the combustion chamber (11); An oil supply line (312) is installed on the mounting base (311); An oil supply nozzle (313) is provided at the outlet end of the oil supply pipeline (312), and the oil supply nozzle (313) is provided at the inlet end of the evaporator pipe (4); A heat insulation sleeve (314) is disposed outside the oil supply line (312), and a gap is provided between the heat insulation sleeve (314) and the oil supply line (312).

12. The annular vortex-pre-evaporation combustion chamber according to claim 10, characterized in that, The ignition nozzle (5) extends through the combustion chamber housing (11) and the flame tube head (22) into the flame tube assembly (2), and is positioned near the starting nozzle (32) on the flame tube head (22).

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