Flame tubes, engines and helicopters

Abstract

The present application relates to a flame tube, an engine and a helicopter, wherein the flame tube comprises an inner flame ring and an outer flame ring, one end of the inner flame ring and the outer flame ring are provided with an opening, the other end of the inner flame ring and the outer flame ring are connected by a mounting plate, a plurality of evaporation tubes are mounted on the mounting plate, an annular cavity is formed between the inner flame ring, the outer flame ring and the mounting plate, the evaporation tube comprises a confluence pipe and an evaporation nozzle, the evaporation nozzle is located in the annular cavity and a plurality of the evaporation nozzles are arranged in an annular shape around the axis of the annular cavity in a preset order, a plurality of jet tubes are arranged on the mounting plate, a plurality of the jet tubes are connected with the annular cavity, and a plurality of the jet tubes are arranged in a spiral shape around the axis of the annular cavity. The flame tube of the present application effectively improves the uniform distribution capability of the oil-gas mixed fluid, improves the outlet temperature field of the combustion chamber, and improves the combustion efficiency.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft engines and gas turbines, and in particular to a flame tube, an engine and a helicopter. Background Art

[0002] Small and micro aircraft engines and gas turbines have been a hot topic of research at home and abroad in recent years. They have the advantages of small size, light weight, high output energy, and high density. Although relevant research work on the combustion chamber of small and micro gas turbine engines has been carried out at home and abroad, the common design is an evaporator tube with a turbulent structure and a direct-flow flame tube. This flame tube adopts a simple evaporator tube oil supply due to space limitations. This method can ensure that the fuel is efficiently burned in a short time, but it puts forward higher requirements for the atomization of the evaporator tube.

[0003] There are two main structural designs for the evaporator tube: straight-tube type and L-type. The straight-tube type uses a circle of straight tubes to penetrate into the flame tube, using the high temperature inside the flame tube to evaporate the fuel, and using the reduced fuel outlet diameter to atomize the fuel. The L-type evaporator tube is a circle of rotating straight tubes that penetrate into the combustion chamber. There is a pre-rotation structure at the outlet of the L-type evaporator tube to atomize the fuel at the outlet and evaporate the fuel inside the tube. The current flame tube and evaporator tube design is based on a multi-ring vortex main combustion zone design, with relatively high local high temperatures, short fuel residence time in the combustion chamber, and insignificant mixing effect with air, which can easily lead to incomplete combustion, high fuel consumption, high nitrogen oxide emissions, and high smoke generation, and high requirements for the material and design of the evaporator tube; in addition, due to the limitations of the flame tube design, the current straight-tube and L-shaped evaporator tubes are too short, and a small number of spiral-shaped ones are also distributed in an axial manner. The main combustion zone in the flame tube is distributed as multiple independent ring vortices, which can also cause relatively high local temperatures, resulting in uneven temperature distribution in the combustion chamber, which in turn leads to large combustion chamber outlet temperature distribution coefficient (OTDF) and combustion chamber outlet radial temperature distribution coefficient (RTDF). Summary of the invention

[0004] In order to solve the above technical problems, the present application provides a flame tube, an engine and a helicopter, which can improve the uniform distribution capability of the oil-gas mixed fluid.

[0005] On the one hand, the present application provides a flame tube, comprising an inner flame ring and an outer flame ring, one end of the inner flame ring and the outer flame ring are provided with openings, the other ends of the inner flame ring and the outer flame ring are connected by a mounting plate, a plurality of evaporation tubes are mounted on the mounting plate, an annular cavity is formed between the inner flame ring, the outer flame ring and the mounting plate, the evaporation tube comprises a converging pipe and an evaporation nozzle, the evaporation nozzle is located in the annular cavity and a plurality of the evaporation nozzles are arranged in a ring shape around the axis of the annular cavity in a preset order, a plurality of jet tubes are arranged on the mounting plate, the plurality of the jet tubes are connected to the annular cavity, and the plurality of the jet tubes are arranged in a spiral shape around the axis of the annular cavity.

[0006] In one embodiment of the present application, the mounting plate is provided with a plurality of mounting holes, the manifold comprises an oil circuit sleeve, an air circuit sleeve is disposed outside the oil circuit sleeve, and the air circuit sleeve is installed in the mounting holes.

[0007] In one embodiment of the present application, an air intake cavity is formed between the air circuit casing and the oil circuit casing, and a plurality of air vents are provided on the oil circuit casing. The air intake cavity is connected to the oil circuit casing through the air vents, the oil circuit casing forms an oil circuit passage, and the air circuit casing forms an air circuit passage.

[0008] In one embodiment of the present application, the evaporation nozzle is spiral-shaped and is provided with an evaporation nozzle.

[0009] In one embodiment of the present application, the jet tubes are arranged in multiple groups on the mounting plate around the axis of the annular cavity, and each group of the jet tubes is located on the same concentric circle of the annular cavity.

[0010] In one embodiment of the present application, each group of the jet tubes forms a jet tube group, and the diameter of the jet tubes in the jet tube group close to the wall of the annular cavity is larger than the diameter of the jet tubes in the jet tube group far from the wall of the annular cavity.

[0011] In one embodiment of the present application, the spiral direction of the jet tube is consistent with the direction in which the evaporation nozzles are arranged in a ring shape in a preset order around the axis of the annular cavity.

[0012] In one embodiment of the present application, a plurality of main combustion holes are provided on the inner flame ring and the outer flame ring at one end close to the mounting plate, and a plurality of mixing holes are provided on the inner flame ring and the outer flame ring at one end away from the mounting plate.

[0013] On the other hand, an engine is provided, which is equipped with the above-mentioned flame tube.

[0014] On the other hand, a helicopter is provided, which is equipped with the above-mentioned engine.

[0015] The flame tube technical solution of the present application has the following advantages compared with the prior art:

[0016] (1) The integral annular vortex formed in the annular cavity in the present application effectively reduces the number of fuel nozzles, effectively improves the cross-flame capability, and can reduce or even remove the fuel nozzles specifically used for ignition, thereby simplifying the engine structure.

[0017] (2) The spirally arranged jet tube in the present application enables the oil-gas mixture in the annular cavity to move along a spiral trajectory, and after being completely evaporated and mixed evenly, it is sprayed into the combustion zone at multiple points and evenly distributed in the combustion reflux zone, so that the oil-gas mixture retains a long residence time in the flame tube, the flame is stable, the combustion is complete, the combustion efficiency is improved, the maximum temperature inside the combustion zone is reduced, the local high-temperature zone is reduced, and the outlet temperature field of the combustion chamber is improved, which is beneficial to extend the service life of the combustion chamber and turbine components, reduce the heat resistance requirements of the materials of the combustion chamber and turbine components, and improve the economy of the engine. At the same time, there is less exhaust smoke and low nitrogen oxide emissions, so that the engine meets higher low-pollution emission requirements.

[0018] (3) In the present application, the evaporator tubes are arranged in a ring-shaped manner in a preset order around the axis of the annular cavity at the mounting plate on the flame tube. Compared with the evaporator tubes arranged along the axis of the flame tube in the prior art, the flame tube of the present application can effectively shorten the length of the flame tube and reduce the weight of the flame tube.

[0019] (4) In the present application, after the evaporator tube is connected to the fuel nozzle, one end of the flame tube is connected to the turbine inlet guide on the engine through the mounting portion, and the other end is connected to the fuel nozzle through the evaporator tube, thereby improving the reliability of the flame tube connection. The double bird beak fixed design structure can increase the vibration resistance of the flame tube and extend the life of the flame tube. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0021] Figure 1 It is a first structural schematic diagram of the flame tube of the present application;

[0022] Figure 2 is a second structural schematic diagram of the flame tube of the present application;

[0023] Figure 3 is a third structural schematic diagram of the flame tube of the present application;

[0024] Figure 4 It is a structural schematic diagram of the evaporation tube of the flame tube of the present application;

[0025] Figure 5 is a cross-sectional view of the evaporation tube of the flame tube of the present application;

[0026] Figure 6 It is a structural schematic diagram of the jet tube group of the flame tube of the present application;

[0027] Figure 7 It is a schematic diagram of the ring vortex formation at the flame tube head of the present application.

[0028] Description of the Figures in the Specification:

[0029] 1. Flame inner ring; 2. Flame outer ring; 3. Opening; 4. Mounting plate; 5. Evaporation tube; 6. Annular cavity; 7. Converging pipe; 8. Evaporation nozzle; 9. Jet tube; 10. Mounting hole; 11. Oil casing; 12. Gas casing; 13. Air inlet cavity; 14. Air vent; 15. Oil passage; 16. Gas passage; 17. Evaporation nozzle; 18. Main combustion hole; 19. Mixing hole; 20. Mounting part. DETAILED DESCRIPTION

[0030] In order to make the purpose, technical solutions and advantages of this application clearer, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the drawings in the embodiments of this application. Obviously, the described embodiments are only part of the embodiments of this application, not all of them. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0031] Embodiment 1

[0032] Reference Figure 1 to Figure 7 As shown, the flame tube of the present application includes an inner flame ring 1 and an outer flame ring 2, one end of the inner flame ring 1 and the outer flame ring 2 are provided with an opening 3, the other end of the inner flame ring 1 and the outer flame ring 2 are connected by a mounting plate 4, a plurality of evaporation tubes 5 are installed on the mounting plate 4, an annular cavity 6 is formed between the inner flame ring 1, the outer flame ring 2 and the mounting plate 4, the evaporation tube 5 includes a confluence pipe 7 and an evaporation nozzle 8, the evaporation nozzle 8 is located in the annular cavity 6 and a plurality of the evaporation nozzles 8 are arranged in a ring shape around the axis of the annular cavity 6 in a preset order, a plurality of jet tubes 9 are arranged on the mounting plate 4, a plurality of the jet tubes 9 are connected to the annular cavity 6, and a plurality of the jet tubes 9 are arranged in a spiral shape around the axis of the annular cavity 6.

[0033] The flame tube of the present application includes an inner flame ring 1 and an outer flame ring 2. An opening 3 is set at one end of the inner flame ring 1 and the outer flame ring 2. The other end of the inner flame ring 1 and the outer flame ring 2 are connected by a mounting plate 4. The end connected by the mounting plate 4 is called the flame tube head; the ends of the inner flame ring 1 and the outer flame ring 2 at the end with the opening 3 are provided with a mounting portion 20. The mounting portion 20 is such as a flame tube outer ring beak and a flame tube inner ring beak. The flame tube is connected to the turbine inlet guide (not shown in the figure) on the engine through the mounting portion 20, that is, through the flame tube outer ring beak and the flame tube inner ring beak. A plurality of evaporation tubes 5 are installed on the mounting plate 4 of the flame tube. An annular cavity 6 is formed between the inner flame ring 1, the outer flame ring 2 and the mounting plate 4. The oil-gas mixed fluid is ignited and organized to burn in the annular cavity 6. The evaporation tube 5 includes a confluence pipe 7 and an evaporation nozzle 8. The evaporation nozzle 8 on the evaporation tube 5 is located in the annular cavity 6 and a plurality of evaporation nozzles 8 are arranged in a ring shape around the axis of the annular cavity 6 in a preset order, such as Figure 3 As shown, the evaporation nozzles 8 can be arranged in a clockwise or counterclockwise manner, as long as the order of all evaporation tubes 5 along the axis of the annular cavity 6 is consistent. The evaporation tubes 5 are arranged in a ring-shaped manner in a preset order around the axis of the annular cavity 6 at the mounting plate 4 on the flame tube. Compared with the evaporation tubes arranged along the axis of the flame tube in the prior art, the flame tube of the present application can effectively shorten the length of the flame tube and reduce the weight of the flame tube. A plurality of jet tubes 9 are arranged on the mounting plate 4, and the plurality of jet tubes 9 are connected to the annular cavity 6, and the plurality of jet tubes 9 are arranged in a spiral shape around the axis of the annular cavity 6, as shown in FIG. Figure 1 As shown, specifically, the angle between the jet tube 9 and the mounting plate 4 is 15° to 60°, preferably 35°; the inner diameter of the jet tube 9 is Φ2mm to Φ8mm, preferably Φ4.5mm; further, when the fuel enters the evaporation tube 5 and is atomized and evaporated through the evaporation nozzle 17 on the evaporation tube 5 to form combustion gas, at the same time, the air in the two channels formed by the combustion chamber casing and the flame tube casing (flame outer ring 2) on the engine flows into the annular cavity 6 through the spirally inclined jet tube 9. The air passing through the jet tube 9 will cause the airflow in the annular cavity 6 to form an integral annular vortex under the force of the direction of the jet tube 9, as shown in FIG. Figure 7 Schematic diagram of ring vortex formation ( Figure 7There is an arrow at the middle jet tube 9, and the arrow is along the axial direction of the jet tube 9), which further promotes the combustion gas formed after the eruption from the evaporation tube 5 to form an integral annular vortex. The integral annular vortex in the annular cavity 6 effectively avoids the appearance of independent annular vortices, can effectively eliminate or reduce the appearance of local hot spots, and improve the uniformity of fuel distribution in the combustion chamber of the gas turbine engine. The design of the evaporation tube 5 arranged in an annular shape can shorten the overall length of the flame tube, reduce the weight of the flame tube, and improve the combustion efficiency and the combustion chamber outlet temperature performance. The evaporation tubes 5 are evenly arranged in 3 to 6 numbers, and the corresponding number of evaporation tubes 5 is set according to the specific space size of the annular cavity 6 on the flame tube. In the prior art, the flame tube is fixed by external screws, or the flame tube is fixed by the fuel nozzle, or the flame tube is overlapped with the turbine inlet guide (not shown in the figure) on the engine through the mounting portion 20. Compared with the above prior art, after the evaporation tube 5 is connected to the fuel nozzle, one end of the flame tube is connected to the turbine inlet guide (not shown in the figure) on the engine through the mounting portion 20, and the other end is connected to the fuel nozzle through the evaporation tube 5, which improves the reliability of the flame tube connection. The double bird beak fixed design structure can increase the vibration resistance of the flame tube and extend the life of the flame tube. In addition, the overall annular vortex formed in the annular cavity 6 effectively reduces the number of fuel nozzles, effectively improves the flame connection capability, and can reduce or even remove the fuel nozzles specifically used for ignition, thereby simplifying the engine structure. The spirally arranged jet tube 9 allows the oil-gas mixed fluid in the annular cavity 6 to move along a spiral trajectory, and after complete evaporation and uniform mixing, it is sprayed into the combustion zone at multiple points and evenly distributed in the combustion reflux zone, so that the oil-gas mixed fluid resides in the flame tube for a long time, the flame is stable, the combustion is complete, the combustion efficiency is improved, the maximum temperature inside the combustion zone is reduced, the local high-temperature zone is reduced, and the outlet temperature field of the combustion chamber is improved, which is beneficial to extend the service life of the combustion chamber and turbine components, reduce the heat resistance requirements of the materials of the combustion chamber and turbine components, and improve the economy of the engine. At the same time, there is less exhaust smoke and low nitrogen oxide emissions, so that the engine meets higher low-pollution emission requirements.

[0034] In one embodiment, a plurality of mounting holes 10 are provided on the mounting plate 4 , and the manifold 7 includes an oil casing 11 , an air casing 12 is disposed outside the oil casing 11 , and the air casing 12 is installed in the mounting holes 10 .

[0035] like Figure 1 As shown, the mounting plate 4 is provided with a plurality of mounting holes 10 for mounting the evaporation tube 5. The evaporation tube 5 includes a manifold 7 and an evaporation nozzle 8. The manifold 7 includes an oil sleeve 11 and a gas sleeve 12. The gas sleeve 12 is sleeved on the outer edge of the oil sleeve 11. The outer edge of the gas sleeve 12 is mounted in the mounting hole 10, thereby realizing the mutual connection between the evaporation tube 5 and the mounting plate 4.

[0036] In one embodiment, an air intake cavity 13 is formed between the air circuit casing 12 and the oil circuit casing 11. The oil circuit casing 11 is provided with a plurality of air vents 14. The air intake cavity 13 is connected to the oil circuit casing 11 through the air vents 14. The oil circuit casing 11 forms an oil circuit passage 15, and the air circuit casing 12 forms an air circuit passage 16.

[0037] like Figure 4 and Figure 5 As shown, the gas sleeve 12 is open on the side close to the oil inlet pipe, and is connected to the oil sleeve 11 on the side close to the evaporation nozzle 8, and is closed. An air inlet cavity 13 is formed between the gas sleeve 12 and the oil sleeve 11, and a plurality of vents 14 are provided on the oil sleeve 11. The vents 14 connect the air inlet cavity 13 with the oil sleeve 11, and the oil sleeve 11 forms the oil passage 15, and the gas sleeve 12 forms the air passage 16. Therefore, the fuel first flows from the oil inlet pipe into the oil sleeve 11; at the same time, the air enters the air inlet cavity 13, and then enters the oil sleeve 11 through the vents 14, and mixes with the fuel to form an oil-gas mixed fluid, which is ejected from the evaporation nozzle 8 through the evaporation nozzle 17 to the annular cavity 6 on the flame tube, and forms an annular vortex under the flow force of the air in the jet tube 9, and further organizes combustion after ignition. The air passing through the vent hole 14 has a shearing effect on the fuel in the oil sleeve 11, thereby promoting the atomization ability of the fuel.

[0038] In one embodiment, the evaporation nozzle 8 is spiral-shaped, and an evaporation nozzle 17 is disposed on the evaporation nozzle 8 .

[0039] like Figure 4 As shown, the evaporation tube 5 is spiral-shaped. With the help of the evaporation nozzle 17, the evaporation nozzle 8 of the same length can effectively increase the residence time of the fuel in the evaporation nozzle 8, and can effectively improve the evaporation and atomization effect of the fuel. Furthermore, when the fuel in the oil inlet pipe passes through the evaporation tube 5, since the evaporation tube 5 is located in the flame tube, the internal high temperature of the flame tube will exchange heat with the high temperature of the oil-gas mixed fluid in the evaporation tube 5, so that the oil-gas mixed fluid in the evaporation tube 5 is fully evaporated and atomized, and the oil-gas mixed fluid is finally ejected through the evaporation nozzle 17 on the evaporation tube 5 to organize combustion.

[0040] In one embodiment, a plurality of groups of the jet tubes 9 are arranged on the mounting plate 4 around the axis of the annular cavity 6 , and each group of the jet tubes 9 is located on the same concentric circle of the axis of the annular cavity 6 .

[0041] Figure 1 A group of jet tubes 9 are arranged on the mounting plate 4 (arranged in a circle around the axis of the annular cavity 6 on the mounting plate 4), except for Figure 1In addition to the set of jet tubes 9 shown, multiple sets of jet tubes 9 can be provided according to the width of the mounting plate 4, such as Figure 6 As shown, each group of jet tubes 9 forms a concentric circle around the annular cavity 6. Therefore, from the axis of the annular cavity 6 to the outside, multiple groups of jet tubes 9 can be arranged on the mounting plate 4 around the axis of the annular cavity 6, which can effectively improve the vortex capacity and avoid or reduce the occurrence of local hot spots.

[0042] In one embodiment, each group of the jet tubes 9 forms a jet tube group, and the diameter of the jet tube 9 in the jet tube group close to the wall of the annular cavity 6 is larger than the diameter of the jet tube 9 in the jet tube group far from the wall of the annular cavity 6.

[0043] When multiple groups of jet tubes 9 are provided, each group of jet tubes 9 forms a jet tube group. Figure 6 As shown in the schematic diagram, the diameter of the jet tube 9 in the jet tube group close to the wall of the annular cavity 6 is smaller than the diameter of the jet tube 9 in the jet tube group far from the wall of the annular cavity 6. This can improve the fluidity of the airflow near the inside of the annular cavity 6 in the annular cavity 6, promote the formation of annular vortex inside the annular cavity 6, and make most of the gas burn inside the annular cavity 6, avoiding the excessive temperature at the wall of the annular cavity 6 or the excessive temperature in the combustion chamber, which affects the life of the flame tube. In addition, along the radial direction of the annular cavity 6, the radial distance between two adjacent groups of jet tube groups is evenly distributed. Generally, 1 to 4 groups of jet tubes 9 are arranged on the mounting plate 4, and each group of jet tubes has 6 to 24 jet tubes. Further, the aperture of the jet tube 9 is set to match the number of jet tubes 9. When the number of jet tubes 9 is increased, the aperture of the jet tube 9 needs to be appropriately reduced according to actual needs.

[0044] In one embodiment, the spiral direction of the jet tube 9 is consistent with the direction in which the evaporation nozzles 8 are arranged in a ring shape in a preset order around the axis of the annular cavity 6 .

[0045] The evaporation nozzle 8 on the evaporation tube 5 is located in the annular cavity 6 and the multiple evaporation nozzles 8 are arranged in a ring in a preset order around the axis of the annular cavity 6 (clockwise or counterclockwise). Further, the spiral direction of the jet tube 9 is consistent with the direction in which the evaporation nozzles 8 are arranged in a ring in a preset order around the axis of the annular cavity 6, that is, if the spiral direction of the jet tube 9 is in the clockwise direction, the arrangement direction of the evaporation tube 5 in the annular cavity 6 is also in the clockwise direction; if the spiral direction of the jet tube 9 is in the counterclockwise direction, the arrangement direction of the evaporation tube 5 in the annular cavity 6 is also in the counterclockwise direction. The spiral direction of the jet tube 9 is: the end of the jet tube 9 away from the mounting plate 4 points to the direction of the end of the jet tube 9 close to the mounting plate 4.

[0046] In one embodiment, a plurality of main combustion holes 18 are provided on the flame inner ring 1 and the flame outer ring 2 at one end close to the mounting plate 4 , and a plurality of mixing holes 19 are provided on the flame inner ring 1 and the flame outer ring 2 at one end away from the mounting plate 4 .

[0047] The inner flame ring 1 and the outer flame ring 2 are both provided with main combustion holes 18 and mixing holes 19. The inner flame ring 1 and the outer flame ring 2 are provided with multiple main combustion holes 18 at one end close to the mounting plate 4, and the inner flame ring 1 and the outer flame ring 2 are provided with multiple mixing holes 19 at one end away from the mounting plate 4. The main combustion holes 18 and the mixing holes 19 both serve as air intake. The air intake of the main combustion holes 18 on the flame inner ring 1 and the main combustion holes 18 on the flame outer ring 2 accounts for about 20% to 40% of the total air volume of the gas combustion chamber, and the air intake of the mixing holes 19 on the flame inner ring 1 and the mixing holes 19 on the flame outer ring 2 accounts for about 20% to 40% of the total air volume of the gas combustion chamber. The entire flame tube is cooled by diverging holes (that is, diverging holes are arranged on the wall surfaces of the flame inner ring 1 and the flame outer ring 2, not shown in the figure), and the air intake of the diverging holes accounts for about 10% to 30% of the total air volume of the gas combustion chamber. The aperture of the diverging holes is 0.2mm to 1.0mm, preferably 0.5mm, and is evenly distributed on the cavity wall of the annular cavity 6 on the flame tube according to the gas distribution design. The diverging holes can cool the cavity walls of the flame inner ring 1 and the flame outer ring 2 to prevent the cavity walls of the flame outer ring 2 and the flame inner ring 1 from being too hot under the combustion of gas and reducing the life of the flame tube. Air enters the flame tube through the main combustion hole 18 for combustion. The air passing through the mixing hole 19 can mix with the combustion gas in the flame tube, reducing the temperature of the combustion gas and controlling the temperature distribution at the combustion chamber outlet to meet the requirements of the turbine. It can also play a role in cooling and protecting the flame tube.

[0048] The fuel flow process is as follows:

[0049] like Figure 5 As shown, the fuel first flows from the fuel inlet pipe into the oil sleeve 11 on the evaporation pipe 5; at the same time, the air passes through the gas path 16 ( Figure 5 The solid arrow (with dotted arrow tail) enters the air inlet chamber 13, then enters the oil casing 11 through the vent hole 14, and connects with the oil passage 15 ( Figure 5 The fuel in the hollow arrow (solid arrow tail) is mixed to form an oil-gas mixed fluid ( Figure 5The solid arrow in the middle has a solid line at the tail end of the arrow); the oil-gas mixture flows to the evaporation nozzle 8, is ejected out of the evaporation nozzle 8 through the evaporation nozzle 17 of the evaporation nozzle 8, and is finally ignited in the flame tube to organize combustion; wherein, a portion of the airflow enters the flame tube from the main combustion holes 18 of the flame outer ring 2 and the main combustion holes 18 of the flame inner ring 1, and a portion of the airflow is ejected into the flame tube head (one end of the flame tube with a mounting plate 4) through the jet tube 9, and an annular vortex recirculation zone is formed in the entire flame tube near the mounting plate 4 area, and at the same time, the oil-gas mixture airflow of fuel and air will be ejected from the evaporation nozzles 17 on the evaporation nozzle 8 at different positions on the evaporation tube 5 and in different directions, and the oil-gas mixture is evenly distributed in the recirculation zone, and after ignition, it organizes combustion and quickly forms a linked flame, and a portion of the remaining air is mixed with the burned gas through the mixing holes 19 of the flame outer ring 2 and the mixing holes 19 of the flame inner ring 1, and a portion of it is cooled on the flame tube wall through the divergent holes.

[0050] Embodiment 2

[0051] An engine is equipped with the flame tube of embodiment 1. The engine using the flame tube of embodiment 1 can effectively improve the fuel efficiency of the engine on the basis of improving the uniformity of fuel distribution by the flame tube, so that the fuel burns more completely and the nitrogen oxide emission is lower.

[0052] Embodiment 3

[0053] A helicopter is equipped with the engine of the second embodiment. The helicopter using the engine of the second embodiment can effectively reduce the fuel cost of the helicopter on the basis of improving the uniformity of fuel distribution in the flame tube and improving the fuel efficiency of the engine.

[0054] Note that the above are only preferred embodiments of the present application and the technical principles used. Those skilled in the art will understand that the present application is not limited to the specific embodiments described herein, and that various obvious changes, readjustments and substitutions can be made by those skilled in the art without departing from the scope of protection of the present application. Therefore, although the present application is described in more detail through the above embodiments, the present application is not limited to the above embodiments, and may include more other equivalent embodiments without departing from the concept of the present application, and the scope of the present application is determined by the scope of the appended claims.

Claims

1. A flame tube, characterized in that: The invention comprises an inner flame ring (1) and an outer flame ring (2), one end of each of the inner flame ring (1) and the outer flame ring (2) is provided with an opening (3), the other end of each of the inner flame ring (1) and the outer flame ring (2) is connected via a mounting plate (4), a plurality of evaporation tubes (5) are mounted on the mounting plate (4), an annular cavity (6) is formed between the inner flame ring (1), the outer flame ring (2) and the mounting plate (4), the evaporation tube (5) comprises a converging pipe (7) and an evaporation nozzle (8), the evaporation nozzle (8) is located in the annular cavity (6), and a plurality of the evaporation nozzles (8) surround the annular cavity (6). ) are arranged in a ring shape according to a preset order, a plurality of jet tubes (9) are arranged on the mounting plate (4), the plurality of jet tubes (9) are connected to the annular cavity (6), and the plurality of jet tubes (9) are arranged in a spiral shape around the axis of the annular cavity (6); a plurality of groups of jet tubes (9) are arranged on the mounting plate (4) around the axis of the annular cavity (6), each group of jet tubes (9) forms a jet tube group, and the diameter of the jet tube (9) in the jet tube group close to the cavity wall of the annular cavity (6) is smaller than the diameter of the jet tube (9) in the jet tube group far from the cavity wall of the annular cavity (6).

2. The flame tube according to claim 1, characterized in that: The mounting plate (4) is provided with a plurality of mounting holes (10), the manifold (7) comprises an oil circuit sleeve (11), an air circuit sleeve (12) is disposed outside the oil circuit sleeve (11), and the air circuit sleeve (12) is mounted in the mounting hole (10).

3. The flame tube according to claim 2, characterized in that: An air intake cavity (13) is formed between the air circuit sleeve (12) and the oil circuit sleeve (11); a plurality of air vents (14) are provided on the oil circuit sleeve (11); the air intake cavity (13) is connected to the oil circuit sleeve (11) through the air vents (14); the oil circuit sleeve (11) forms an oil circuit passage (15); and the air circuit sleeve (12) forms an air circuit passage (16).

4. The flame tube according to claim 1, characterized in that: The evaporation nozzle (8) is spiral-shaped and is provided with an evaporation nozzle opening (17).

5. The flame tube according to claim 1, characterized in that: Each group of the jet tubes (9) is located on the same concentric circle of the axis of the annular cavity (6).

6. The flame tube according to claim 1, characterized in that: The spiral direction of the jet tube (9) is consistent with the direction in which the evaporation nozzles (8) are arranged in a ring shape in a preset order around the axis of the annular cavity (6).

7. The flame tube according to claim 1, characterized in that: A plurality of main combustion holes (18) are provided on the ends of the inner flame ring (1) and the outer flame ring (2) close to the mounting plate (4), and a plurality of mixing holes (19) are provided on the ends of the inner flame ring (1) and the outer flame ring (2) away from the mounting plate (4).

8. An engine comprising the flame tube according to any one of claims 1 to 7.

9. A helicopter comprising the engine according to claim 8.

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