Combustion components and aircraft engines

Abstract

This invention relates to the field of aero-engine technology, disclosing a combustion assembly and an aero-engine. The invention includes: a flame tube; an evaporator tube comprising a main pipe and several branch pipes, one end of the main pipe forming an evaporator tube inlet, the branch pipes corresponding to the other end of the main pipe, and the ends of the branch pipes away from the main pipe forming several evaporator tube outlets, which are located within the flame tube; and a fuel supply structure connected to the evaporator tube inlet. This invention, by arranging the branched evaporator tubes in a blood vessel-like pattern on the flame tube, increases the probability of fuel breaking up upon impact with the wall under the action of the branched structure, resulting in better fuel atomization. Simultaneously, because the branched evaporator tubes have a larger contact area with the hot wall surface, they absorb more heat, thus allowing the fuel to be heated more fully, thereby evaporating more fuel and ultimately improving combustion efficiency.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, specifically to combustion components and aero-engines. Background Technology

[0002] Modern small and medium-sized aero-engine combustors typically employ annular multi-swirl combustors or annular evaporator combustors. In annular evaporator combustors, evaporator tubes are usually distributed on the flame tube, with their inlets extending outwards from the flame tube and connecting to multiple direct-injection nozzles on the fuel manifold. Serving as fuel atomization and air-fuel mixing devices, evaporator tubes not only compensate for the poor atomization quality of direct-injection nozzles but also heat air and liquid fuel, and mix air and fuel vapors. However, since the invention of evaporator tubes, problems such as weak interaction between liquid fuel and air within the evaporator tube, insufficient fuel heating within the evaporator tube, and insufficient turbulence intensity within the evaporator tube have persisted. Summary of the Invention

[0003] In view of this, the present invention provides a combustion assembly and an aircraft engine to solve the problems of poor fuel atomization in the evaporator tube and poor fuel combustion in the flame tube.

[0004] In a first aspect, the present invention provides a combustion assembly, comprising: a flame tube; an evaporation tube including a main pipe and a plurality of branch pipes, one end of the main pipe forming an evaporation tube inlet, the branch pipes being disposed corresponding to the other end of the main pipe, the ends of the plurality of branch pipes away from the main pipe forming a plurality of evaporation tube outlets, the plurality of evaporation tube outlets being located inside the flame tube; and an oil supply structure communicating with the evaporation tube inlet.

[0005] Beneficial effects: By redesigning traditional single-tube or T-type / multi-outlet evaporator tubes into a branched evaporator tube structure resembling blood vessels, the evaporator tubes are arranged in a vascular shape on the flame tube. This allows both fuel and air to circulate within each evaporator tube. The branched structure increases turbulence, improves the probability of fuel impact and breakup against the flame tube walls, and enhances atomization and atomization. Simultaneously, because the branched evaporator tube has a larger contact area with the hot wall of the flame tube compared to conventional fuel-air premixing devices, it absorbs more heat. Therefore, the branched evaporator tube allows for more complete heating of the fuel, resulting in more fuel evaporation, increasing the fuel evaporation rate of the evaporator tube, and ultimately improving combustion performance.

[0006] In one optional embodiment, the branching pipeline includes a base pipe and a plurality of branch pipes, one end of the base pipe being connected to the main pipeline, the branch pipes being disposed corresponding to the other end of the base pipe, and a plurality of evaporator outlets being disposed corresponding to the ends of the branch pipes away from the base pipe; and / or, the branching pipeline includes an output pipe, one end of the output pipe being connected to the main pipeline or the base pipe, and the other end of the output pipe forming the evaporator outlet.

[0007] In one alternative implementation, the branch pipe has a bifurcated structure.

[0008] Beneficial effects: By designing the evaporator pipe into a multi-stage branching structure with one main pipe and multiple branch pipes, the original single pipe and single inlet / outlet form can be changed to a multi-outlet form. On the one hand, it can improve the fuel atomization and evaporation effect, and on the other hand, it can achieve simultaneous fuel supply at different locations and multiple points, improving the uniformity of the oil and gas distribution throughout the ring.

[0009] In one optional embodiment, the flow direction of the evaporator inlet is set at an angle α of 20°-40° with the axis of the flame tube.

[0010] Beneficial effects: By designing the evaporator tube to be arranged at an angle near the outer ring of the flame tube, the airflow swirl angle at the evaporator tube inlet and the compressor outlet is matched, resulting in a more uniform oil-gas matching.

[0011] In one optional embodiment, the flow direction of the evaporator outlet is set at an angle β of 20°-50° with the axis of the flame tube.

[0012] Beneficial effects: By controlling the direction of the evaporator tube outlet, the jet direction of the oil-gas mixture when entering the flame tube is adjusted, so as to realize the circumferential flow of the oil-gas mixture in the flame tube, thereby avoiding the problem of the oil-gas mixture at the evaporator tube outlet directly contacting the flame tube wall and burning, causing ablation.

[0013] In one alternative implementation, the sum of the cross-sectional areas of the plurality of base pipes is the same as the cross-sectional area of ​​the main pipeline.

[0014] Beneficial effects: By controlling the flow area of ​​the branched pipe, the flow area of ​​the evaporator pipe gradually decreases from the evaporator pipe inlet to the evaporator pipe outlet, thereby avoiding the problem of evaporator pipe burn-out caused by backflow of oil-gas mixture.

[0015] In one optional embodiment, two branch pipes are provided, and the central axis of the outlet of the main pipe is the angle bisector of the angle between the two base pipes.

[0016] Beneficial effect: By controlling the bifurcation angle of the branch pipe, the distribution of the oil-gas mixture at the outlet of the evaporator pipe is ensured to be basically consistent.

[0017] In one optional embodiment, the branch pipe is connected to the main pipe at a position between 1 / 3 and 2 / 3 of the total length of the evaporator pipe.

[0018] Beneficial effects: By controlling the branching position of the branch pipe, the fuel is fully broken up by impacting the walls inside the evaporator pipe, thereby improving the fuel atomization effect.

[0019] In one alternative embodiment, the fuel supply structure includes a fuel main and a direct-injection nozzle, the fuel main being connected to the direct-injection nozzle, the direct-injection nozzle being inserted into the evaporator inlet.

[0020] Beneficial effects: By arranging the fuel supply structure outside the combustion chamber casing and bending it to insert it into the evaporator pipe inlet direction or directly radially, while allowing air to flow in along the evaporator pipe inlet, the assembly difficulty of the fuel main and direct injection nozzle can be reduced and the assembly efficiency improved.

[0021] Secondly, the present invention also provides an aircraft engine including the combustion components described above. Attached Figure Description

[0022] 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.

[0023] Figure 1 This is a front view of the combustion assembly according to an embodiment of the present invention;

[0024] Figure 2 for Figure 1 A three-dimensional view of the combustion assembly shown;

[0025] Figure 3 for Figure 1 A top view of the combustion assembly shown;

[0026] Figure 4 This is a partial structural schematic diagram of the oil supply structure according to an embodiment of the present invention;

[0027] Figure 5 This is a schematic diagram of another embodiment of the evaporator tube of the present invention.

[0028] Explanation of reference numerals in the attached figures:

[0029] 1. Flame tube; 2. Evaporator tube; 201. Main pipe; 202. Branch pipe; 2021. Base pipe; 2022. Branch pipe; 2023. Output pipe; 203. Evaporator tube inlet; 204. Evaporator tube outlet; 3. Fuel supply structure; 301. Fuel main pipe; 3011. Fuel outlet pipe; 302. Direct injection nozzle; 3021. Pipe connector. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. 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.

[0031] The following is combined with Figures 1 to 5 The following describes embodiments of the present invention.

[0032] According to embodiments of the present invention, in one aspect, such as Figures 1 to 3 As shown, a combustion assembly is provided, including: a flame tube 1, an evaporator tube 2, and an oil supply structure 3. The evaporator tube 2 includes a main pipe 201 and several branch pipes 202. One end of the main pipe 201 forms an evaporator tube inlet 203, and the branch pipes 202 are arranged corresponding to the other end of the main pipe 201. The ends of the several branch pipes 202 away from the main pipe 201 form several evaporator tube outlets 204, and the several evaporator tube outlets 204 are located inside the flame tube 1; the oil supply structure 3 is connected to the evaporator tube inlet 203.

[0033] By redesigning traditional single-tube or T-type / multi-outlet evaporator tubes into a branched evaporator tube 2 structure resembling a blood vessel, the evaporator tubes 2 are arranged in a blood vessel shape on the flame tube 1. This allows both fuel and air to circulate within each evaporator tube 2. The branched structure increases turbulence, improves the probability of fuel impact and breakup against the flame tube wall, and enhances atomization and breakup effects. Simultaneously, because the branched evaporator tube 2 has a larger contact area with the hot wall of the flame tube 1 compared to conventional fuel-air premixing devices, it absorbs more heat. Therefore, the branched evaporator tube 2 allows for more complete heating of the fuel, resulting in more fuel evaporation, increasing the fuel evaporation rate of the evaporator tube 2, and ultimately improving combustion performance.

[0034] In one embodiment, such as Figures 1 to 3As shown, the branch pipe 202 includes a base pipe 2021 and several branch pipes 2022. One end of the base pipe 2021 is connected to the main pipe 201, and the branch pipes 2022 are set at the other end of the base pipe 2021. Several evaporator outlets 204 are set at the ends of the branch pipes 2022 away from the base pipe 2021. And / or, the branch pipe 202 includes an output pipe 2023. One end of the output pipe 2023 is connected to the main pipe 201 or the base pipe 2021, and the other end of the output pipe 2023 forms an evaporator outlet 204.

[0035] Specifically, in one embodiment of the evaporator tube 2, such as Figure 1 As shown, the main pipe 201 is connected to two branch pipes 202, each branch pipe 202 including a base pipe 2021 and two branch pipes 2022. In another specific embodiment of the evaporator pipe 2, as... Figure 5 As shown, the main pipe 201 is connected to two branch pipes 202. One branch pipe 202 includes an output pipe 2023, and the other branch pipe 202 includes an output pipe 2023 and a branch pipe 2022. During the branching process, the evaporator pipe 2 can adopt a two-way structure, a three-way structure, or a multi-way structure, depending on the actual structure of the combustion chamber and the internal flow state of the evaporator pipe 2 and the combustion chamber flame tube 1.

[0036] In one embodiment, such as Figures 1 to 3 As shown, branch pipe 2022 has a bifurcated structure. By designing evaporator pipe 2 as a multi-stage bifurcated structure with one main pipe and multiple branch pipes, the original single pipe and single inlet / outlet form is changed to a multi-outlet form. On the one hand, this can improve the fuel atomization and evaporation effect, and on the other hand, it can realize simultaneous fuel supply at different locations and multiple points, improving the uniformity of the oil and gas distribution throughout the ring.

[0037] It is worth noting that the overall deflection direction of the evaporator tube 2 can be different. By designing the evaporator tube 2 as a multi-directional deformation structure, multiple outlets of the oil-gas mixture in the evaporator tube 2 can be arranged to achieve the effect of multi-point injection.

[0038] It should be further explained that the bifurcation structure of the evaporator tube 2 is not necessarily limited to the annular surface that matches the annular structure. Depending on the actual combustion chamber structure, the branch pipes 2022 formed by the bifurcation of the evaporator tube 2 can be arranged at any angle in space. The branch pipes 2022 can also be partially or completely inserted into the flame tube 1 to directly contact the high-temperature gas.

[0039] In one embodiment, such as Figure 1As shown, the flow direction of the evaporator inlet 203 is set at an angle α of 20°-40° with the axis of the flame tube 1. By designing the evaporator 2 to be arranged at an angle near the outer ring of the flame tube 1, the evaporator inlet 203 is matched with the airflow cosmog angle at the compressor outlet, resulting in more uniform oil-gas matching.

[0040] In one embodiment, such as Figure 2 As shown, the flow direction of the evaporator outlet 204 is set at an angle β of 20°-50° with the axis of the flame tube 1. By controlling the direction of the evaporator outlet 204, the jet direction of the oil-gas mixture when entering the flame tube 1 is adjusted, so that the oil-gas mixture flows circumferentially in the flame tube 1, thereby avoiding the problem of the oil-gas mixture at the evaporator outlet 204 directly contacting the wall of the flame tube 1 and burning, causing ablation.

[0041] It is worth noting that the present invention utilizes the adjustable shape and size of the evaporator tube 2 to arrange multiple evaporator tube outlets 204. Combined with the different combustion states in the flame tube 1, the position, direction, and flow rate of the oil-gas mixture injected into the flame tube 1 from the evaporator tube outlet 204 are controlled, thereby reducing the combustion temperature of the oil-gas mixture in the main combustion zone of the combustion chamber and reducing the pollution emissions from the combustion chamber.

[0042] In one embodiment, such as Figure 1 As shown, the sum of the cross-sectional areas of several base pipes 2021 is the same as the cross-sectional area of ​​the main pipe 201. By controlling the flow area of ​​the branch pipes 202, the flow area of ​​the evaporator pipe 2 gradually decreases from the evaporator pipe inlet 203 to the evaporator pipe outlet 204, thereby avoiding the problem of evaporator pipe 2 burning caused by backflow of oil-gas mixture.

[0043] In one embodiment, such as Figure 1 As shown, there are two branch pipes 202, and the central axis of the outlet of the main pipe 201 is the angle bisector of the angle between the two base pipes 2021. By controlling the branching angle of the branch pipes 202, the distribution of the oil-gas mixture at the outlet of the evaporator pipe 204 is ensured to be basically consistent.

[0044] In one embodiment, such as Figure 1 As shown, the connection point between the branch pipe 202 and the main pipe 201 is located at 1 / 3 to 2 / 3 of the total length of the evaporator pipe 2. By controlling the branching position of the branch pipe 202, the fuel is fully broken up by impact within the evaporator pipe 2, thereby improving the fuel atomization effect.

[0045] In one embodiment, such as Figure 4As shown, the fuel supply structure 3 includes a fuel main 301 and a direct-injection nozzle 302. The fuel main 301 is connected to the direct-injection nozzle 302, which is inserted into the interior of the evaporator inlet 203. By arranging the fuel supply structure 3 outside the combustion chamber casing 4 and bending it to insert it into the evaporator inlet 203 along the direction of the evaporator inlet 203 or directly radially, while allowing air to flow in along the evaporator inlet 203, the assembly difficulty of the fuel main 301 and the direct-injection nozzle 302 can be reduced and the assembly efficiency improved.

[0046] It is worth noting that in related technologies, aero-engine combustors typically employ annular multi-swirl combustors or annular evaporator combustor designs. Both configurations usually use centrifugal nozzles or direct-injection nozzles for fuel supply. Direct-injection nozzles have a simpler structure, with multiple nozzles arranged circumferentially within the annular combustor, typically matched with a single-line fuel manifold. For combustors employing a low-cost design philosophy, direct-injection nozzles and fuel manifolds are usually welded in sections using standard-specification tubing. However, for combustors with higher requirements, machining, surface fitting, and precision welding are used. Sectionally welded fuel manifolds and direct-injection nozzles, due to the large number of nozzles, solder penetration during machining, and deformation, are prone to issues such as significant circumferential unevenness in the manifold, leading to a large temperature difference between the hot spot at the combustor outlet and the surrounding environment, ultimately affecting the combustor's operational stability on the engine. Precision-machined fuel manifolds and direct-injection nozzles, on the other hand, may result in higher costs and more complex processes due to the larger number of nozzles and more mating surfaces.

[0047] Therefore, as Figure 4 As shown, in this embodiment of the invention, the direct-injection nozzle 302 is designed in a figure-7 shape to match the nozzle outlet with the evaporator inlet 203, and the outlet of the direct-injection nozzle 302 is inserted a certain distance into the evaporator inlet 203 to prevent fuel from splashing out of the evaporator inlet 203 during the operation of the combustion chamber. The direct-injection nozzle 302 is connected to the fuel outlet pipe 3011 extending from the fuel main pipe 301 via the pipe connector 3021. The outlet of the direct-injection nozzle 302 can be in various forms such as a direct injection port, a double / multiple oblique injection port, or a double / multiple vertical injection port. By controlling the relative position of the outlet of the direct-injection nozzle 302 and the inlet 203 of the evaporator pipe, as well as the number of nozzles at the outlet of the direct-injection nozzle 302 and the injection direction of the injection port, the fuel can be broken up by impacting the bifurcated structure of the evaporator pipe 2, and the fuel can be evenly distributed in each bifurcated pipe of the bifurcated evaporator pipe 2, thereby improving the uniformity of the fuel-air distribution inside the evaporator pipe 2 and ensuring that the fuel-air distribution at each evaporator pipe outlet 204 is uniform.

[0048] According to an embodiment of the present invention, in another aspect, an aircraft engine is also provided, including the combustion components described above.

[0049] When using the combustion assembly of this embodiment, firstly, fuel is supplied to the interior of the evaporator tube 2 from the evaporator tube inlet 203 through the fuel supply structure 3. Then, while receiving fuel from the fuel supply structure 3, the evaporator tube 2 also draws in fresh air from the annular cavity formed by the flame tube 1 and the combustion chamber casing 4. Next, inside the evaporator tube 2, the fuel is broken up by aerodynamic forces and fully mixed with air. It is heated and evaporated by the flame tube 1 and the evaporator tube 2 to form fuel vapor, which is further mixed with air and finally ejected from the evaporator tube outlet 204. The evaporator tube outlet 204 is tangentially injected along the outer ring of the flame tube 1. The ejected fuel-air mixture is further mixed with air under the action of the circumferential airflow inside the flame tube 1 and is ignited by the igniter in the main combustion zone. The high-temperature combustion gas formed enters the turbine components to do work, realizing the normal operation of the engine.

[0050] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A combustion assembly, characterized in that, include: Flame tube (1); Evaporator (2) includes a main pipe (201) and several branch pipes (202). One end of the main pipe (201) forms an evaporator inlet (203), and the branch pipes (202) are provided at the other end of the main pipe (201). The ends of the several branch pipes (202) away from the main pipe (201) form several evaporator outlets (204), and the several evaporator outlets (204) are located inside the flame tube (1). The oil supply structure (3) is connected to the evaporator inlet (203); The branching pipeline (202) includes a base pipe (2021) and several branch pipes (2022). One end of the base pipe (2021) is connected to the main pipeline (201), and each branch pipe (2022) is positioned corresponding to the other end of the base pipe (2021). Several evaporator outlets (204) are positioned corresponding to the ends of the branch pipes (2022) away from the base pipe (2021); and / or, The branch pipe (202) includes an output pipe (2023), one end of which is connected to the main pipe (201) or the base pipe (2021), and the other end of which forms the evaporator outlet (204).

2. The combustion assembly according to claim 1, characterized in that, The branch pipe (2022) has a bifurcated structure.

3. The combustion assembly according to claim 1 or 2, characterized in that, The flow direction of the evaporator inlet (203) is set at an angle α of 20°-40° with the axis of the flame tube (1).

4. The combustion assembly according to claim 3, characterized in that, The flow direction of the evaporator outlet (204) is set at an angle β of 20°-50° with the axis of the flame tube (1).

5. The combustion assembly according to claim 1, characterized in that, The sum of the cross-sectional areas of the plurality of the base pipes (2021) is the same as the cross-sectional area of ​​the main pipe (201).

6. The combustion assembly according to claim 1, characterized in that, There are two branch pipes (202), and the central axis of the outlet of the main pipe (201) is the angle bisector of the included angle of the two base pipes (2021).

7. The combustion assembly according to claim 6, characterized in that, The connection position between the branch pipe (202) and the main pipe (201) is at 1 / 3 to 2 / 3 of the total length of the evaporator pipe (2).

8. The combustion assembly according to claim 1, characterized in that, The fuel supply structure (3) includes a fuel main pipe (301) and a direct injection nozzle (302). The fuel main pipe (301) is connected to the direct injection nozzle (302), and the direct injection nozzle (302) is inserted into the interior of the evaporator inlet (203).

9. An aircraft engine, characterized in that, It includes the combustion assembly as described in any one of claims 1 to 8.

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