An aeroengine fuel nozzle

Abstract

The utility model discloses an aero-engine fuel nozzle belongs to aero-engine technical field, including the shell, the bottom fixed sleeve of shell has the outer thread pipe, the top end of outer thread pipe extends to the inner chamber of shell and is fixedly connected with the oil pipe. In the utility model, when the oil flows in the inner chamber of the oil pipe, the first ball plug is moved upward by the oil to overcome the elasticity of the first spring, so that the oil flows smoothly in the inner chamber of the oil pipe. When there is no oil flow, the first spring is used to drive the first ball plug to reset and block the inner chamber of the oil pipe. Similarly, when air flows in the inner chamber of the air inlet pipe, the second ball plug is moved upward by the air to overcome the elasticity of the second spring, so that the air flows smoothly in the inner chamber of the air inlet pipe. When there is no gas flow, the second spring is used to drive the second ball plug to reset and block the inner chamber of the air inlet pipe, avoiding air and oil backflow, and having good practicability.

Description

Technical Field

[0001] This utility model relates to the field of aero-engine technology, and more specifically, to an aero-engine fuel nozzle. Background Technology

[0002] Fuel nozzles for aircraft engines are key components in the design of combustion chambers in the field of aerospace engineering. Their main function is to atomize or vaporize fuel, accelerate the formation of air-fuel mixture to ensure stable combustion and improve combustion efficiency. The main types include centrifugal nozzles, pneumatic nozzles, evaporative nozzles and oil slinger nozzles.

[0003] According to the search, the publication number is CN214009272U A utility model patent discloses an aero-engine fuel injector with a high-temperature resistant structure, including an outer cover, an inner tube, a baffle plate, an air passage, a high-temperature resistant coating, an outer nozzle, a sealing layer, an inner nozzle, an air hole, a guide pipe, an oil connection pipe, a gas connection pipe, a slot, a sealing ring, a spring, a support plate, and a baffle. The inner tube is housed inside the outer cover, and a baffle plate is located on the outer side of the middle position of the inner tube. An air passage is opened inside the baffle plate, and a sealing layer is placed above the baffle plate. The outer surface of the outer cover is coated with a high-temperature resistant coating, and an outer nozzle is opened at the top of the outer cover. An inner nozzle is opened at the top of the inner tube, and air holes are opened at the lower left and lower right corners of the inner tube. A guide pipe is connected to the lower end of the inner tube, and an oil connection pipe is installed at the right end of the guide pipe. The device is equipped with a baffle plate to block the air hole, so that the airflow direction can only be from the outside to the inside, thereby preventing oil from entering the inner cover from the air hole.

[0004] However, the above patent still has the following shortcomings: although the air hole can be blocked by the baffle and the oil will not enter the air hole, the gas can easily enter the oil pipe, which is not very practical; and it is not easy to make the oil and gas fully mix. Therefore, we have proposed an aircraft engine fuel nozzle. Utility Model Content

[0005] In view of the problems existing in the prior art, the purpose of this utility model is to provide a fuel nozzle for an aircraft engine.

[0006] To solve the above problems, the present invention adopts the following technical solution: an aero-engine fuel nozzle, comprising a housing, an externally threaded tube fixedly sleeved at the bottom of the housing, an oil guide tube fixedly connected to the top of the externally threaded tube extending into the inner cavity of the housing, a mixing shell fixedly connected to the top of the oil guide tube, an injection port provided at the top of the mixing shell extending into the top of the inner cavity of the housing, a mixing shell connected to the side of the mixing shell and the inner wall of the housing, an agitation mechanism provided on the inner wall of the mixing shell, an air guide tube fixedly sleeved on the side of the housing, one end of the air guide tube extending into the outside of the housing and fixedly sleeved with an air pipe connector, the other end of the air guide tube extending into the inner cavity of the housing and fixedly connected with an air distribution pipe, a plurality of air inlet pipes fixedly sleeved on the side of the oil guide tube, the bottom ends of the plurality of air inlet pipes respectively fixedly sleeved into the inner cavity of the air distribution pipe, a one-way oil guiding mechanism provided in the inner cavity of the oil guide tube, and a one-way air guiding mechanism provided in the inner cavity of the air inlet pipe.

[0007] As a preferred embodiment of the present invention, the stirring mechanism includes a support tube fixedly sleeved on the inner wall of the mixing shell, a support frame fixedly connected to the inner cavity of the support tube, a rotating shaft rotatably connected to the middle of the support frame via a bearing, and multiple turbine blades fixedly connected to the side of the rotating shaft.

[0008] As a preferred embodiment of the present invention, the unidirectional oil guiding mechanism includes a first lower support ring and a first upper support ring fixedly sleeved on the inner wall of the oil guiding pipe. The top of the first lower support ring is provided with a first arc-shaped groove, and the bottom surface of the first upper support ring is fixedly connected to a first spring. The bottom end of the first spring is fixedly connected to a first plug ball, and the bottom surface of the first plug ball is in contact with the inner wall of the first arc-shaped groove.

[0009] As a preferred embodiment of the present invention, the one-way air guide mechanism includes a second lower support ring and a second upper support ring fixedly sleeved on the inner wall of the air intake pipe. The top end of the second lower support ring is provided with a second arc-shaped groove, and the bottom surface of the second upper support ring is fixedly connected to a second spring. The bottom end of the second spring is fixedly connected to a second stop ball, and the bottom surface of the second stop ball is in contact with the inner wall of the second arc-shaped groove.

[0010] As a preferred embodiment of this utility model, a first slider is fixedly connected to both sides of the first ball, and the end face of the first slider is in contact with the inner wall of the oil guide pipe.

[0011] As a preferred embodiment of this utility model, a second slider is fixedly connected to both sides of the second blocking ball, and the end face of the second slider is in contact with the inner wall of the air intake pipe.

[0012] Compared with the prior art, the advantages of this utility model are: (1) In this utility model, when the oil flows in the inner cavity of the oil guide pipe, the oil pushes the first blocking ball to overcome the elastic force of the first spring and move upward, so that the oil flows smoothly in the inner cavity of the oil guide pipe. When there is no oil flow, the elastic force of the first spring drives the first blocking ball to reset and block the inner cavity of the oil guide pipe. Similarly, when the air flows in the inner cavity of the air intake pipe, the air pushes the second blocking ball to overcome the elastic force of the second spring and move upward, so that the air flows smoothly in the inner cavity of the air intake pipe. When there is no gas flow, the elastic force of the second spring drives the second blocking ball to reset and block the inner cavity of the air intake pipe, thus preventing the backflow of air and oil. In addition, the oil in the oil guide pipe and the air in the air intake pipe mix at the top of the inner cavity of the oil guide pipe and move in one direction, thus preventing the air from entering the bottom of the inner cavity of the oil guide pipe and preventing the oil from entering the inner cavity of the air intake pipe.

[0013] (2) In this utility model, by using the support pipe, support frame, rotating shaft and turbine blades together, when the oil and gas enter the inner cavity of the mixing shell, the turbine blades and rotating shaft are driven to rotate. The rotation of the turbine blades is used to stir the oil and gas, so that the oil and gas are effectively mixed. The mixed oil and gas is sprayed out from the oil nozzle, which is convenient for igniting the oil and gas. It has good practicality. Attached Figure Description

[0014] Figure 1 is a schematic diagram of the overall structure of this utility model.

[0015] Figure 2 is a schematic cross-sectional view of the present invention.

[0016] Figure 3 is a cross-sectional schematic diagram of the unidirectional oil guiding mechanism of this utility model.

[0017] Figure 4 is a cross-sectional schematic diagram of the unidirectional airflow mechanism of this utility model.

[0018] Figure 5 is a schematic diagram of the stirring mechanism of this utility model.

[0019] The following are the labels in the diagram: 1. Outer shell; 2. External threaded pipe; 3. Oil guide pipe; 4. Mixing shell; 5. Injector nozzle; 6. Agitator; 7. Air guide pipe; 8. Air distribution pipe; 9. Air inlet pipe; 10. Air pipe connector; 11. One-way oil guide mechanism; 12. One-way air guide mechanism; 13. Support pipe; 14. Support frame; 15. Rotating shaft; 16. Turbine blade; 17. First lower support ring; 18. First upper support ring; 19. First arc groove; 20. First spring; 21. First blocking ball; 22. First slider; 23. Second lower support ring; 24. Second upper support ring; 25. Second arc groove; 26. Second spring; 27. Second blocking ball; 28. Second slider. Detailed Implementation

[0020] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the scope of protection of the present utility model.

[0021] In the description of this utility model, it should be noted that the terms "upper," "lower," "inner," "outer," "top / bottom," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and 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, and therefore should not be construed as a limitation of this utility model. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0022] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," "sleeved / connected," "connected," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances. Example 1

[0023] As shown in Figures 1 to 5, an aircraft engine fuel nozzle includes a housing 1. A threaded tube 2 is fixedly sleeved at the bottom of the housing 1. The end of the threaded tube 2 is installed on a fuel supply pipe, allowing fuel to enter a guide tube 3 and a mixing shell 4 from the threaded tube 2. The top end of the threaded tube 2 extends into the inner cavity of the housing 1 and is fixedly connected to the guide tube 3. The top end of the guide tube 3 is fixedly connected to the mixing shell 4. The top end of the mixing shell 4 extends to the top of the inner cavity of the housing 1 and is provided with a fuel injection port 5. The side of the mixing shell 4 is flush with the housing 1. The inner walls of the mixing shell 4 are connected to each other. The inner wall of the mixing shell 4 is provided with an agitation mechanism 6. The side of the outer shell 1 is fixedly sleeved with a vent pipe 7. One end of the vent pipe 7 extends to the outside of the outer shell 1 and is fixedly sleeved with a pipe connector 10. The other end of the vent pipe 7 extends to the inner cavity of the outer shell 1 and is fixedly connected with a distribution pipe 8. The side of the oil guide pipe 3 is fixedly sleeved with multiple air inlets 9. The bottom ends of the multiple air inlets 9 are respectively fixedly sleeved to the inner cavity of the distribution pipe 8. The inner cavity of the oil guide pipe 3 is provided with a one-way oil guiding mechanism 11. The inner cavity of the air inlets 9 is provided with a one-way air guiding mechanism 12. The one-way oil guiding mechanism 11 includes a first lower support ring 17 and a first upper support ring 18 fixedly sleeved on the inner wall of the oil guide pipe 3. The top of the first lower support ring 17 is provided with a first arc-shaped groove 19. The bottom surface of the first upper support ring 18 is fixedly connected with a first spring 20. The bottom end of the first spring 20 is fixedly connected with a first blocking ball 21. The bottom surface of the second upper support ring 23 is in contact with the inner wall of the first arc-shaped groove 19. The one-way air guide mechanism 12 includes a second lower support ring 23 and a second upper support ring 24 fixedly sleeved on the inner wall of the air intake pipe 9. The top end of the second lower support ring 23 is provided with a second arc-shaped groove 25. The bottom surface of the second upper support ring 24 is fixedly connected with a second spring 26. The bottom end of the second spring 26 is fixedly connected with a second ball stop 27. The bottom surface of the second ball stop 27 is in contact with the inner wall of the second arc-shaped groove 25. Example 2

[0024] Based on Embodiment 1, as shown in Figures 2 and 5, the stirring mechanism 6 includes a support tube 13 fixedly sleeved on the inner wall of the mixing shell 4. A support frame 14 is fixedly connected to the inner cavity of the support tube 13. A rotating shaft 15 is rotatably connected to the middle of the support frame 14 via a bearing. Multiple turbine blades 16 are fixedly connected to the side of the rotating shaft 15. The air and oil entering the inner cavity of the mixing shell 4 drive the turbine blades 16 and the rotating shaft 15 to rotate, thereby stirring the air and oil to mix thoroughly, so that the mixed oil and gas are sprayed out from the oil injection port 5. Example 3

[0025] Based on Embodiments 1 and 2, as shown in Figures 2 to 4, a first slider 22 is fixedly connected to both sides of the first blocking ball 21. The end face of the first slider 22 is in contact with the inner wall of the oil guide pipe 3. The first blocking ball 21 is limited by the cooperation between the first slider 22 and the inner wall of the oil guide pipe 3, so that the first blocking ball 21 can only move along the axial direction of the oil guide pipe 3. A second slider 28 is fixedly connected to both sides of the second blocking ball 27. The end face of the second slider 28 is in contact with the inner wall of the air intake pipe 9. The second blocking ball 27 is limited by the cooperation between the second slider 28 and the inner wall of the air intake pipe 9, so that the second blocking ball 27 can only move along the axial direction of the air intake pipe 9.

[0026] It should be noted that this utility model is a fuel nozzle for an aircraft engine. In use, the nozzle is first installed on the fuel supply pipe via the external threaded pipe 2, while simultaneously connecting the air supply pipe to the air pipe connector 10. This allows fuel to enter the inner cavity of the fuel guide pipe 3 from the external threaded pipe 2, and air to enter the inner cavity of the intake pipe 9 from the air guide pipe 7 and the air distribution pipe 8. Then, the fuel in the inner cavity of the fuel guide pipe 3 pushes the first plug ball 21 upwards against the elastic force of the first spring 20, allowing fuel to enter the upper part of the inner cavity of the fuel guide pipe 3 from the first lower support ring 17 and the first upper support ring 18. Simultaneously, the air in the inner cavity of the intake pipe 9 pushes the second plug ball 27 upwards against the elastic force of the second spring 26, allowing air to enter the upper part of the inner cavity of the fuel guide pipe 3 from the second lower support ring 23 and the second upper support ring 24. Finally, the air and fuel mix in the upper part of the inner cavity of the fuel guide pipe 3, and the mixed fuel-air mixture enters the mixing shell 4. The oil and gas move into the inner cavity of the mixing shell 4, causing the turbine blades 16 and the shaft 15 to rotate. At the same time, the stirring of the turbine blades 16 makes the oil and gas fully mixed. Finally, the mixed oil and gas is sprayed out from the injection port 5.

[0027] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model based on the technical solution and its improved concept should be covered within the protection scope of the present utility model.

Claims

1. An aircraft engine fuel nozzle, comprising a housing (1), characterized in that: The bottom of the outer shell (1) is fixedly fitted with an external threaded tube (2). The top end of the external threaded tube (2) extends into the inner cavity of the outer shell (1) and is fixedly connected with an oil guide tube (3). The top end of the oil guide tube (3) is fixedly connected with a mixing shell (4). The top end of the mixing shell (4) extends into the top of the inner cavity of the outer shell (1) and is provided with an oil spray nozzle (5). The side of the mixing shell (4) is connected to the inner wall of the outer shell (1). The inner wall of the mixing shell (4) is provided with a stirring mechanism (6). The side of the outer shell (1) is fixedly fitted with an air guide tube. (7) One end of the air guide pipe (7) extends to the outside of the outer shell (1) and is fixedly sleeved with an air pipe connector (10). The other end of the air guide pipe (7) extends to the inner cavity of the outer shell (1) and is fixedly connected with a gas distribution pipe (8). Multiple air inlet pipes (9) are fixedly sleeved on the side of the oil guide pipe (3). The bottom ends of the multiple air inlet pipes (9) are respectively fixedly sleeved to the inner cavity of the gas distribution pipe (8). The inner cavity of the oil guide pipe (3) is provided with a one-way oil guiding mechanism (11). The inner cavity of the air inlet pipe (9) is provided with a one-way air guiding mechanism (12).

2. The aircraft engine fuel nozzle according to claim 1, characterized in that: The stirring mechanism (6) includes a support tube (13) fixedly sleeved on the inner wall of the mixing shell (4). A support frame (14) is fixedly connected to the inner cavity of the support tube (13). A rotating shaft (15) is rotatably connected to the middle part of the support frame (14) through a bearing. Multiple turbine blades (16) are fixedly connected to the side of the rotating shaft (15).

3. The fuel nozzle for an aircraft engine according to claim 1, characterized in that: The unidirectional oil guiding mechanism (11) includes a first lower support ring (17) and a first upper support ring (18) fixedly sleeved on the inner wall of the oil guiding pipe (3). The top of the first lower support ring (17) is provided with a first arc-shaped groove (19). The bottom surface of the first upper support ring (18) is fixedly connected to a first spring (20). The bottom end of the first spring (20) is fixedly connected to a first plug ball (21). The bottom surface of the first plug ball (21) is in contact with the inner wall of the first arc-shaped groove (19).

4. The aircraft engine fuel nozzle according to claim 1, characterized in that: The one-way air guide mechanism (12) includes a second lower support ring (23) and a second upper support ring (24) fixedly sleeved on the inner wall of the air inlet pipe (9). The top end of the second lower support ring (23) is provided with a second arc-shaped groove (25). The bottom surface of the second upper support ring (24) is fixedly connected to a second spring (26). The bottom end of the second spring (26) is fixedly connected to a second stop ball (27). The bottom surface of the second stop ball (27) is in contact with the inner wall of the second arc-shaped groove (25).

5. The fuel nozzle for an aircraft engine according to claim 3, characterized in that: The first ball stopper (21) is fixedly connected to the first slider (22) on both sides, and the end face of the first slider (22) is in contact with the inner wall of the oil guide pipe (3).

6. The fuel nozzle for an aircraft engine according to claim 4, characterized in that: The second block ball (27) is fixedly connected to the second slider (28) on both sides, and the end face of the second slider (28) is in contact with the inner wall of the air inlet pipe (9).

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