Structure of an aircraft turborotor engine fuel injector

Abstract

The present application relates to the technical field of engine oil injectors, and discloses an aviation rotor engine oil injector structure, which comprises a valve body, an oil injection channel is arranged in the valve body, an atomizing cavity is arranged on the inner wall of the oil injection channel, a needle valve is inserted into the oil injection channel, a sliding groove is arranged in the needle valve, a round block is slidably connected to the sliding groove, the round block is clamped to the inner wall of the oil injection channel, a fixing rod is fixedly connected to the lower end of the round block, and the combination structure of the fixing cone block and the sliding cone block is adopted, so that the sliding cone block is lowered relative to the fixing cone block at the moment when the needle valve is opened, the oil film on the surface of the sliding cone block is actively punctured by the fixing cone block, the broken residual liquid flows into the guide groove, the part of the oil flowing through the guide groove is not attached to the oil film, the carbonization of the oil film is inhibited from the source, the clogging of the injection hole is prevented, the uniform oil injection and stable atomization are ensured under long-term work, power attenuation and thermal area failure are avoided, and the aviation engine long-time high-temperature working condition is adapted.

Description

Technical Field

[0001] This invention relates to the field of engine injector technology, specifically to the structure of an aircraft rotor engine injector. Background Technology

[0002] The rotary engine injector is a core precision component of the rotary engine fuel supply system. It relies on the on / off control of the needle valve by the on / off control of the electromagnetic coil to accurately complete the timing and quantity of fuel injection. It is adapted to the working requirements of the unique crescent-shaped variable volume combustion chamber of the rotary engine. Its working principle is that the engine ECU outputs a pulse signal, the electromagnetic coil is energized to generate a suction force to open the needle valve for fuel injection, and after the power is cut off, the spring returns to the reset position to close the needle valve and cut off the fuel supply. The amount of fuel injected can be precisely adjusted by controlling the duration of the energization.

[0003] For example, an electronically controlled fuel injector with publication number CN114017221B uses a solenoid valve element to control a rack and pinion adjustment mechanism to control fuel injection, thereby improving the sensitivity of the injector control. However, after the needle valve closes at the end of the injection, the residual fuel at the nozzle easily forms a thin oil film. The high temperature in the combustion chamber causes the oil film to carbonize and coke rapidly, which accumulates and blocks the nozzle over a long period of time, resulting in uneven fuel injection, poor atomization, and power reduction. In addition, traditional nozzles are mostly simple conical hole structures, with large fuel atomization particle size, fixed spray cone angle, and concentrated spatial distribution. This makes it difficult to match the narrow and high-speed airflow field of the crescent-shaped variable volume combustion chamber of a rotary engine. Fuel tends to stick to the wall and burn incompletely, resulting in high fuel consumption and emissions. Summary of the Invention

[0004] To address the problems in the prior art, this invention provides a fuel injector structure for an aircraft rotor engine.

[0005] The technical solution adopted by this invention to solve its technical problem is: an aero-rotor engine injector structure, including a valve body, an oil injection channel is provided inside the valve body, an atomizing chamber is provided on the inner wall of the oil injection channel, a needle valve is inserted inside the oil injection channel, a sliding groove is provided inside the needle valve, a circular block is slidably connected inside the sliding groove, the circular block is engaged with the inner wall of the oil injection channel, a fixing rod is fixedly connected to the lower end of the circular block, a through hole is provided on the inner wall of the lower end of the sliding groove, the fixing rod is inserted into the through hole, and the lower end of the fixing rod... Multiple fixed cone blocks for breaking the oil film at the lower end of the needle valve are fixedly connected to the end surface. The lower surface of the oil injection channel has an inner cone surface. A cone cylinder is fixedly connected to the lower end of the valve body. Multiple clamping grooves are formed on the lower surface of the needle valve. A sliding cone block is fixedly connected to the lower end of the needle valve. Multiple guide grooves for storing the broken oil film droplets are formed on the lower surface of the sliding cone block. A threaded cylinder is fixedly connected to the upper end of the valve body. An oil injection body is threadedly connected inside the threaded cylinder. A slot is formed inside the oil injection body. The needle valve is inserted into the slot.

[0006] Specifically, the inner diameter of the oil injection channel is larger than the outer diameter of the needle valve, and the lower end surface of the needle valve matches the inner wall of the cone.

[0007] Specifically, the fixed cone block is engaged inside the guide groove, and the fixed cone block and the sliding cone block have a conical structure when they coincide.

[0008] Specifically, the oil injection assembly includes an oil injection hole located inside the oil injector body. A clamping hole is formed on the inner wall of the oil injection hole. An oil injection connector is fixedly connected to the surface of the oil injector body, and the oil injection connector corresponds to the clamping hole. An oil return hole is formed inside the oil injector body. A connecting hole communicating with a slot is formed on the inner wall of the oil return hole. An oil return cavity is formed on the upper inner wall of the oil return hole, and an oil return connector is embedded inside the oil return cavity.

[0009] Specifically, the control component includes a fixed box, which is fixedly sleeved on the surface of the valve body. An electromagnetic coil is fixedly connected inside the fixed box. A circular cavity is opened on the upper surface of the valve body. A spring is snapped into the inside of the circular cavity. An armature is snapped into the bottom of the circular cavity. The armature is fixedly connected to the surface of the needle valve.

[0010] Specifically, the electromagnetic coil corresponds to the spring, and the electromagnetic coil is located at the upper end of the armature.

[0011] Specifically, both the oil injection hole and the oil return hole are located at the lower end of the fuel injector body, and both the oil injection hole and the oil return hole are connected to the circular cavity.

[0012] The beneficial effects of this invention are: (1) The aero-rotor engine injector structure described in this invention uses a combination of a fixed cone and a sliding cone. When the needle valve is opened, the sliding cone moves downward relative to the fixed cone. The fixed cone actively punctures the oil film on the surface of the sliding cone, and the broken residual liquid flows into the guide groove, so that the part through which the oil flows will not be attached to the oil film. This inhibits oil film carbonization from the source, prevents nozzle blockage, ensures uniform oil injection and stable atomization under long-term operation, avoids power attenuation and hot zone failure, and is suitable for long-term high-temperature operating conditions of aero-engines.

[0013] (2) The fuel injector structure of the aircraft rotor engine described in this invention forms a cone-shaped nozzle through a fixed cone block and a sliding cone block. The fuel enters the multi-stage atomization chamber through the fuel injection channel to complete the initial high-speed atomization, and then accelerates atomization again through the inner cone surface, the gap between the cone and the sliding cone block. Combined with the circumferential clamping groove, it forms a multi-cone angle and multi-directional divergent spray. The atomized particle size is smaller, the distribution is more uniform, and the coverage is wider. It is more compatible with the airflow field of the crescent-shaped combustion chamber of the rotor engine, which significantly improves combustion efficiency, reduces fuel consumption and emissions, and enhances power output. Attached Figure Description

[0014] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0015] Figure 1 A schematic diagram of the closed-state structure of the fuel injector for an aircraft rotary engine provided by the present invention; Figure 2 A cross-sectional structural diagram of the fuel injector structure for an aircraft rotary engine provided by the present invention; Figure 3 A schematic diagram of the needle valve structure for the fuel injector structure of an aircraft rotor engine provided by the present invention; Figure 4 A schematic diagram of the needle valve cross-sectional structure of the fuel injector for an aircraft rotor engine provided by the present invention. Figure 5 A schematic diagram of the fixed cone block structure of the fuel injector structure for an aircraft rotor engine provided by the present invention; Figure 6 The present invention provides an aero-rotor engine injector structure. Figure 2 Enlarged view of section A in the middle; Figure 7 The present invention provides an aero-rotor engine injector structure. Figure 4 Enlarged view of section B; Figure 8 This is a schematic diagram of the injection state portion of the fuel injector structure for an aircraft rotor engine provided by the present invention.

[0016] In the diagram: 1. Valve body; 2. Oil injection channel; 3. Atomizing chamber; 4. Needle valve; 5. Slide groove; 6. Circular block; 7. Fixing rod; 8. Through hole; 9. Fixing cone block; 10. Inner cone surface; 11. Conical cylinder; 12. Clamping groove; 13. Sliding cone block; 14. Guide groove; 15. Threaded cylinder; 16. Oil injector; 17. Slot; 18. Oil injection assembly; 181. Oil injection hole; 182. Clamping hole; 183. Oil injection connector; 184. Oil return hole; 185. Connecting hole; 186. Oil return chamber; 187. Oil return connector; 19. Control assembly; 191. Fixing box; 192. Electromagnetic coil; 193. Circular cavity; 194. Spring; 195. Armature. Detailed Implementation

[0017] To make the technical means, creative features, objectives and effects of this invention easier to understand, the invention will be further described below in conjunction with specific embodiments.

[0018] Please see Figures 1 to 8 The present invention provides the following technical solutions: Example 1: An aero-rotor engine injector structure includes a valve body 1. An axially oriented oil injection channel 2 is provided inside the valve body 1. A multi-stage atomizing chamber 3 is circumferentially formed in the middle section of the inner wall of the oil injection channel 2. An axially sliding needle valve 4 is coaxially arranged inside the oil injection channel 2. A through-groove 5 is axially formed inside the needle valve 4. A circular block 6 is slidably assembled within the groove 5. The outer edge of the circular block 6 is engaged with the inner wall of the oil injection channel 2 and remains stationary. A fixing rod 7 is coaxially fixed to the lower end of the circular block 6. A coaxial through hole 8 is formed in the lower end wall of the groove 5. The lower end of the fixing rod 7 extends through the through hole 8 to the outside of the bottom end of the needle valve 4. The lower end of the fixing rod 7 is circumferentially... Four radially extending fixed cone blocks 9 are uniformly fixed. The inner wall of the lower end of the oil injection channel 2 is machined with a converging inner cone surface 10. The lower end of the valve body 1 is coaxially fixed with a conical nozzle cone cylinder 11. The lower end of the needle valve 4 has four axially extending clamping grooves 12 on its outer wall. The bottom end of the needle valve 4 is coaxially fixed with a hollow conical sliding cone block 13. The lower surface of the sliding cone block 13 has four guide grooves 14 on its lower surface. The upper end of the valve body 1 is coaxially fixed with an external threaded cylinder 15. The threaded cylinder 15 is internally connected with a detachable oil injection body 16. The lower end of the oil injection body 16 has a slot 17. The upper end of the needle valve 4 is coaxially inserted into the slot 17 and can slide axially.

[0019] The inner diameter of the oil injection channel 2 is larger than the outer diameter of the needle valve 4, forming an annular fuel gap. The lower outer conical surface of the needle valve 4 is in high-precision fit and seal with the inner wall of the cone cylinder 11. The fixed cone block 9 is embedded in the guide groove 14 in a one-to-one correspondence. When the fixed cone block 9 and the sliding cone surface 13 are closed, they are coplanar to form a complete conical surface. When opened, they move downwards relative to each other to expose the ruptured membrane.

[0020] The fuel injector 16 integrates a fuel injection assembly 18 and a fuel return assembly. The fuel injection assembly 18 includes a fuel injection hole 181, a clamping hole 182, and a fuel injection connector 183. The fuel return assembly includes a fuel return hole 184, a connecting hole 185, a fuel return chamber 186, and a fuel return connector 187. The valve body 1 externally integrates a control assembly 19, which includes a fixing box 191, an electromagnetic coil 192, a circular cavity 193, a spring 194, and an armature 195. The electromagnetic coil 192 is located directly above the armature 195. The lower ends of the fuel injection hole 181 and the fuel return hole 184 are connected to the circular cavity 193, forming a closed-loop oil circuit.

[0021] During operation, when the engine is running normally, high-pressure fuel is delivered to the fuel injector 183 via the fuel supply line, enters the fuel injector 181 inside the fuel injector body 16 through the clamping hole 182, then flows into the circular cavity 193 at the upper end of the valve body 1, and then flows downward along the annular gap between the fuel injection channel 2 and the needle valve 4, completing the fuel supply preparation. When the engine ECU sends a fuel injection pulse signal, the solenoid coil 192 is instantly energized and generates a strong electromagnetic attraction. The electromagnetic force overcomes the preload of the return spring 194, pulling the armature 195 to move upward rapidly. Since the armature 195 is rigidly connected to the needle valve 4, the needle valve 4 slides upward axially in sync, causing the lower outer conical surface of the needle valve 4 to separate from the inner wall of the cone cylinder 11, and the fuel injector... When the injection is activated, fuel, under the influence of pressure difference, enters the multi-stage atomization chamber 3 at high speed from the injection channel 2. It undergoes repeated impact, shearing, and acceleration against the inner wall of the chamber, completing the initial atomization. Subsequently, the fuel flows through the inner cone surface 10, where the cross-section contracts sharply, further increasing the flow velocity. It is then ejected at high speed through the annular slit between the inner wall of the cone 11 and the outer wall of the sliding cone block 13, achieving secondary fine atomization. Simultaneously, as the high-speed fuel flows through the groove 12 on the lower outer wall of the needle valve 4, the airflow is compressed into a multi-directional, cone-shaped spray. This results in uniform atomized particle size and a wide distribution range, effectively covering the high-speed airflow field of the rotary engine's crescent-shaped combustion chamber, ensuring rapid and uniform mixing of fuel and air. During injection, excess high-pressure fuel in the fuel line is discharged... The fuel flows through slot 17 and connecting hole 185 into return oil hole 184, and then through return oil chamber 186 and return oil connector 187 back to fuel tank or low-pressure oil circuit, forming a stable closed-loop cycle of fuel supply-injection-return. This effectively buffers fuel supply pressure fluctuations, maintains constant injection pressure, and ensures that the fuel injection quantity, atomization quality, and spray pattern are highly consistent with each injection, meeting the high-frequency, high-speed, and high-precision fuel injection control requirements of aero-rotor engines. When the ECU fuel injection pulse ends, the electromagnetic coil 192 is de-energized, the electromagnetic attraction disappears, and the return spring 194, under the preload, quickly pushes the armature 195 and needle valve 4 downwards to reset, so that the lower outer conical surface of the needle valve 4 is tightly fitted again against the inner wall of the cone cylinder 11, and the fuel injection port... The valve quickly shuts off the fuel injection, at which point the fixed cone 9 moves out of the sliding cone 13. As the needle valve 4 slides downward, the round block 6 remains stationary in the positioning groove on the inner wall of the fuel injection channel 2. The fixed rod 7 and the lower fixed cone 9 remain in their original positions. Meanwhile, the needle valve 4 drives the sliding cone 13 to move downward, exposing the fixed cone 9 relative to the sliding cone 13. This instantly punctures the thin oil film remaining on the surface of the sliding cone 13 during the needle valve closing phase. After the oil film is punctured evenly at multiple points, it forms tiny oil droplets that flow into the guide groove 14 along the surface of the sliding cone 13. This prevents residual oil from remaining on the fuel injection path, fundamentally avoiding high-temperature carbonization and coking of the oil film that could clog the nozzle.

[0022] Example 2: The technical solution of this example that differs from Example 1 includes: the number of fixed cone blocks 9 is set to 6 and evenly distributed along the circumference, the guide grooves 14 correspond to 6, the cone angle of the fixed cone block 9 is set to 45°, and the cutting edge is sharpened; the cone angle of the sliding cone block 13 is set to 60°, and the guide grooves 14 are deepened and widened.

[0023] When in use, the fixed cone blocks break the film simultaneously at 6 points, providing more comprehensive coverage and more thorough removal of the high-temperature oil film, further reducing the risk of carbon buildup. It is suitable for high-power, long-term high-temperature aero-rotor engine operating conditions, resulting in higher reliability.

[0024] Example 3: The technical solution that differs from Example 2 in this example includes: the atomizing chamber 3 is set as a three-stage stepped expansion structure to accelerate the crushing step by step, the cone angle of the inner cone surface 10 is set to 45°, the number of clamping grooves 12 is set to 6 and the cross-section is arc-shaped, and the spray cone angle and distribution are optimized.

[0025] When in use, the three-stage atomization makes the fuel particles smaller and more uniform, and the multi-arc grooves form a wide cone angle and evenly distributed spray, resulting in more complete combustion and lower emissions, making it suitable for aircraft rotary engines.

Claims

1. An injector structure for an aircraft rotary engine, comprising a valve body (1), characterized in that: The valve body (1) has an oil injection channel (2) inside, and an atomizing chamber (3) is provided on the inner wall of the oil injection channel (2). A needle valve (4) is inserted into the oil injection channel (2). A sliding groove (5) is provided inside the needle valve (4). A round block (6) is slidably connected inside the sliding groove (5). The round block (6) is snapped onto the inner wall of the oil injection channel (2). A fixing rod (7) is fixedly connected to the lower end of the round block (6). A through hole (8) is provided on the inner wall of the lower end of the sliding groove (5). The fixing rod (7) is inserted into the through hole (8). Multiple fixing cones (9) for breaking the oil film at the lower end of the needle valve (4) are fixedly connected to the lower surface of the fixing rod (7). An inner cone surface (10) is provided on the lower surface of the oil injection channel (2). (1) The lower end of the valve body (1) is fixedly connected to a cone (11), the lower surface of the needle valve (4) is provided with multiple clamping grooves (12), the lower end of the needle valve (4) is fixedly connected to a sliding cone (13), the lower surface of the sliding cone (13) is provided with multiple guide grooves (14) for storing broken oil film droplets, the upper end of the valve body (1) is fixedly connected to a threaded cylinder (15), the inside of the threaded cylinder (15) is threadedly connected to an oil injection body (16), the inside of the oil injection body (16) is provided with a slot (17), the needle valve (4) is inserted into the slot (17), the oil injection body (16) is provided with an oil injection component (18) for injecting oil into the valve body (1), and the valve body (1) is provided with a control component (19) for controlling the opening and closing of the needle valve (4). The control component (19) includes a fixed box (191), which is fixedly sleeved on the surface of the valve body (1). An electromagnetic coil (192) is fixedly connected inside the fixed box (191). A circular cavity (193) is opened on the upper surface of the valve body (1). A spring (194) is snapped inside the circular cavity (193). An armature (195) is snapped at the bottom of the circular cavity (193). The armature (195) is fixedly connected to the surface of the needle valve (4).

2. The fuel injector structure for an aircraft rotary engine according to claim 1, characterized in that: The inner diameter of the oil injection channel (2) is larger than the outer diameter of the needle valve (4), and the lower end surface of the needle valve (4) matches the inner wall of the cone (11).

3. The fuel injector structure for an aircraft rotary engine according to claim 1, characterized in that: The fixed cone block (9) is engaged inside the guide groove (14), and the fixed cone block (9) and the sliding cone block (13) are conical when they coincide.

4. The fuel injector structure for an aircraft rotary engine according to claim 1, characterized in that: The oil injection assembly (18) includes an oil injection hole (181), which is located inside the oil injection body (16). A clamping hole (182) is provided on the inner wall of the oil injection hole (181). An oil injection connector (183) is fixedly connected to the surface of the oil injection body (16). The oil injection connector (183) corresponds to the clamping hole (182). An oil return hole (184) is provided inside the oil injection body (16). A connecting hole (185) communicating with the slot (17) is provided on the inner wall of the oil return hole (184). An oil return cavity (186) is provided on the upper inner wall of the oil return hole (184). An oil return connector (187) is embedded inside the oil return cavity (186).

5. The fuel injector structure for an aircraft rotary engine according to claim 1, characterized in that: The electromagnetic coil (192) corresponds to the spring (194), and the electromagnetic coil (192) is located at the upper end of the armature (195).

6. The fuel injector structure for an aircraft rotary engine according to claim 4, characterized in that: The oil injection hole (181) and the oil return hole (184) are both located at the lower end of the oil injector (16), and the oil injection hole (181) and the oil return hole (184) are both connected to the circular cavity (193).

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