Oil injection system assembly for aero-engine

Abstract

The invention relates to the technical field of aero-engine oil injection control, in particular to an oil injection system assembly for an aero-engine, which comprises an annular oil supply pipe, a main oil pipe, a connecting seat, an air pressure sensor, a mounting seat, a guide pipe, an oil injection head, an aperture adjusting assembly, an oil hole shielding assembly, an end cover, a round rod, a limiting seat and a hydraulic push rod, a penetrating hole is formed in the center of the side wall of the oil spraying head, oil spraying holes distributed in an annular array mode relative to the penetrating hole are further formed in the side wall of the oil spraying head, and the hole diameter adjusting assembly is rotationally connected with the oil spraying head through the penetrating hole. When the flight height of the meteorological monitoring unmanned aerial vehicle changes, the size of the oil injection holes and the opening and closing number of the oil injection holes are sequentially and correspondingly adjusted, and the problems that the monitoring height of the meteorological monitoring unmanned aerial vehicle is frequently increased, the amount of air entering a turbine engine is reduced, and oil injection efficiency is low in the adjusting process of an oil injection pump are solved. Residual aviation kerosene in the oil injection pipe cannot be fully combusted after being sprayed out, and a small amount of aviation kerosene is attached to the combustion chamber.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine fuel injection control, in particular to a fuel injection system component for an aircraft engine. Background Art

[0002] As the scope of drone applications expands, their application scenarios are becoming more diverse. Using drones to fly at high altitudes to collect meteorological data can make up for the lack of accuracy in satellite observations. Currently, the widely used drone aviation engines mainly include aviation piston engines suitable for medium and low altitudes and jet (turbine, turbofan) engines suitable for medium and high altitudes. The working altitude of drones used in the field of meteorological monitoring needs to be flexibly adjusted at distances ranging from hundreds of meters to thousands of meters according to the monitoring needs of different meteorological conditions. Therefore, it is necessary to use turbine engines that can fly at medium and high altitudes. Compared with gasoline, aviation kerosene is safer to store and transport, has a higher combustion calorific value and stable quality, so turbine engines usually use aviation kerosene as fuel.

[0003] Drones used for meteorological observation need to fly at different altitudes to collect meteorological data at different altitudes, and have altitude differences of up to several thousand meters. When the meteorological environment in a local area is complex, the drone needs to continuously change its flight altitude in the area to comprehensively monitor and collect meteorological data in the area.

[0004] In a high-altitude environment, when the flight altitude of a UAV changes rapidly in a short period of time, the higher the flight altitude, the lower the pressure, temperature, and oxygen content of the corresponding altitude layer, resulting in a reduction in the amount of air entering the turbine engine, causing incomplete combustion of the turbine engine. In order to ensure the full combustion of the turbine engine, the injection amount needs to be reduced accordingly. Due to the rapid change in the flight altitude of the UAV, there is a surplus of aviation kerosene pumped into the pipeline by the injection pump. In the process of adjusting the appropriate injection amount by the injection pump, a part of the aviation kerosene is still sprayed out at the initial injection setting value, resulting in a small amount of aviation kerosene that cannot be fully atomized. This will not only reduce the fuel economy of the UAV used for meteorological monitoring, but also the aviation kerosene that is not fully atomized is easy to adhere to the combustion chamber of the turbine engine, resulting in a reduction in the subsequent working efficiency of the turbine engine.

[0005] To this end, a fuel injection system component for an aircraft engine is proposed. Summary of the invention

[0006] The purpose of the present invention is to provide a fuel injection system component for an aircraft engine. When the flight altitude of a meteorological monitoring UAV changes, the size of the fuel injection hole and the number of fuel injection holes opened and closed are adjusted in sequence accordingly. This solves the problem that the amount of air entering the turbine engine is reduced due to frequent increase in the monitoring altitude of the meteorological monitoring UAV, and the aviation kerosene remaining in the fuel injection pipe cannot be fully atomized during the adjustment of the fuel injection pump, and adheres to the combustion chamber after being sprayed out. The component has the effect of ensuring the atomization effect of the aviation kerosene when the altitude of the UAV changes, maintaining the fuel economy of the meteorological monitoring UAV and the subsequent working efficiency of the turbine engine.

[0007] To achieve the above object, the present invention provides the following technical solutions:

[0008] Compared with gasoline, aviation kerosene has higher kinematic viscosity, lower volatility and poor atomization performance. It is necessary to adjust the fuel injection parameters through a better-performing fuel injection system to improve the atomization quality of aviation kerosene and obtain a higher combustion rate. When the cruising altitude of the meteorological monitoring drone changes, the atmospheric environment pressure and temperature at high altitude will have a greater impact on engine performance. Since aviation kerosene needs to be assisted by air for atomization, when the cruising altitude rises, the total air intake of the turbine engine decreases, so the amount of air assisting the atomization of aviation kerosene decreases, resulting in a decrease in the atomization effect of aviation kerosene when the injection amount, the aperture and number of the injection holes remain unchanged. At this time, in order to ensure the atomization effect of aviation kerosene and enable it to be fully burned, it is necessary to first reduce the injection amount and then adjust the working power of the turbine engine. However, in the process of adjusting the injection amount, due to the presence of a certain volume of aviation kerosene in the annular fuel supply pipe and the main fuel pipe, a small amount of aviation kerosene is sucked out under the action of negative air pressure, resulting in the inability to accurately control the injection amount in a short period of time. Therefore, there will still be a small amount of aviation kerosene that is not completely atomized. Because it is not completely atomized and the oxygen content in the air decreases when the cruising altitude rises, this part of the aviation kerosene cannot be fully burned, which not only reduces the fuel economy of the meteorological monitoring UAV, but also due to the high viscosity of aviation kerosene, the unburned aviation kerosene will adhere to the combustion chamber of the turbine engine, causing the working efficiency of the turbine engine to be reduced and having an adverse effect on the working life of the turbine engine.

[0009] A fuel injection system component for an aircraft engine, comprising an annular fuel supply pipe, a main fuel pipe, a connecting seat, an air pressure sensor, a mounting seat, a conduit, a fuel injection head, and also comprising an aperture adjustment component, an oil hole shielding component, an end cover, a round rod, a limit seat and a hydraulic push rod. A perforation is provided at the center of the side wall of the fuel injection head, and the side wall of the fuel injection head is also provided with fuel injection holes distributed in a perforated annular array. The aperture adjustment component is rotatably connected to the fuel injection head through the perforation, the oil hole shielding component is rotatably installed inside the aperture adjustment component, and the end cover is installed on the oil hole shielding component. The end of the block assembly, the limit seat is installed on the inner side of the oil spray head, the hydraulic push rod is installed on the limit seat, the round rod is installed at the end of the hydraulic push rod, and the round rod is respectively limited and fitted with the aperture adjustment assembly and the oil hole shielding assembly. When the hydraulic push rod is extended to a set value, it drives the aperture adjustment assembly to rotate a set angle, and the oil hole shielding assembly remains stationary. When the hydraulic push rod continues to extend, it drives the oil hole shielding assembly to rotate a set angle, and the aperture adjustment assembly remains stationary. When the hydraulic push rod contracts, it drives the oil hole shielding assembly and the aperture adjustment assembly to reset in turn.

[0010] In the above scheme, under rated power, the injection holes on the injection head are used normally. When the cruising altitude of the meteorological monitoring UAV is frequently increased and the cruising altitude changes in a short period of time, and the circulating injection amount is not adjusted quickly due to the residual aviation kerosene in the main oil pipe and the annular fuel supply pipe, when the hydraulic push rod is extended to push the round rod to translate a single set length, the aperture adjustment component rotates first, and the aperture adjustment component is converted from a staggered distribution with the injection hole to a setting that fits the outside of the injection hole, thereby blocking the injection hole, and the diameter of the injection hole formed by the aperture adjustment component and the injection hole is reduced, the injection rate is increased, and the Sauter average diameter of the fuel spray is reduced, which improves the atomization performance of the aviation kerosene and extends the combustion cycle of the aviation kerosene, thereby allowing the aviation kerosene to be fully burned and avoiding the aviation kerosene from adhering to the combustion chamber; when the nozzle diameter value is reduced, the nozzle sprayed from a single nozzle As the flow rate of aviation kerosene increases, the jet fuel spraying distance increases. The radiation range of aviation kerosene after spraying is conical, which causes the radiation range to increase. In order to avoid overlapping and interference between adjacent oil beams, resulting in excessive local mixed gas concentration in the combustion chamber, which in turn leads to incomplete combustion, the hydraulic push rod extends and pushes the round rod to translate beyond a single set length to twice the set length. The aperture adjustment component no longer continues to rotate, and the oil hole shielding component slowly rotates through the limit cooperation with the round rod, thereby blocking half of the injection holes to varying degrees, reducing the injection range of the blocked injection holes, while the injection range of the unblocked injection holes remains unchanged, and the injection amount of the annularly distributed injection holes changes alternately, thereby fully avoiding interference between the misted aviation kerosene sprayed from adjacent injection holes, thereby ensuring that the sprayed misted aviation kerosene is fully burned, and fully improving the fuel economy of the meteorological monitoring UAV.

[0011] Preferably, the round rod is provided with an oblique groove, and the oblique groove is divided into three sections a, b, and c from back to front, the lengths of the three sections a, b, and c are consistent along the axis of the round rod, the edge of section a is point d, the connection between sections a and b is point e, and the connection between sections b and c is point f.

[0012] In the above scheme, sections a and c are arranged parallel to the axis of the round rod. When the round rod moves forward one-third of the total length of the round rod under the action of the hydraulic push rod, the contact position of the oil hole shielding assembly and the round rod changes from point d to point e, and the contact position of the aperture adjustment assembly and the round rod changes from point e to point f. When the round rod continues to extend, the oil hole shielding assembly contacts section b of the round rod and deflects, and the aperture adjustment assembly moves along section c.

[0013] Preferably, the aperture adjustment assembly includes a retaining ring, a connecting strip, a connecting rod, a first rotating cylinder, a first limit block and a limit column. The retaining ring is slidably fitted with the outer wall of the fuel injector head, the connecting strip is connected between the peripheries of multiple retaining rings, the first rotating cylinder is rotatably connected to the fuel injector head, and the first rotating cylinder passes through the fuel injector head, the connecting rod is installed between the periphery of the end of the first rotating cylinder and the periphery of the retaining ring, the first limit block is installed on the inner edge of the first rotating cylinder, and the limit column is installed on the periphery of the first rotating cylinder.

[0014] In the above scheme, the aperture adjustment assembly can be controlled to rotate to a corresponding angle through the cooperation of the first limit block and the inclined groove sections b and c. The maximum rotation angle is three hundred and sixty degrees divided by half of the number of injection holes. Taking the number of eight injection holes as an example, the maximum rotation angle of the aperture adjustment assembly is 22.5°, so that when not rotating, the retaining ring is located between adjacent injection holes.

[0015] Preferably, the oil hole shielding assembly includes a second rotating cylinder, an annular groove, a straight rod, a baffle, a threaded ring and a second limit block, the second rotating cylinder is arranged in the first rotating cylinder, the annular groove is opened on the outer periphery of the second rotating cylinder, the straight rod is installed on the outer periphery of the end of the second rotating cylinder, the baffle is installed on the end of the straight rod, the threaded ring is fixed on the end of the second rotating cylinder, and the second limit block is fitted on the inner peripheral edge of the second rotating cylinder.

[0016] In the above scheme, the oil hole shielding assembly can be controlled to rotate to a corresponding angle through the cooperation of the second limit block and the inclined groove sections a and b. Under normal circumstances, the oil hole shielding assembly does not need to be rotated to the maximum angle. It is only necessary to block a small area of ​​the staggered injection holes so that adjacent injection holes spray different amounts of misted aviation kerosene to ensure sufficient combustion. In addition, when the oil hole shielding assembly rotates, the aperture adjustment assembly has been pre-rotated to the maximum angle.

[0017] Preferably, a circular groove is constructed inside the first rotating cylinder, and the inner diameter of the circular groove is equal to the outer diameter of the second rotating cylinder, the inner diameter of the first rotating cylinder is equal to the inner diameter of the second rotating cylinder, the first limit block and the second limit block are staggered, the end of the limit column extends into the annular groove, and the end of the limit column is constructed to be hemispherical.

[0018] In the above solution, the cooperation between the limiting column and the annular groove allows the second rotating cylinder to rotate within the first rotating cylinder within a limited position, thereby preventing the second rotating cylinder from being separated from the first rotating cylinder.

[0019] Preferably, the number of the baffle rings is consistent with the number of the fuel injection holes, and the number of the fuel injection holes is set to an even number, and the number of the baffle plates is set to half of the number of the fuel injection holes.

[0020] In the above scheme, the number of the fuel injection holes is designed to be an even number, so that the number of the baffles is also an even number, and then the baffles can block the staggered fuel injection holes to a corresponding degree after rotating around the axis of the round rod, preventing the same fuel injection amount from two adjacent fuel injection holes.

[0021] Preferably, the inner circumference depth of the end cover is equal to the length of the second rotating cylinder, and the length of the first rotating cylinder is twice the length of the second rotating cylinder.

[0022] In the above scheme, the length value of the second rotating cylinder corresponds to the length value of sections a, b, and c along the axis of the round rod. Therefore, combined with the design of the circular groove, the front end of the hydraulic push rod can be accommodated inside the round rod, and the total length of the hydraulic push rod, the round rod, the first rotating cylinder, the second rotating cylinder and the end cover is controlled within a small range to avoid occupying a large space inside the injector head, thereby ensuring the smooth flow of aviation kerosene in the injector head.

[0023] Compared with the prior art, the present invention has the following beneficial effects:

[0024] 1. The present invention is applied to a meteorological monitoring UAV using a turbine engine. When the UAV frequently switches altitude, the air density and oxygen content of the corresponding altitudes are different due to different flight altitudes. The altitude change is identified by an air pressure sensor, and the angle of the rotating aperture adjustment component is correspondingly controlled by the telescopic length change of the hydraulic push rod. After the air density and oxygen content are reduced, the injection pump quickly changes the diameter of the injection hole formed by the injection hole and the aperture adjustment component during the process of adjusting the injection amount to a suitable size, thereby ensuring the atomization effect of the aviation kerosene, so that the aviation kerosene can be fully burned later, avoiding the aviation kerosene from being attached to the combustion chamber of the turbine engine without being burned out after being sprayed out, and ensuring the normal operation of the subsequent turbine engine.

[0025] 2. By setting the round rod and oil hole shielding assembly, when the diameter of the nozzle hole is reduced, the flow rate of the aviation kerosene sprayed from a single nozzle increases, the nozzle distance of the aviation kerosene increases, and the radiation range of the aviation kerosene after spraying is conical, thereby increasing the radiation range. In order to avoid overlapping and interference between adjacent oil beams, the oil hole shielding assembly slowly rotates through the limit cooperation with the round rod. After the baffle rotates, the staggered nozzle holes are shielded to varying degrees, reducing the injection range of the blocked nozzle holes, while the injection range of the unblocked nozzle holes remains unchanged, and the injection amount of the annularly distributed nozzle holes changes alternately, thereby fully avoiding interference between the misted aviation kerosene sprayed from adjacent nozzle holes, thereby ensuring that the sprayed misted aviation kerosene is fully burned, and fully improving the fuel economy of the meteorological monitoring UAV.

[0026] 3. By setting the round rod, aperture adjustment assembly and oil hole shielding assembly, when the hydraulic push rod pushes the round rod to translate, the aperture adjustment assembly is first driven to rotate. After the aperture adjustment assembly is rotated to the maximum angle, the round rod continues to translate to drive the oil hole shielding assembly to rotate. When the round rod is reset, the oil hole shielding assembly is reset before the aperture adjustment assembly. By limiting the rotation sequence of the aperture adjustment assembly and the oil hole shielding assembly, it is avoided that the oil hole shielding assembly rotates alone and causes adverse interference to the aviation kerosene atomization effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0028] Figure 2 It is a schematic diagram of the installation position between the aperture adjustment component, the oil hole shielding component and the oil injection head of the present invention;

[0029] Figure 3 It is a structural schematic diagram of the fuel injection head of the present invention;

[0030] Figure 4 It is a cross-sectional view of the oil injection head when the hydraulic push rod of the present invention is fully extended;

[0031] Figure 5 It is a structural schematic diagram of a round rod of the present invention;

[0032] Figure 6 It is a structural schematic diagram of the aperture adjustment component and the oil hole shielding component when the oil injection hole of the present invention is completely blocked;

[0033] Figure 7 It is a structural schematic diagram of the aperture adjustment assembly of the present invention;

[0034] Figure 8 It is a structural schematic diagram of the oil hole shielding assembly of the present invention;

[0035] Fig. 9 It is a cross-sectional view of the fuel injection head when the retaining ring of the present invention rotates to the outside of the fuel injection hole;

[0036] Fig.10 It is a cross-sectional view of the fuel injection head when the retaining ring of the present invention is located between adjacent fuel injection holes.

[0037] In the figure: 1. annular oil supply pipe; 2. main oil pipe; 3. connecting seat; 4. air pressure sensor; 5. mounting seat; 6. conduit; 7. oil injection head; 71. perforation; 72. oil injection hole; 8. aperture adjustment assembly; 9. oil hole shielding assembly; 10. end cover; 11. round rod; 111. inclined groove; 12. limit seat; 13. hydraulic push rod; 81. retaining ring; 82. connecting strip; 83. connecting rod; 84. first rotating cylinder; 841. circular groove; 85. first limit block; 86. limit column; 91. second rotating cylinder; 92. annular groove; 93. straight rod; 94. baffle; 95. threaded ring; 96. second limit block. DETAILED DESCRIPTION

[0038] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0039] See also Figures 1 to 10 The present invention provides an injection system component for an aircraft engine, and the technical solution is as follows:

[0040] Reference Figures 1 to 4 , a fuel injection system component for an aircraft engine, applied to a turbine engine, the combustion chamber of the turbine engine is composed of an inner and outer shells, including an annular fuel supply pipe 1, a main fuel pipe 2, a connecting seat 3, an air pressure sensor 4, a mounting seat 5, a conduit 6, and a fuel injector 7, the annular fuel supply pipe 1 is arranged on the outer side of the outer shell of the combustion chamber, the main fuel pipe 2 is connected to the annular fuel supply pipe 1, and is used to pass aviation kerosene into the annular fuel supply pipe 1, the connecting seat 3 is installed on the annular fuel supply pipe 1 in an annular array, and the interior of the connecting seat 3 is connected to the annular fuel supply pipe 1, the air pressure sensor 4 is independently installed on the unmanned aerial vehicle, the corresponding fuel injection pump connected to the main fuel pipe 2 is electrically connected to the air pressure sensor 4 through an electronic control system, the mounting seat 5 is fixed to one end of the connecting seat 3, the conduit 6 is sealed and installed with the mounting seat 5, the fuel injector 7 is installed and connected with the end of the conduit 6, and the fuel injector 7 extends between the inner and outer shells of the combustion chamber, and also includes an aperture adjustment component 8, an oil hole shielding component 9, an end cover 10, a round rod 11, a limit seat 12 and a hydraulic push rod 13, refer to Figure 3A perforation 71 is provided at the center of the side wall of the fuel injection head 7, and the side wall of the fuel injection head 7 is also provided with fuel injection holes 72 distributed in a circular array about the perforation 71; the aperture adjustment component 8 is rotatably connected to the fuel injection head 7 through the perforation 71, the aperture adjustment component 8 is rotatably sealed and connected to the perforation 71, one end of the aperture adjustment component 8 extends to the inside of the fuel injection head 7, and the other end extends to the outside of the fuel injection head 7, the oil hole shielding component 9 is rotatably installed inside the aperture adjustment component 8, the end cover 10 is installed at the end of the oil hole shielding component 9, and the end cover 10 rotates when the oil hole shielding component 9 rotates, the limit seat 12 is installed on the inside of the fuel injection head 7, the hydraulic push rod 13 is installed on the limit seat 12, the tail end of the hydraulic push rod 13 is fixedly connected to the limit seat 12, the round rod 11 is installed at the end of the hydraulic push rod 13, the front end of the hydraulic push rod 13 extends to the inside of the end of the round rod 11, and the round rod 11 is respectively limited and fitted with the aperture adjustment component 8 and the oil hole shielding component 9;

[0041] Reference Figure 4 , Fig. 9 and Fig.10 When the hydraulic push rod 13 is extended to a set value, it drives the aperture adjustment component 8 to rotate to a set angle, and the oil hole shielding component 9 remains stationary. When the aperture adjustment component 8 is rotated to a set angle, the side wall of the oil injection hole 72 fits with the aperture adjustment component 8, thereby reducing the diameter of the injection hole formed by the aperture adjustment component 8 and the oil injection hole 72, increasing the injection rate, reducing the Soter average diameter of the fuel spray, extending the combustion cycle of the aviation kerosene, improving the atomization performance of the aviation kerosene, and thus allowing the aviation kerosene to be fully burned. When the hydraulic push rod 13 continues to extend, it drives the oil hole shielding component 9 to rotate to a set angle, and the aperture adjustment component 8 remains stationary. When the diameter of the injection hole is reduced, the flow rate of the aviation kerosene sprayed from a single injection hole The speed increases, the jet fuel spraying distance increases, and the radiation range of the jet fuel after spraying is conical, thus causing the radiation range to increase. The radiation ranges of adjacent oil beams overlap and cause overlap and interference. When the hydraulic push rod 13 continues to extend, the oil hole shielding component 9 slowly rotates to a suitable angle through the limit cooperation between the round rod 11 and the oil hole shielding component 9, thereby blocking the staggered injection holes 72, reducing the injection range of the blocked injection holes, and the injection amount of the annularly distributed injection holes changes alternately, thereby avoiding the mutual interference of the misted jet fuel sprayed from adjacent injection holes. When the hydraulic push rod 13 contracts, it drives the oil hole shielding component 9 and the aperture adjustment component 8 to reset in turn. When the round rod 11 is reset, the oil hole shielding component 9 is reset before the aperture adjustment component 8.

[0042] As an embodiment of the present invention, refer to Figure 4 and Figure 5The round rod 11 is provided with an inclined groove 111, and the inclined groove 111 is divided into three sections a, b, and c from the back to the front. The lengths of the three sections a, b, and c along the axis of the round rod 11 are consistent, and the length value is L. The edge of section a is point d, the connection between sections a and b is point e, and the connection between sections b and c is point f. Sections a and c are arranged parallel to the axis of the round rod 11; refer to Fig.10 and Fig. 9 When the round rod 11 moves forward L under the action of the hydraulic push rod 13, the contact position between the oil hole shielding component 9 and the round rod 11 changes from point d to point e, and the contact position between the aperture adjustment component 8 and the round rod 11 changes from point e to point f; refer to Fig. 9 and Figure 4 When the round rod 11 translates from L to 2L, the oil hole shielding component 9 contacts the round rod 11b segment and deflects, and the aperture adjustment component 8 moves and deflects along the c segment.

[0043] As an embodiment of the present invention, refer to Figure 6 and Figure 7 The aperture adjustment assembly 8 includes a retaining ring 81, a connecting strip 82, a connecting rod 83, a first rotating cylinder 84, a first limiting block 85 and a limiting column 86. The retaining ring 81 is slidably fitted with the outer wall of the oil injection head 7. The connecting strip 82 is connected between the outer peripheries of multiple retaining rings 81. The first rotating cylinder 84 is rotatably connected to the oil injection head 7, and the first rotating cylinder 84 passes through the oil injection head 7. The connecting rod 83 is installed between the outer periphery of the end of the first rotating cylinder 84 and the outer periphery of the retaining ring 81. The first limiting block 85 is installed at the inner peripheral edge of the first rotating cylinder 84. The first limiting block 85 is the contact position between the aperture adjustment assembly 8 and the round rod 11. The limiting column 86 is installed outside the first rotating cylinder 84. When the hydraulic push rod 13 is extended by L, the first limit block 85 moves along the inclined groove 111b and c sections, and the first limit block 85 moves to point f. Taking eight injection holes 72 as an example, the maximum rotation angle of the aperture adjustment component 8 is 22.5°. At this time, the inner hole of the retaining ring 81 coincides with the outer periphery of the injection hole 72, and the diameter of the injection hole formed by the retaining ring 81 and the injection hole 72 is reduced, thereby increasing the injection rate of a single injection hole, increasing the jet fuel spray length, and extending the combustion cycle. At the same time, the Sauter average diameter of the fuel spray is reduced, thereby improving the atomization performance of the aviation kerosene, ensuring that the subsequent aviation kerosene can be fully burned.

[0044] As an embodiment of the present invention, refer to Figure 6 and Figure 8The oil hole shielding assembly 9 includes a second rotating cylinder 91, an annular groove 92, a straight rod 93, a baffle 94, a threaded ring 95 and a second stopper 96. The second rotating cylinder 91 is arranged in the first rotating cylinder 84, the annular groove 92 is opened on the outer periphery of the second rotating cylinder 91, the straight rod 93 is installed on the outer periphery of the end of the second rotating cylinder 91, the baffle 94 is installed on the end of the straight rod 93, the threaded ring 95 is fixed on the end of the second rotating cylinder 91, and the second stopper 96 is fitted on the inner peripheral edge of the second rotating cylinder 91. The second stopper 96 is the contact position between the oil hole shielding assembly 9 and the round rod 11; when the hydraulic push rod 13 is extended by L, the second stopper 96 moves along the a section, and the second The limit block 96 moves from point d to point e. When the hydraulic push rod 13 continues to extend after extending beyond L, the second limit block 96 moves along section b. The second limit block 96 moves from point e to point f. At this time, the second rotating cylinder 91, under the cooperation of the second limit block 96 and the inclined groove 111, rotates to a suitable angle in accordance with the inner circumference of the first rotating cylinder 84. The baffle 94 blocks the staggered retaining rings 81 to varying degrees, reducing the spray range of the blocked spray holes, while the spray range of the unblocked spray holes remains unchanged. The spray amounts of the annularly distributed spray holes change alternately, avoiding interference between the misted aviation kerosene sprayed from adjacent spray holes, thereby ensuring that the sprayed misted aviation kerosene is fully burned.

[0045] As an embodiment of the present invention, refer to Figure 6 A circular groove 841 is constructed inside the first rotating cylinder 84, and the inner diameter of the circular groove 841 is equal to the outer diameter of the second rotating cylinder 91. The inner diameter of the first rotating cylinder 84 is equal to the inner diameter of the second rotating cylinder 91. In the initial state, the first limit block 85 and the second limit block 96 are staggered, and the end of the limit column 86 extends into the annular groove 92. The end of the limit column 86 is flush with the outer periphery of the first rotating cylinder 84, and the end of the limit column 86 is constructed to be hemispherical; through the cooperation between the limit column 86 and the annular groove 92, the second rotating cylinder 91 is limited and rotated in the first rotating cylinder 84 without being separated from the first rotating cylinder 84.

[0046] As an embodiment of the present invention, refer to Figure 3 and Figure 6 The number of baffle rings 81 is consistent with the number of fuel injection holes 72, and the number of fuel injection holes 72 is set to an even number. In this embodiment, the number of fuel injection holes 72 is eight, and the number of baffles 94 is set to half of the number of fuel injection holes 72, that is, the number of baffles 94 is four; after the baffles 94 rotate around the axis of the round rod 11, they are distributed on the side walls of the staggered fuel injection holes 72, and then the staggered fuel injection holes 72 are blocked to the same extent, preventing the same fuel injection amount from two adjacent nozzles, and avoiding interference between the mist kerosene sprayed from the adjacent nozzles.

[0047] As an embodiment of the present invention, refer to Figure 6The inner circumference depth of the end cover 10 is equal to the length of the second rotating cylinder 91, and the length of the first rotating cylinder 84 is twice the length of the second rotating cylinder 91; the front end of the hydraulic push rod 13 extends to the inner side of the end of the round rod 11, and the hydraulic push rod 13 is located at the outer end of the round rod 11 with a smaller length, so as to avoid the hydraulic push rod 13 occupying a large space inside the injector head 7.

[0048] Working process: the annular oil supply pipe 1 is pre-installed on the outside of the outer casing of the turbine engine combustion chamber, and the oil injection head 7 is extended to the combustion chamber and the outer casing through the conduit 6. The air pressure sensor 4 monitors the cruising altitude air pressure of the meteorological monitoring UAV in real time. When the cruising altitude changes, the air pressure changes accordingly. Then, the hydraulic push rod 13 is controlled to extend and retract accordingly through the electronic control system of the UAV. When the hydraulic push rod 13 is extended, the aperture adjustment component 8 and the oil hole shielding component 9 are driven to rotate in turn. By changing the diameter value of the spray hole and shielding the staggered spray holes with different areas, the aviation kerosene combustion cycle is extended when the air pressure is reduced, and the atomization effect of the aviation kerosene is improved, so as to avoid the mutual interference of the aviation kerosene sprayed from the adjacent spray holes after the speed is increased, thereby ensuring the full combustion of the aviation kerosene after subsequent atomization;

[0049] In a stable state, the aperture adjustment component 8 and the oil hole shielding component 9 are in the following state: Fig.10 As shown;

[0050] When the UAV climbs sharply, the status of the aperture adjustment component 8 and the oil hole shielding component 9 is as follows: Fig. 9 As shown, and to Figure 4 The state transition is shown in ; when the hydraulic push rod 13 extends the axial length L of the inclined groove 111a section, the first limit block 85 in the aperture adjustment component 8 moves along the inclined groove 111b section, and the first limit block 85 is transferred from point e to point f. At this time, the rotation angle of the aperture adjustment component 8 reaches the maximum value, and the first rotating cylinder 84 rotates around the axis of the round rod 11 under the action of the first limit block 85 and the inclined groove 111 until the injection hole 72 coincides with the inner circumference of the retaining ring 81, the diameter value of the injection hole formed by the retaining ring 81 and the injection hole 72 is reduced, the injection rate in the injection hole is increased, the Sauter average diameter of the fuel spray is reduced, and the atomization performance of the aviation kerosene is improved. The second limit block 96 in the oil hole shielding component 9 moves along the inclined groove 111a section, and the second limit block 96 is transferred from point d to point e;

[0051] When the hydraulic push rod 13 continues to extend to twice L, the first limit block 85 moves along the c section, and the second limit block 96 moves along the b section. During this period, the second rotating cylinder 91 rotates a corresponding angle by the second limit block 96 and the inclined groove 111, and the baffle 94 connected to the second rotating cylinder 91 through the straight rod 93 rotates a corresponding angle. After the baffle 94 rotates, it blocks the adjacent baffle ring 81, and the staggered and spaced spray holes are blocked with the same area. The sprayed aviation kerosene sprayed from adjacent spray holes has different ranges, thereby avoiding mutual interference between the sprayed aviation kerosene sprays, thereby ensuring the subsequent full combustion of the aviation kerosene.

[0052] When the UAV lowers its cruising altitude, the air pressure increases. If the hydraulic push rod 13 is in a fully retracted state, no additional operation is required. If the hydraulic push rod 13 is not in a fully retracted state, the hydraulic push rod 13 contracts rapidly. When the hydraulic push rod 13 contracts, the first limit block 85 and the second limit block 96 cooperate with the inclined groove 111 on the round rod 11 to first drive the oil hole shielding assembly 9 to reset, and then drive the aperture adjustment assembly 8 to reset.

[0053] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A fuel injection system assembly for an aircraft engine, comprising an annular fuel supply pipe (1), a main fuel pipe (2), a connecting seat (3), an air pressure sensor (4), a mounting seat (5), a guide tube (6), and a fuel injection head (7), characterized in that: The invention also comprises an aperture adjustment component (8), an oil hole shielding component (9), an end cover (10), a round rod (11), a limit seat (12) and a hydraulic push rod (13); a through hole (71) is provided at the center of the side wall of the oil spray head (7); and the side wall of the oil spray head (7) is also provided with oil spray holes (72) distributed in a circular array with respect to the through hole (71); the aperture adjustment component (8) is rotatably connected to the oil spray head (7) through the through hole (71); the oil hole shielding component (9) is rotatably mounted inside the aperture adjustment component (8); the end cover (10) is mounted at the end of the oil hole shielding component (9); and the limit seat (12) is mounted inside the oil spray head (7). On the side, the hydraulic push rod (13) is installed on the limit seat (12), the round rod (11) is installed on the end of the hydraulic push rod (13), and the round rod (11) is respectively limited and fitted with the aperture adjustment component (8) and the oil hole shielding component (9). When the hydraulic push rod (13) is extended to a set value, it drives the aperture adjustment component (8) to rotate the set angle, and the oil hole shielding component (9) remains stationary. When the hydraulic push rod (13) continues to extend, it drives the oil hole shielding component (9) to rotate the set angle, and the aperture adjustment component (8) remains stationary. When the hydraulic push rod (13) is retracted, it drives the oil hole shielding component (9) and the aperture adjustment component (8) to reset in turn.

2. The fuel injection system component for an aircraft engine according to claim 1, characterized in that: The round rod (11) is provided with an inclined groove (111), and the inclined groove (111) is divided into three sections a, b and c from the back to the front, and the lengths of the three sections a, b and c along the axis direction of the round rod (11) are consistent.

3. The fuel injection system component for an aircraft engine according to claim 2, characterized in that: The aperture adjustment assembly (8) comprises a retaining ring (81), a connecting strip (82), a connecting rod (83), a first rotating cylinder (84), a first limiting block (85) and a limiting column (86); the retaining ring (81) is slidably fitted with the outer wall of the fuel injection head (7); the connecting strip (82) is connected between the outer peripheries of a plurality of retaining rings (81); the first rotating cylinder (84) is rotatably connected to the fuel injection head (7), and the first rotating cylinder (84) is arranged to penetrate the fuel injection head (7); the connecting rod (83) is installed between the outer periphery of the end of the first rotating cylinder (84) and the outer periphery of the retaining ring (81); the first limiting block (85) is installed on the inner peripheral edge of the first rotating cylinder (84); and the limiting column (86) is installed on the outer periphery of the first rotating cylinder (84).

4. The fuel injection system component for an aircraft engine according to claim 3, characterized in that: The oil hole shielding assembly (9) comprises a second rotating cylinder (91), an annular groove (92), a straight rod (93), a baffle (94), a threaded ring (95) and a second limit block (96); the second rotating cylinder (91) is arranged in the first rotating cylinder (84); the annular groove (92) is opened on the outer periphery of the second rotating cylinder (91); the straight rod (93) is installed on the outer periphery of the end of the second rotating cylinder (91); the baffle (94) is installed on the end of the straight rod (93); the threaded ring (95) is fixed on the end of the second rotating cylinder (91); and the second limit block (96) is installed in a close fit on the inner peripheral edge of the second rotating cylinder (91).

5. The fuel injection system component for an aircraft engine according to claim 4, characterized in that: A circular groove (841) is formed inside the first rotating cylinder (84), and the inner diameter of the circular groove (841) is equal to the outer diameter of the second rotating cylinder (91).

6. The fuel injection system component for an aircraft engine according to claim 5, characterized in that: The inner diameter value of the first rotating cylinder (84) is equal to the inner diameter value of the second rotating cylinder (91), and the first limiting block (85) and the second limiting block (96) are arranged in a staggered manner.

7. The fuel injection system component for an aircraft engine according to claim 6, characterized in that: The number of the baffle rings (81) is consistent with the number of the oil injection holes (72), and the number of the oil injection holes (72) is set to an even number, and the number of the baffle plates (94) is set to half the number of the oil injection holes (72).

8. The fuel injection system component for an aircraft engine according to claim 3, characterized in that: The end of the limiting column (86) extends into the annular groove (92), and the end of the limiting column (86) is constructed in a hemispherical shape.

9. The fuel injection system component for an aircraft engine according to claim 4, characterized in that: The inner circumference depth of the end cover (10) is equal to the length of the second rotating cylinder (91), and the length of the first rotating cylinder (84) is twice the length of the second rotating cylinder (91).

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