A pressure-reducing oxygen supplement device for high-altitude rapid starting of a turbojet engine and a use method thereof

Abstract

The present application relates to turbojet engine oxygen supplement technical field, particularly to a kind of decompression oxygen supplement device for turbojet engine high-altitude rapid start and use method, including bottle body, the top of bottle body is equipped with the pressure reducing valve for adjusting pressure, the bottom of bottle body is equipped with the base for filling bottle body with air;Pressure reducing valve includes with bottle body fixed connection gas cylinder upper cover, gas cylinder upper cover is communicated with pusher and exhaust nozzle, gas cylinder upper cover is installed with pressure regulating assembly at the end away from bottle body.The present application is equipped with pressure regulating assembly in pressure reducing valve, can effectively supplement oxygen to engine when starting at high altitude, avoid air thin, make fuel burn rapidly, solve high-altitude starting problem, reduce starting time simultaneously;The present application is integrated with pressure reducing valve on bottle body, can effectively reduce the weight and volume of bottle body under the condition of increasing volume.

Description

Technical Field

[0001] This invention relates to the field of oxygen replenishment technology for turbojet engines, and in particular to a decompression and oxygen replenishment device for rapid high-altitude start-up of turbojet engines and its usage method. Background Technology

[0002] The working process of a turbojet core engine is as follows: First, the compressor impeller at the front of the turbojet core engine compresses the air, which is then further decelerated and diffused by the diffuser, resulting in an increase in both the total temperature and total pressure of the compressed air. Subsequently, the air enters the combustion chamber and mixes with atomized fuel to form a combustible fuel-air mixture. The mixture is ignited by a spark plug or glow plug installed in the combustion chamber, extracting chemical energy from the fuel through combustion. The gas temperature rises sharply, forming a high-temperature, high-pressure gas. The high-temperature, high-pressure gas drives the turbine to rotate, and the turbine expands and does work, driving the compressor to rotate, forming the entire heat engine cycle. The gas flowing through the turbine expands again through the nozzle to do work, generating thrust.

[0003] However, the requirements for rapid high-altitude start-up, compact structure, and lightweight design of small fixed-wing aircraft conflict with the large size, heavy weight, and inability to depressurize and throttle conventional oxygen cylinders (which have high costs for pyrotechnic starters and igniters).

[0004] As the preferred power source for small aircraft, the ability of turbojet engines to start at high altitudes directly affects the aircraft's envelope and performance. Engines that cannot start quickly at high altitudes cannot meet the requirements for special applications.

[0005] Currently, the conventional solution on the market is to use a built-in pyrotechnic igniter and pyrotechnic starter to solve the problem of starting at high altitudes. Pyrotechnic solutions have large and heavy engines, and the pyrotechnic components are disposable materials, resulting in high costs and significant safety risks.

[0006] Existing turbojet engine oxygen supply devices operate at high pressures (20 MPa), so they are mostly made of stainless steel. However, this material has low strength and high density. With the same wall thickness, it cannot withstand high pressure (due to insufficient oxygen filling). Increasing the oxygen mass can only be achieved by increasing the volume or wall thickness, which results in a heavy oxygen supply device.

[0007] It is evident that existing oxygen replenishment devices are too bulky to meet the requirements of compact structures for special aircraft, and too heavy to meet the requirements of lightweight design for special aircraft.

[0008] Therefore, there is an urgent need for a decompression and oxygen supply device and its usage method for rapid high-altitude starting of turbojet engines. This device can effectively supplement oxygen to the engine during high-altitude starting, avoid the problem of thin air, and enable rapid combustion of fuel, thereby solving the high-altitude starting problem and reducing the starting time. Summary of the Invention

[0009] The purpose of this invention is to provide a decompression and oxygen replenishment device and its usage method for rapid high-altitude start-up of turbojet engines, in order to solve the problems existing in the prior art.

[0010] To achieve the above objectives, the present invention provides the following solution: a pressure-reducing and oxygen-supplementing device for high-altitude rapid start-up of a turbojet engine, comprising a cylinder body, wherein a pressure-reducing valve for adjusting pressure is installed on the top of the cylinder body, and a base for inflating the cylinder body is installed on the bottom of the cylinder body; the pressure-reducing valve includes a cylinder cap fixedly connected to the cylinder body, wherein a pusher and an exhaust nozzle are connected to the cylinder cap, and a pressure regulating component is installed at the end of the cylinder cap away from the cylinder body.

[0011] Preferably, the pressure regulating component includes a diaphragm base installed on the end of the gas cylinder cover away from the cylinder body, and a diaphragm cap installed on the end of the diaphragm base away from the gas cylinder cover, and a diaphragm compartment is formed inside the diaphragm cap.

[0012] Preferably, the diaphragm compartment is connected to a throat tube through a first through hole, the first through hole being formed on the diaphragm base, and the throat tube being installed inside the gas cylinder cover.

[0013] Preferably, the end of the throat tube with the larger diameter is connected to an air inlet pipe, and the end of the air inlet pipe extending outside the top cover of the gas cylinder is connected to the cylinder body.

[0014] Preferably, the end of the throat tube with a smaller diameter is connected to an air outlet tube, and the end of the air outlet tube extending outside the top cover of the gas cylinder is connected to an exhaust nozzle.

[0015] Preferably, a connecting pipe is fixedly connected to and communicates with the air outlet pipe, and the connecting pipe is connected to the diaphragm chamber through a second through hole, which is formed on the diaphragm base.

[0016] Preferably, a diaphragm is installed at one end of the diaphragm cover facing the diaphragm base, and a second pressure adjusting spring is fixedly connected to the end of the diaphragm away from the diaphragm base. The end of the second pressure adjusting spring away from the diaphragm is fixedly connected to the top inside the diaphragm cover.

[0017] Preferably, a connecting rod is fixedly connected to one end of the diaphragm facing the diaphragm base, and a throttling ball is fixedly connected to the end of the connecting rod that extends through the first through hole into the end of the throat with a larger diameter. A first pressure adjusting spring is fixedly connected to the end of the throttling ball that is away from the connecting rod, and the end of the first pressure adjusting spring that is away from the throttling ball is fixedly connected to the end of the throat.

[0018] Preferably, an inflation check valve is installed at the center of the end of the base away from the bottle body, and the inflation check valve is connected to the bottle body.

[0019] A method for rapid high-altitude start-up of a turbojet engine using decompression and oxygen replenishment includes the following steps:

[0020] S1. The pusher operates when the engine needs additional oxygen;

[0021] S2. Then, the voltage regulating component operates;

[0022] S3. The gas inside the bottle is ejected through the exhaust port.

[0023] The present invention discloses the following technical effects:

[0024] This invention, through a pressure regulating component installed in the pressure reducing valve, can effectively supplement oxygen to the engine during high-altitude starting, avoiding thin air and enabling rapid fuel combustion, thus solving the high-altitude starting problem and reducing starting time.

[0025] This invention integrates a pressure-reducing valve into the bottle body, which can effectively reduce the weight and volume of the bottle while increasing its capacity. Attached Figure Description

[0026] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

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

[0028] Figure 2 This is a schematic cross-sectional view of the pressure reducing valve of the present invention;

[0029] Figure 3 This is a schematic diagram of the gas flow structure inside the pressure reducing valve of the present invention;

[0030] The components are as follows: 1. Pressure reducing valve; 2. Bottle body; 3. Promoter; 4. Base; 5. Inflation check valve; 6. Exhaust nozzle; 10. First pressure regulating spring; 11. Gas cylinder cap; 12. Diaphragm base; 13. Diaphragm compartment; 14. Diaphragm; 15. Diaphragm cap; 16. Second pressure regulating spring; 17. Connecting rod; 18. Throat tube; 19. Throttle ball; 20. Inlet pipe; 21. Outlet pipe. Detailed Implementation

[0031] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0032] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0033] Reference Figures 1-3 This invention provides a pressure-reducing and oxygen-supplementing device for high-altitude rapid start-up of a turbojet engine, comprising a cylinder body 2, a pressure-reducing valve 1 for adjusting pressure installed on the top of the cylinder body 2, and a base 4 for inflating the cylinder body 2 installed on the bottom of the cylinder body 2; the pressure-reducing valve 1 includes a cylinder cover 11 fixedly connected to the cylinder body 2, a pusher 3 and an exhaust nozzle 6 connected to the cylinder cover 11, and a pressure regulating component installed at the end of the cylinder cover 11 away from the cylinder body 2.

[0034] This invention, through a pressure regulating component installed in the pressure reducing valve 1, can effectively supplement oxygen to the engine during high-altitude starting, avoid thin air, and enable rapid fuel combustion, thus solving the high-altitude starting problem and reducing starting time.

[0035] By integrating a pressure reducing valve 1 onto the bottle body 2, this invention can effectively reduce the weight and volume of the bottle body 2 while increasing its capacity.

[0036] Further optimization of the design includes a pressure regulating assembly comprising a diaphragm base 12 installed on the end of the gas cylinder cover 11 away from the cylinder body 2, and a diaphragm cap 15 installed on the end of the diaphragm base 12 away from the gas cylinder cover 11, with a diaphragm compartment 13 inside the diaphragm cap 15. This allows the pressure regulating assembly to be effectively installed inside the pressure reducing valve 1.

[0037] In a further optimized design, the diaphragm compartment 13 is connected to a throat tube 18 via a first through-hole. The first through-hole is located on the diaphragm base 12, and the throat tube 18 is installed inside the gas cylinder cover 11. The first through-hole allows the throat tube 18 to communicate with the diaphragm compartment 13.

[0038] In a further optimized design, the larger diameter end of the throat tube 18 is connected to an air inlet pipe 20, and the end of the air inlet pipe 20 extending outside the gas cylinder cap 11 is connected to the cylinder body 2. The air inlet pipe 20 allows gas from the cylinder body 2 to enter the throat tube 18.

[0039] In a further optimized design, the smaller diameter end of the throat tube 18 is connected to an outlet tube 21, and the end of the outlet tube 21 extending outside the gas cylinder cap 11 is connected to an exhaust nozzle 6. Gas enters the outlet tube 21 through the throat tube 18, and then the gas is ejected from the exhaust nozzle 6 through the outlet tube 21.

[0040] In order to ensure that the ejected gas can be effectively sprayed into the engine, the exhaust nozzle 6 is connected to the engine through a Teflon hose, which can effectively reduce the overall weight.

[0041] The pusher 3 is connected to the end of the exhaust pipe 21 near the exhaust nozzle 6 via a seal. The pusher 3 can open and close the pipeline between the exhaust pipe 21 and the exhaust nozzle 6.

[0042] The seal is used to control the opening and closing of the vent pipe 21.

[0043] When the engine does not require oxygen replenishment, the turbojet controller sends a command to the pusher 3, which controls the seal to block the exhaust pipe 21, thus disconnecting the pipeline between the exhaust pipe 21 and the exhaust nozzle 6.

[0044] When the engine needs to replenish oxygen, the turbojet controller sends a command to the pusher 3, which controls the seal to operate. The seal does not block the exhaust pipe 21, so that the pipeline between the exhaust pipe 21 and the exhaust nozzle 6 is connected, allowing gas to be ejected from the exhaust nozzle 6 through the exhaust pipe 21.

[0045] The design is further optimized by fixing a connecting pipe to the vent pipe 21. The connecting pipe is connected to the diaphragm chamber 13 through a second through hole, which is located on the diaphragm base 12. The vent pipe 21 is connected to the diaphragm chamber 13 through the second through hole.

[0046] In a further optimized design, a diaphragm 14 is mounted on the end of the diaphragm cover 15 facing the diaphragm base 12. A second pressure regulating spring 16 is fixedly connected to the end of the diaphragm 14 away from the diaphragm base 12. The end of the second pressure regulating spring 16 away from the diaphragm 14 is fixedly connected to the top inside the diaphragm cover 15. When the pressure on the diaphragm 14 is greater than the contraction pressure of the second pressure regulating spring 16, the second pressure regulating spring 16 is compressed, connecting the first through hole and the second through hole.

[0047] In a further optimized design, a connecting rod 17 is fixedly connected to one end of the diaphragm 14 facing the diaphragm base 12, and a throttling ball 19 is fixedly connected to the end of the connecting rod 17 that extends through the first through hole into the larger diameter end of the throat tube 18.

[0048] By contracting the second pressure regulating spring 16, the diaphragm 14 drives the connecting rod 17 to move, and the connecting rod 17 drives the throttle ball 19 to move. When the throttle ball 19 moves to the junction of the larger diameter end and the smaller diameter end of the throat tube 18, the throttle ball 19 disconnects the flow of gas in the throat tube 18 to the first through hole and the outlet pipe 21. Through the cooperation of the throttle ball 19 and the throat tube 18, the pressure regulating function is realized.

[0049] In a further optimized design, a first pressure regulating spring 10 is fixedly connected to the end of the throttle ball 19 away from the connecting rod 17, and the end of the first pressure regulating spring 10 away from the throttle ball 19 is fixedly connected to the end of the throat tube 18.

[0050] When the throttle ball 19 seals the throat 18, the second pressure regulating spring 16 releases its elasticity, causing the diaphragm 14 to move towards the diaphragm base 12. The diaphragm 14 drives the connecting rod 17 to move, and the connecting rod 17 drives the throttle ball 19 to move. At this time, the throttle ball 19 does not seal the throat 18, allowing the gas to be effectively ejected through the outlet pipe 21.

[0051] In a further optimized design, an inflation check valve 5 is installed at the center of the end of the base 4 furthest from the bottle body 2, and the inflation check valve 5 is connected to the bottle body 2. The inflation check valve 5 facilitates inflation of the bottle body 2.

[0052] A method for rapid high-altitude start-up of a turbojet engine using decompression and oxygen replenishment includes the following steps:

[0053] S1. When the engine needs to replenish oxygen, the pusher 3 works, connecting the exhaust pipe 21 and the exhaust nozzle 6.

[0054] S2. Then, the pressure regulating component operates; the gas in the bottle 2 enters the throat 18 from the inlet pipe 20. Part of the gas in the throat 18 flows into the outlet pipe 21, and the other part enters the diaphragm chamber 13 through the first through hole. The gas in the diaphragm chamber 13 pushes the diaphragm 14 to squeeze the second pressure regulating spring 16. The diaphragm 14 deforms and moves upward, allowing the gas in the diaphragm chamber 13 to enter the outlet pipe 21 through the second through hole. At the same time, the diaphragm 14 pulls the throttle ball 19 upward through the connecting rod 17. When the gas pressure in the throat 18 is much greater than the pressure of the second pressure regulating spring 16, the throttle ball 19 cooperates with the throat 18 to seal the throat 18. At this time, the diaphragm 14 moves downward under the action of the second pressure regulating spring 16, so that the throttle ball 19 no longer seals the throat 18, and the flow channel in the throat 18 reopens. The pressure regulating function is achieved through the extremely high frequency reciprocating cycle of the throttle ball 19.

[0055] S3. The gas in the bottle 2 is ejected through the exhaust nozzle 6; the gas in the diaphragm chamber 13 enters the exhaust pipe 21 through the second through hole and part of the gas in the throat 18 flows into the exhaust pipe 21, so that the gas in the exhaust pipe 21 enters the exhaust nozzle 6, and the gas in the exhaust nozzle 6 is injected into the engine through the Teflon hose.

[0056] When the gas in bottle 2 is insufficient, the gas in bottle 2 can be filled by the one-way valve 5.

[0057] Working process: When the engine needs oxygen replenishment, the turbojet controller sends a command to the pusher 3, which activates the pusher 3 to connect the outlet pipe 21 and the exhaust nozzle 6. At this time, the gas in the cylinder 2 enters the throat pipe 18 from the intake pipe 20. Part of the gas in the throat pipe 18 flows into the outlet pipe 21, and the other part enters the diaphragm chamber 13 through the first through hole. The gas in the diaphragm chamber 13 pushes the diaphragm 14 to squeeze the second pressure regulating spring 16, causing the diaphragm 14 to deform upwards, allowing the gas in the diaphragm chamber 13 to pass through the second pressure regulating spring 16. The gas enters the outlet pipe 21 through the through hole. At the same time, the diaphragm 14 pulls the throttle ball 19 upward through the connecting rod 17. When the gas pressure in the throat 18 is much greater than the pressure of the second pressure regulating spring 16, the throttle ball 19 cooperates with the throat 18 to seal the throat 18. At this time, the diaphragm 14 moves downward under the action of the second pressure regulating spring 16, so that the throttle ball 19 no longer seals the throat 18, and the flow channel in the throat 18 reopens. Through the extremely high frequency reciprocating cycle of the throttle ball 19, the pressure regulating function is achieved.

[0058] In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and are not intended to 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 invention.

[0059] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A decompression and oxygen replenishment device for rapid high-altitude start-up of a turbojet engine, characterized in that: Includes a bottle body (2), the top of which is equipped with a pressure reducing valve (1) for adjusting pressure, and the bottom of which is equipped with a base (4) for inflating the bottle body (2). The pressure reducing valve (1) includes a gas cylinder cover (11) fixedly connected to the cylinder body (2), and a pusher (3) and an exhaust nozzle (6) are connected to the gas cylinder cover (11). A pressure regulating component is installed at the end of the gas cylinder cover (11) away from the cylinder body (2). The pressure regulating assembly includes a diaphragm base (12) installed on the gas cylinder top cover (11) at the end away from the cylinder body (2). A diaphragm cap (15) is installed on the end of the diaphragm base (12) away from the gas cylinder top cover (11). A diaphragm compartment (13) is opened inside the diaphragm cap (15).

2. The decompression and oxygen replenishment device for high-altitude rapid start of a turbojet engine according to claim 1, characterized in that: The diaphragm compartment (13) is connected to a throat tube (18) through a first through hole. The first through hole is opened on the diaphragm base (12), and the throat tube (18) is installed inside the gas cylinder cover (11).

3. The decompression and oxygen replenishment device for high-altitude rapid start-up of a turbojet engine according to claim 2, characterized in that: The larger diameter end of the throat tube (18) is connected to the air inlet tube (20), and the end of the air inlet tube (20) extending out of the top cover (11) of the gas cylinder is connected to the cylinder body (2).

4. The decompression and oxygen replenishment device for high-altitude rapid start-up of a turbojet engine according to claim 2, characterized in that: The smaller diameter end of the throat tube (18) is connected to the air outlet tube (21), and the end of the air outlet tube (21) extending out of the gas cylinder cap (11) is connected to the exhaust nozzle (6).

5. The decompression and oxygen replenishment device for high-altitude rapid start of a turbojet engine according to claim 4, characterized in that: The air outlet pipe (21) is fixedly connected to and connected to a connecting pipe, which is connected to the diaphragm compartment (13) through a second through hole, which is opened on the diaphragm base (12).

6. The decompression and oxygen replenishment device for high-altitude rapid start-up of a turbojet engine according to claim 2, characterized in that: A diaphragm (14) is installed on one end of the diaphragm cover (15) facing the diaphragm base (12). A second pressure adjusting spring (16) is fixedly connected to the end of the diaphragm (14) away from the diaphragm base (12). The end of the second pressure adjusting spring (16) away from the diaphragm (14) is fixedly connected to the top inside the diaphragm cover (15).

7. The decompression and oxygen replenishment device for high-altitude rapid start of a turbojet engine according to claim 6, characterized in that: A connecting rod (17) is fixedly connected to one end of the diaphragm (14) facing the diaphragm base (12). A throttling ball (19) is fixedly connected to the end of the connecting rod (17) that extends through the first through hole into the larger diameter end of the throat tube (18). A first pressure adjusting spring (10) is fixedly connected to the end of the throttling ball (19) away from the connecting rod (17). The end of the first pressure adjusting spring (10) away from the throttling ball (19) is fixedly connected to the end of the throat tube (18).

8. The decompression and oxygen replenishment device for high-altitude rapid start of a turbojet engine according to claim 7, characterized in that: An inflation check valve (5) is installed at the center of one end of the base (4) away from the bottle body (2), and the inflation check valve (5) is connected to the bottle body (2).

9. A method for using a decompression and oxygen replenishment device for rapid high-altitude start-up of a turbojet engine, based on any one of claims 1-8, characterized in that: Includes the following steps: S1. The pusher (3) operates when the engine needs additional oxygen; S2. Then, the voltage regulating component operates; S3. The gas inside the bottle (2) is ejected through the exhaust nozzle (6).

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