Pressure reduction and oxygen supplementation device for high-altitude quick start of turbojet engine and use method of pressure reduction and oxygen supplementation device

Abstract

The invention relates to the technical field of turbojet engine oxygen supplementation, in particular to a pressure reducing and oxygen supplementation device for high-altitude quick start of a turbojet engine and a using method, the pressure reducing and oxygen supplementation device comprises a bottle body, a pressure reducing valve used for adjusting pressure is mounted at the top of the bottle body, and a base used for inflating the bottle body is mounted at the bottom of the bottle body; the pressure reducing valve comprises a gas cylinder upper cover fixedly connected with the cylinder body, the gas cylinder upper cover is communicated with a pin pusher and an exhaust nozzle, and a pressure adjusting assembly is installed at the end, away from the cylinder body, of the gas cylinder upper cover. By means of the pressure regulating assembly arranged in the pressure reducing valve, oxygen can be effectively supplemented to the engine during high-altitude starting, air rarefaction is avoided, fuel oil is rapidly combusted, the high-altitude starting problem is solved, and meanwhile the starting time is shortened; the pressure reducing valve is integrated on the bottle body, so that the weight and the size of the bottle body can be effectively reduced under the condition of increasing the volume.

Description

Technical Field

[0001] The present invention relates to the technical field of oxygen supplementation for turbojet engines, and particularly to a decompression oxygen supplementation device and a usage method for high-altitude rapid start of a turbojet engine. Background Art

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

[0003] However, there is a contradiction between the high-altitude rapid start, compact structure, and lightweight requirements of small fixed-wing aircraft and the large volume, high weight, and inability to decompress and throttle of conventional oxygen cylinders (the cost of pyrotechnic starters and pyrotechnic igniters is high).

[0004] As the preferred power for current small aircraft, whether a turbojet engine can start at high altitude directly affects the flight envelope and performance of the aircraft. An engine that does not have high-altitude rapid start cannot meet the usage requirements under special conditions.

[0005] Currently, the conventional solution on the market is to use an internal pyrotechnic igniter and a pyrotechnic starter to solve the high-altitude start problem. The engine with the pyrotechnic solution has a large volume and high weight, and the pyrotechnics are disposable consumable materials, with high costs and high safety risks.

[0006] The existing oxygen supplementation device for turbojet engines has a relatively high inflation pressure (20 Mpa), so most of them use stainless steel materials, which have low strength and high density of the material itself. Under the condition of the same wall thickness, it cannot withstand a large pressure (less oxygen filling). If you want to increase the oxygen mass, it can only be achieved by increasing the volume or the wall thickness, which brings the problem of the large weight of the oxygen supplementation device.

[0007] It can be seen that the existing oxygen supplementation devices have a large volume and do not meet the requirements of special aircraft for a compact structure, and have a large weight and do not meet the lightweight requirements of special aircraft.

[0008] Therefore, there is an urgent need for a decompression oxygen supplementation device and a usage method for high-altitude rapid start of a turbojet engine, which can effectively supplement oxygen to the engine during high-altitude start, avoid thin air, enable the fuel to burn rapidly, solve the high-altitude start problem, and at the same time reduce the start time. Summary of the Invention

[0009] The object of the present invention is to provide a decompression and oxygen supplementation device for high-altitude rapid start of a turbojet engine and a usage method thereof, so as to solve the problems existing in the above-mentioned prior art.

[0010] To achieve the above object, the present invention provides the following solution: A decompression and oxygen supplementation device for high-altitude rapid start of a turbojet engine, including a bottle body, a pressure reducing valve for adjusting pressure is installed at the top of the bottle body, and a base for inflating the bottle body is installed at the bottom of the bottle body; the pressure reducing valve includes a gas cylinder upper cover fixedly connected to the bottle body, a pusher and an exhaust nozzle are communicated with the gas cylinder upper cover, and a pressure regulating assembly is installed at one end of the gas cylinder upper cover away from the bottle body.

[0011] Preferably, the pressure regulating assembly includes a diaphragm base installed at one end of the gas cylinder upper cover away from the bottle body, a diaphragm gland is installed at one end of the diaphragm base away from the gas cylinder upper cover, and a diaphragm chamber is opened in the diaphragm gland.

[0012] Preferably, the diaphragm chamber is communicated with a throat pipe through a first through hole, the first through hole is opened on the diaphragm base, and the throat pipe is installed in the gas cylinder upper cover.

[0013] Preferably, the end with a larger diameter of the throat pipe is communicated with an air inlet pipe, and one end of the air inlet pipe extending outside the gas cylinder upper cover is communicated with the bottle body.

[0014] Preferably, the end with a smaller diameter of the throat pipe is communicated with an air outlet pipe, and one end of the air outlet pipe extending outside the gas cylinder upper cover is communicated with an exhaust nozzle.

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

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

[0017] Preferably, a connecting rod is fixedly connected to one end of the diaphragm facing the diaphragm base, the end of the connecting rod passing through the first through hole and extending into the end with a larger diameter of the throat pipe is fixedly connected with a throttle ball, a first pressure regulating spring is fixedly connected to one end of the throttle ball facing away from the connecting rod, and the end of the first pressure regulating spring away from the throttle ball is fixedly connected to the end of the throat pipe.

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

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

[0020] S1. When the engine needs to supplement oxygen, the pusher works;

[0021] S2. Then, the pressure regulating assembly operates;

[0022] S3. The gas in the cylinder body is ejected through the exhaust nozzle.

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

[0024] By providing a pressure regulating assembly in the pressure reducing valve, the present invention can effectively supplement oxygen to the engine during high-altitude start-up, avoid thin air, enable rapid combustion of fuel, solve the high-altitude start-up problem, and at the same time reduce the start-up time.

[0025] By integrating a pressure reducing valve on the cylinder body, the present invention can effectively reduce the weight and volume of the cylinder body while increasing the volume. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required to be used in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

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

[0028] Figure 2 It is a schematic cross-sectional structure diagram of the pressure reducing valve of the present invention;

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

[0030] Among them, 1, pressure reducing valve; 2, cylinder body; 3, pusher; 4, base; 5, inflation check valve; 6, exhaust nozzle; 10, first pressure regulating spring; 11, cylinder head; 12, diaphragm base; 13, diaphragm chamber; 14, diaphragm; 15, diaphragm gland; 16, second pressure regulating spring; 17, connecting rod; 18, throat; 19, throttle ball; 20, intake pipe; 21, outlet pipe. DETAILED DESCRIPTION OF THE INVENTION

[0031] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present invention.

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

[0033] Referring to Figures 1 - 3 , the present invention provides a decompression and oxygen supplementation device for high-altitude rapid start of a turbojet engine, including a bottle body 2. A pressure reducing valve 1 for regulating pressure is installed at the top of the bottle body 2, and a base 4 for inflating the bottle body 2 is installed at the bottom of the bottle body 2; the pressure reducing valve 1 includes a gas cylinder upper cover 11 fixedly connected to the bottle body 2. A pusher 3 and an exhaust nozzle 6 are communicated with the gas cylinder upper cover 11, and a pressure regulating assembly is installed at one end of the gas cylinder upper cover 11 away from the bottle body 2.

[0034] Through the pressure regulating assembly provided in the pressure reducing valve 1, the present invention can effectively supplement oxygen to the engine during high-altitude start-up, avoid thin air, enable the fuel to burn rapidly, solve the high-altitude start-up problem, and at the same time reduce the start-up time.

[0035] By integrating the pressure reducing valve 1 on the bottle body 2, the present invention can effectively reduce the weight and volume of the bottle body 2 while increasing the volume.

[0036] In a further optimized solution, the pressure regulating assembly includes a diaphragm base 12 installed at one end of the gas cylinder upper cover 11 away from the bottle body 2. A diaphragm gland 15 is installed at one end of the diaphragm base 12 away from the gas cylinder upper cover 11, and a diaphragm chamber 13 is opened in the diaphragm gland 15. This enables the pressure regulating assembly to be effectively installed in the pressure reducing valve 1.

[0037] In a further optimized solution, the diaphragm chamber 13 is communicated with a throat 18 through a first through hole. The first through hole is opened on the diaphragm base 12, and the throat 18 is installed in the gas cylinder upper cover 11. Through the first through hole, the throat 18 can be communicated with the diaphragm chamber 13.

[0038] In a further optimized solution, the end with a larger diameter of the throat 18 is communicated with an intake pipe 20. The end of the intake pipe 20 extending outside the gas cylinder upper cover 11 is communicated with the bottle body 2. Through the intake pipe 20, the gas in the bottle body 2 can enter the throat 18.

[0039] In a further optimized solution, the end of the throat 18 with a small diameter is connected to an air outlet pipe 21, and the end of the air outlet pipe 21 extending outside the gas cylinder cover 11 is connected to an exhaust nozzle 6. The gas enters the air outlet pipe 21 through the throat 18, and then the gas is ejected from the exhaust nozzle 6 through the air outlet pipe 21.

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

[0041] The pusher 3 is connected to one end of the air outlet pipe 21 close to the exhaust nozzle 6 through a sealing member, and the pipeline between the air outlet pipe 21 and the exhaust nozzle 6 can be opened and closed by the pusher 3.

[0042] The sealing member is used to control the opening and closing of the air outlet pipe 21 .

[0043] When the engine does not need to supplement oxygen, the turbojet controller sends a command to the sales pitcher 3, and the sales pitcher 3 controls the action of the seal, which blocks the outlet pipe 21, thereby disconnecting the pipeline between the outlet pipe 21 and the exhaust nozzle 6.

[0044] When the engine needs to supplement oxygen, the turbojet controller sends instructions to the sales pitcher 3, and the sales pitcher 3 controls the action of the seal, so that the seal does not block the outlet pipe 21, so that the pipeline between the outlet pipe 21 and the exhaust nozzle 6 is connected, so that the gas can be ejected from the exhaust nozzle 6 through the outlet pipe 21.

[0045] In a further optimized solution, a connecting pipe is fixedly connected to and communicated with the air outlet pipe 21, and the connecting pipe is connected to the diaphragm bin 13 through a second through hole, and the second through hole is opened on the diaphragm base 12. The air outlet pipe 21 is connected to the diaphragm bin 13 through the second through hole.

[0046] In a further optimized solution, a diaphragm 14 is installed at one end of the diaphragm gland 15 facing the diaphragm base 12, a second pressure regulating spring 16 is fixedly connected to one end of the diaphragm 14 away from the diaphragm base 12, and one end of the second pressure regulating spring 16 away from the diaphragm 14 is fixedly connected to the top inside the diaphragm gland 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 to connect the first through hole with the second through hole.

[0047] According to a further optimization scheme, 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 passes through the first through hole and extends into the end of the throat 18 with a larger diameter.

[0048] Through the contraction of 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 large-diameter end and the small-diameter end of the throat 18, the throttle ball 19 cuts off the flow of gas in the throat 18 to the first through hole and the air outlet pipe 21; through the cooperation of the throttle ball 19 and the throat 18, the function of pressure regulation is realized.

[0049] In a further optimized solution, a first pressure regulating spring 10 is fixedly connected to the end of the throttle ball 19 facing 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 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 effectively spray out through the air outlet pipe 21.

[0051] In a further optimized solution, an inflation check valve 5 is installed at the center of the end of the base 4 away from the bottle body 2, and the inflation check valve 5 is communicated with the bottle body 2. It is convenient to inflate the bottle body 2 through the inflation check valve 5.

[0052] A method of using a pressure reducing and oxygen supplementing device for high-altitude rapid start of a turbojet engine includes the following steps:

[0053] S1. When the engine needs to supplement oxygen, the pusher 3 works; the pipeline between the air outlet pipe 21 and the exhaust nozzle 6 is connected.

[0054] S2. Then, the pressure regulating assembly operates; the gas in the bottle body 2 enters the throat 18 from the inlet pipe 20. A part of the gas in the throat 18 flows into the air outlet pipe 21, and the other part of the gas enters the diaphragm chamber 13 through the first through hole. The gas in the diaphragm chamber 13 pushes the diaphragm 14 to compress the second pressure regulating spring 16. The diaphragm 14 deforms and displaces upward, allowing the gas in the diaphragm chamber 13 to enter the air 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 displaces downward under the action of the second pressure regulating spring 16, causing the throttle ball 19 to no longer seal the throat 18 and reopening the flow channel in the throat 18; through the extremely high-frequency reciprocating cycle of the throttle ball 19, the pressure regulating function is realized.

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

[0056] When the gas in the bottle body 2 is insufficient, the bottle body 2 can be inflated through the inflation check valve 5.

[0057] Working process: When the engine needs to supplement oxygen, the turbojet controller issues an instruction to the pusher 3, and the pusher 3 works to connect the pipeline between the outlet pipe 21 and the exhaust nozzle 6. At this time, the gas in the bottle body 2 enters the throat pipe 18 from the inlet pipe 20. Part of the gas in the throat pipe 18 flows into the outlet pipe 21, and the other part of the gas 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, and the diaphragm 14 deforms and displaces upward, so that the gas in the diaphragm chamber 13 enters 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 pipe 18 is much greater than the pressure of the second pressure regulating spring 16, the throttle ball 19 cooperates with the throat pipe 18 to seal the throat pipe 18. At this time, the diaphragm 14 displaces downward under the action of the second pressure regulating spring 16, so that the throttle ball 19 no longer seals the throat pipe 18, and the flow channel in the throat pipe 18 is reopened. Through the extremely high-frequency reciprocating cycle of the throttle ball 19, the pressure regulating function is realized.

[0058] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "longitudinal", "transverse", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0059] The above-described embodiments are only descriptions of the preferred embodiments of the present invention, and do not limit the scope of the present invention. Without departing from the design spirit of the present invention, various deformations and improvements made by those of ordinary skill in the art to the technical solutions of the present invention shall fall within the protection scope determined by the claims of the present invention.

Claims

1. A decompression and oxygen supplementation device for high-altitude rapid start of a turbojet engine, characterized in that: It comprises a bottle body (2), a pressure reducing valve (1) for adjusting the pressure is installed on the top of the bottle body (2), and a base (4) for inflating the bottle body (2) is installed on the bottom of the bottle body (2); The pressure reducing valve (1) comprises a gas cylinder upper cover (11) fixedly connected to the bottle body (2); the gas cylinder upper cover (11) is connected to a pusher (3) and an exhaust nozzle (6); and a pressure regulating assembly is installed at one end of the gas cylinder upper cover (11) away from the bottle body (2).

2. The decompression and oxygen supplementation device for high-altitude rapid start of a turbojet engine according to claim 1, wherein: The pressure regulating assembly comprises a diaphragm base (12) mounted on an end of the gas cylinder upper cover (11) away from the bottle body (2); a diaphragm pressure cover (15) is mounted on an end of the diaphragm base (12) away from the gas cylinder upper cover (11); and a diaphragm chamber (13) is provided in the diaphragm pressure cover (15).

3. The decompression and oxygen supplementation device for high-altitude rapid start of a turbojet engine according to claim 2, wherein: The diaphragm bin (13) is connected to a throat (18) via a first through hole, the first through hole is provided on the diaphragm base (12), and the throat (18) is installed in the gas cylinder upper cover (11).

4. The decompression and oxygen supplementation device for high-altitude rapid start of a turbojet engine according to claim 3, characterized in that: The end of the throat pipe (18) with a larger diameter is connected to an air intake pipe (20), and the end of the air intake pipe (20) extending outside the gas cylinder upper cover (11) is connected to the cylinder body (2).

5. The decompression and oxygen supplementation device for high-altitude rapid start of a turbojet engine according to claim 3, wherein: The end of the throat pipe (18) with a smaller diameter is connected to an air outlet pipe (21), and the end of the air outlet pipe (21) extending outside the gas cylinder upper cover (11) is connected to an exhaust nozzle (6).

6. The decompression and oxygen supplementation device for high-altitude rapid start of a turbojet engine according to claim 5, characterized in that: A connecting pipe is fixedly connected to and communicated with the air outlet pipe (21), and the connecting pipe is connected to the diaphragm bin (13) via a second through hole, and the second through hole is provided on the diaphragm base (12).

7. The decompression and oxygen supplementation device for high-altitude rapid start of a turbojet engine according to claim 3, characterized in that: A diaphragm (14) is installed on one end of the diaphragm cover (15) facing the diaphragm base (12); a second pressure-regulating spring (16) is fixedly connected to one end of the diaphragm (14) facing away from the diaphragm base (12); and an end of the second pressure-regulating spring (16) away from the diaphragm (14) is fixedly connected to the top inside the diaphragm cover (15).

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

9. The decompression and oxygen supplementation device for high-altitude rapid start of a turbojet engine according to claim 8, wherein: 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).

10. A method of using decompression and oxygen supplementation for high-altitude rapid start of a turbojet engine, based on the decompression and oxygen supplementation device for high-altitude rapid start of a turbojet engine according to any one of claims 1-9, characterized in that: The following steps are involved: S1. When the engine needs additional oxygen, the sales promoter (3) works; S2. Then, the voltage regulating component operates; S3. The gas in the bottle body (2) is ejected through the exhaust nozzle (6).

Images