Lightweight torch ignition system and method

Abstract

The invention discloses a light-weight torch ignition system and method. The light-weight torch ignition system comprises an oxidant supply unit, a fuel supply unit, a thrust chamber and an igniter. The oxidant supply unit and the fuel supply unit are both communicated with the thrust chamber so as to supply an oxidant and fuel into the thrust chamber; the oxidant supply unit is sequentially connected with an oxygen pump and an oxygen main valve through a pipeline; the oxygen main valve is connected with the thrust chamber; the fuel supply unit is sequentially connected with a fuel pump and a fuel main valve through a pipeline; the fuel main valve is connected with the thrust chamber; the igniter is mounted on the thrust chamber; an oxygen inlet and a fuel inlet are formed in the igniter; the pipeline between the oxygen pump and the oxygen main valve is communicated through a first auxiliary pipeline; the first auxiliary pipeline is connected with an igniter oxygen valve; the pipeline between the fuel pump and the fuel main valve is communicated through a second auxiliary pipeline; and an igniter oxygen valve is arranged on the first auxiliary pipeline. According to the torch ignition system, infinite ignition can be achieved, and the mass and the size of the torch ignition system are greatly reduced.

Description

Technical Field

[0001] This invention relates to the field of liquid rocket engine technology, and in particular to a lightweight torch ignition system and method. Background Technology

[0002] Liquid rocket engines are typically ignited using methods such as gunpowder ignition, torch ignition, and chemical auto-ignition. Gunpowder ignition involves using a pyrotechnic device filled with solid gunpowder to ignite the propellant. When the pyrotechnic device is energized, the gunpowder ignites, producing a flame. Pyrotechnic devices are generally for single use; multiple devices are needed for multiple ignitions. Torch ignition uses a small combustion chamber, where an electric spark plug ignites the propellant injected into the chamber, forming a torch. Torch ignition usually requires a high-pressure gas cylinder or starter box to supply propellant to the combustion chamber. Theoretically, torch ignition can be used multiple times until the maximum allowable capacity of the high-pressure gas cylinder or starter box is reached. Chemical auto-ignition uses a chemical agent that can auto-ignite with the oxidizer to ignite the propellant. This chemical agent is typically a mixture of triethylaluminum and triethylboron, which is a flammable and explosive hazardous material and must be sealed in a special conduit. It is generally for single-use ignition.

[0003] Existing liquid rocket engine torch ignition generally employs a high-pressure compression supply scheme, with high-pressure gas cylinders specifically carried on the engine or rocket. High-pressure oxygen cylinders are used as oxidizers, and high-pressure hydrogen or high-pressure methane cylinders are used as fuels. The flow of oxidizer and fuel is controlled by valves at the cylinder outlets, and electric spark plugs are used to ignite the propellant in the igniter.

[0004] The main drawback of the current high-pressure extrusion torch ignition scheme is that it requires carrying a high-pressure gas cylinder with large mass and volume, which makes the torch ignition system bulky and complex, reducing the effective payload mass of the rocket. Summary of the Invention

[0005] The purpose of this invention is to provide a lightweight torch ignition system and method to overcome the shortcomings of the prior art. It can achieve unlimited ignition and greatly reduce the weight and volume of the torch ignition system.

[0006] The present invention provides a lightweight flare ignition system, comprising an oxidizer supply unit and a fuel supply unit, a thrust chamber and an igniter; Both the oxidant supply unit and the fuel supply unit are connected to the thrust chamber to supply oxidant and fuel into the thrust chamber; The oxidant supply unit is connected in sequence to the oxygen pump and the oxygen main valve via pipelines; the oxygen main valve is connected to the thrust chamber. The fuel supply unit is connected in sequence to a fuel pump and a main fuel valve via pipelines; the main fuel valve is connected to the thrust chamber. The igniter is mounted on the thrust chamber; the igniter is provided with an oxygen inlet and a fuel inlet; the pipeline between the oxygen pump and the main oxygen valve is connected through a first auxiliary pipeline; the igniter oxygen valve is connected to the first auxiliary pipeline; the pipeline between the fuel pump and the main fuel valve is connected through a second auxiliary pipeline. An igniter oxygen valve is installed on the first auxiliary pipeline.

[0007] In the lightweight flare ignition system described above, optionally, an igniter fuel valve is provided on the second auxiliary pipeline.

[0008] In the lightweight flare ignition system described above, optionally, during ignition, both the oxygen pump and the fuel pump operate, and the main oxygen valve, the main fuel valve, the igniter oxygen valve, and the igniter fuel valve are all open; the igniter ignites, and the oxidizer entering the thrust chamber through the main oxygen valve and the fuel entering the thrust chamber through the main fuel valve mix and are ignited in the thrust chamber.

[0009] In the lightweight torch ignition system described above, optionally, the igniter oxygen valve opens during ignition and closes after ignition is complete.

[0010] In the lightweight flare ignition system described above, optionally, the igniter fuel valve remains open after successful ignition in the fuel chamber.

[0011] The lightweight flare ignition system described above may optionally include a third auxiliary pipeline, a fourth auxiliary pipeline, a gas generator, and a turbine. An oxygen auxiliary valve is provided on the third auxiliary pipeline, and a fuel auxiliary valve is provided on the fourth auxiliary pipeline; One end of the third auxiliary pipeline is connected between the oxygen pump and the oxygen main valve, and the other end is connected to the gas generator; One end of the fourth auxiliary pipeline is connected between the fuel pump and the main fuel valve, and the other end is connected to the gas generator; The exhaust outlet of the gas generator is connected to the turbine; the turbine is connected to the oxygen pump and the fuel pump.

[0012] The present invention also proposes a lightweight torch ignition method for use in the lightweight torch ignition system described in Example 1, the method comprising: The oxidant between the oxygen pump and the main oxygen valve is introduced into the oxygen inlet of the igniter. Fuel between the fuel pump and the main fuel valve is introduced into the igniter fuel inlet; Ignition by igniter; Open the oxygen main valve and the fuel main valve.

[0013] In the lightweight flare ignition method described above, optionally, the igniter oxygen valve on the first auxiliary pipeline is closed after ignition is completed.

[0014] In the lightweight torch ignition method described above, optionally, after the igniter oxygen valve on the first auxiliary pipeline is closed, the pressure in the thrust chamber increases, pressing the igniter oxygen valve tightly.

[0015] In the lightweight torch ignition method described above, the oxidant may optionally be liquid oxygen.

[0016] Compared with the prior art, the present invention has the following beneficial effects: The lightweight flare ignition system described in the invention theoretically enables an unlimited number of ignitions since the propellant supply is not limited by the volume of the high-pressure gas cylinder, and also greatly reduces the mass and volume of the flare ignition system. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of a lightweight torch ignition system proposed in this invention.

[0018] Explanation of reference numerals in the attached figures: 1-Oxidizer supply unit, 2-Fuel supply unit, 3-Thrust chamber, 4-Igniter, 5-Igniter oxygen valve, 6-Igniter fuel valve, 7-Third auxiliary pipeline, 8-Fourth auxiliary pipeline, 9-Gas generator, 10-Turbine; 11-Oxygen pump, 12-Oxygen main valve, 13-First auxiliary pipeline; 21-Fuel pump, 22-Main fuel valve, 23-Second auxiliary pipeline; 71-Oxygen auxiliary valve; 81-Fuel auxiliary valve. Detailed Implementation

[0019] The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0020] In view of the problems mentioned in the background art, the present invention provides the following embodiments to solve them.

[0021] Example 1 Please refer to Figure 1 This invention proposes a lightweight flare ignition system, comprising an oxidizer supply unit 1 and a fuel supply unit 2, a thrust chamber 3, and an igniter 4. The oxidizer supply unit 1 supplies oxidizer to the thrust chamber 3, the fuel supply unit 2 supplies fuel to the thrust chamber 3, and the thrust chamber 3 is used for co-fuel combustion.

[0022] In practice, both the oxidant supply unit 1 and the fuel supply unit 2 are connected to the thrust chamber 3 to supply oxidant and fuel to the thrust chamber 3. The oxidant supply unit 1 is connected in sequence to the oxygen pump 11 and the oxygen main valve 12 via pipelines; the oxygen main valve 12 is connected to the thrust chamber 3.

[0023] The fuel supply unit 2 is connected in sequence to a fuel pump 21 and a fuel main valve 22 via pipelines; the fuel main valve 22 is connected to the thrust chamber 3.

[0024] The igniter 4 is mounted on the thrust chamber 3; the igniter 4 is equipped with an oxygen inlet and a fuel inlet; the pipeline between the oxygen pump 11 and the main oxygen valve 12 is connected through a first auxiliary pipeline 13; an igniter oxygen valve 5 is connected to the first auxiliary pipeline 13; the pipeline between the fuel pump 21 and the main fuel valve 22 is connected through a second auxiliary pipeline 23. An igniter oxygen valve 5 is provided on the first auxiliary pipeline 13. An igniter fuel valve 6 is provided on the second auxiliary pipeline 23.

[0025] When ignition is required, the oxidant enters the oxygen main valve 12 via the oxygen pump 11; the fuel enters the fuel main valve 22 via the fuel pump 21; the igniter oxygen valve 5 and igniter fuel valve 6 are opened, and the oxidant enters the igniter 4 via the first auxiliary pipeline 13, while the fuel enters the igniter 4 via the second auxiliary pipeline 23. The oxidant and fuel mix in the igniter 4 and are ignited by the spark plug inside the igniter 4. Then, the oxygen main valve 12 and fuel main valve 22 are opened, allowing the fuel and oxidant to enter the thrust chamber 3 via the main pipeline, and the fuel is then added to the thrust chamber 3.

[0026] After ignition, as the engine starts, the engine operating conditions continuously increase, the pressure in the thrust chamber rises, controlling the igniter oxygen valve to close, and the igniter shuts off. The high pressure after the oxygen pump makes the igniter oxygen valve core close more tightly, preventing liquid oxygen from the oxygen pump outlet from entering the igniter during the main stage of the engine, which would cause an excessively high mixture ratio in the igniter and lead to igniter erosion. The igniter fuel valve remains open during the main stage of the engine, also for the purpose of protecting the igniter from erosion.

[0027] Through the above system, the lightweight flare ignition system proposed in this embodiment can theoretically achieve an unlimited number of ignitions because the propellant supply is not limited by the volume of the high-pressure gas cylinder, and the mass and volume of the flare ignition system are greatly reduced.

[0028] In specific implementation, during ignition, both the oxygen pump 11 and the fuel pump 21 operate, and the oxygen main valve 12, the fuel main valve 22, the igniter oxygen valve 5, and the igniter fuel valve 6 are all opened; the igniter 4 ignites, and the oxidant entering the thrust chamber 3 through the oxygen main valve 12 and the fuel entering the thrust chamber 3 through the fuel main valve 22 mix and are ignited in the thrust chamber 3.

[0029] During use, in order to prevent the igniter from being burned, the igniter oxygen valve 5 is opened during ignition and closed after ignition is completed, thus shutting off the igniter oxygen valve 5.

[0030] In practice, the igniter fuel valve 6 remains open after successful ignition in the fuel chamber. In practical applications, the igniter fuel valve 6 can also be adjusted as needed.

[0031] In specific implementation, to drive the oxygen pump 11 and fuel pump 21, this embodiment also includes a third auxiliary pipeline 7, a fourth auxiliary pipeline 8, a gas generator 9, and a turbine 10. The gas generator is used to supply the oxidant to react with the fuel, and the resulting gas flow drives the turbine 10 to rotate, which in turn drives the oxygen pump 11 and fuel pump 21. Specifically, the third auxiliary pipeline 7 is equipped with an oxygen auxiliary valve 71, and the fourth auxiliary pipeline 8 is equipped with a fuel auxiliary valve 81. One end of the third auxiliary pipeline 7 is connected between the oxygen pump 11 and the oxygen main valve 12, and the other end is connected to the gas generator 9. One end of the fourth auxiliary pipeline 8 is connected between the fuel pump 21 and the fuel main valve 22, and the other end is connected to the gas generator 9. The exhaust outlet of the gas generator 9 is connected to the turbine 10. The turbine 10 is connected to the oxygen pump 11 and the fuel pump 21. In use, the oxygen pump 11 and fuel pump 21 can be controlled by controlling the oxygen auxiliary valve 71 and the fuel auxiliary valve 81.

[0032] Example 2 This embodiment is the system torch ignition method proposed in Embodiment 1. The similarities will not be repeated. Only the differences will be explained below.

[0033] This embodiment proposes a lightweight torch ignition method, wherein the lightweight torch ignition system includes the following methods: The oxidant between the oxygen pump 11 and the oxygen main valve 12 is introduced into the oxygen inlet of the igniter.

[0034] Fuel between fuel pump 21 and main fuel valve 22 is introduced into the igniter fuel inlet. In specific implementation, the oxidizer between oxygen pump 11 and main oxygen valve 12 is introduced into the igniter oxygen inlet by the pressure of the rocket tank, and fuel between fuel pump 21 and main fuel valve 22 is introduced into the igniter fuel inlet.

[0035] Ignition 4 ignites; the ignition process of the igniter is initiated by the spark plug inside the igniter 4, which ignites the fuel sprayed out by the igniter 4.

[0036] Open the oxygen main valve 12 and the fuel main valve 22.

[0037] After ignition is complete, close the igniter oxygen valve 5 on the first auxiliary pipeline 13.

[0038] After the igniter oxygen valve 5 on the first auxiliary pipeline 13 is closed, the pressure in the thrust chamber 3 increases, pressing the igniter oxygen valve 5 tightly.

[0039] After the main fuel in thrust chamber 3 is ignited, as the engine starts, the engine operating conditions continuously increase, the chamber pressure in thrust chamber 3 rises, controlling the igniter oxygen valve to close, and the igniter shuts off. The high pressure after the oxygen pump makes the igniter oxygen valve core close more tightly, preventing liquid oxygen from the oxygen pump outlet from entering the igniter during the main stage of the engine, which would cause the mixture ratio inside the igniter to be too high and cause the igniter to burn. The igniter fuel valve remains open during the main stage of the engine, also for the purpose of protecting the igniter from burning.

[0040] In Embodiments 1 and 2 of this invention, the oxidant is liquid oxygen.

[0041] The above description, based on the embodiments shown in the figures, details the structure, features, and effects of the present invention. The above description is only a preferred embodiment of the present invention, but the present invention is not limited to the scope of implementation shown in the figures. Any changes made in accordance with the concept of the present invention, or equivalent embodiments modified to have equivalent changes, that do not exceed the spirit covered by the specification and figures, should be within the protection scope of the present invention.

Claims

1. A lightweight torch ignition system, characterized in that: It includes an oxidizer supply unit (1) and a fuel supply unit (2), a thrust chamber (3) and an igniter (4); The oxidant supply unit (1) and the fuel supply unit (2) are both connected to the thrust chamber (3) to supply oxidant and fuel to the thrust chamber (3); The oxidant supply unit (1) is connected in sequence to the oxygen pump (11) and the oxygen main valve (12) via pipelines; the oxygen main valve (12) is connected to the thrust chamber (3); The fuel supply unit (2) is connected in sequence to a fuel pump (21) and a fuel main valve (22) via pipelines; the fuel main valve (22) is connected to the thrust chamber (3); The igniter (4) is installed on the thrust chamber (3); the igniter (4) is provided with an oxygen inlet and a fuel inlet; the pipeline between the oxygen pump (11) and the oxygen main valve (12) is connected through a first auxiliary pipeline (13); the igniter oxygen valve (5) is connected to the first auxiliary pipeline (13); the pipeline between the fuel pump (21) and the fuel main valve (22) is connected through a second auxiliary pipeline (23); An igniter oxygen valve (5) is installed on the first auxiliary pipeline (13).

2. The lightweight torch ignition system according to claim 1, characterized in that: The second auxiliary pipeline (23) is equipped with an igniter fuel valve (6).

3. The lightweight torch ignition system according to claim 2, characterized in that: During ignition, both the oxygen pump (11) and the fuel pump (21) are operational, and the oxygen main valve (12), the fuel main valve (22), the igniter oxygen valve (5), and the igniter fuel valve (6) are all open; the igniter (4) ignites, and the oxidant entering the thrust chamber (3) through the oxygen main valve (12) and the fuel entering the thrust chamber (3) through the fuel main valve (22) are mixed and ignited in the thrust chamber (3).

4. The lightweight torch ignition system according to claim 3, characterized in that: The igniter oxygen valve (5) opens during ignition and closes after ignition is complete.

5. The lightweight torch ignition system according to claim 4, characterized in that: The igniter fuel valve (6) remains open after successful ignition in the fuel chamber.

6. The lightweight torch ignition system according to claim 1, characterized in that: It also includes a third auxiliary pipeline (7), a fourth auxiliary pipeline (8), a gas generator (9), and a turbine (10); The third auxiliary pipeline (7) is equipped with an oxygen auxiliary valve (71), and the fourth auxiliary pipeline (8) is equipped with a fuel auxiliary valve (81). One end of the third auxiliary pipeline (7) is connected between the oxygen pump (11) and the oxygen main valve (12), and the other end is connected to the gas generator (9); One end of the fourth auxiliary pipeline (8) is connected between the fuel pump (21) and the fuel main valve (22), and the other end is connected to the gas generator (9); The exhaust outlet of the gas generator (9) is connected to the turbine (10); the turbine (10) is connected to the oxygen pump (11) and the fuel pump (21).

7. A lightweight torch ignition method, characterized in that, The method for the lightweight flare ignition system according to any one of claims 1-6 comprises: The oxidant between the oxygen pump (11) and the oxygen main valve (12) is introduced into the oxygen inlet of the igniter; Fuel between the fuel pump (21) and the main fuel valve (22) is introduced into the igniter fuel inlet; Ignition (4) igniter; Open the oxygen main valve (12) and the fuel main valve (22).

8. The lightweight torch ignition method according to claim 7, characterized in that, After ignition is completed, close the igniter oxygen valve (5) on the first auxiliary pipeline (13).

9. The lightweight torch ignition method according to claim 8, characterized in that, After the igniter oxygen valve (5) on the first auxiliary pipeline (13) is closed, the pressure in the thrust chamber (3) increases, pressing the igniter oxygen valve (5) tightly.

10. The lightweight torch ignition method according to claim 7, characterized in that, The oxidant is liquid oxygen.

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