Torch type electric igniter integrated on thrust chamber injector

Abstract

The invention relates to a torch type electric igniter integrated on a thrust chamber injector. The torch type electric igniter comprises an ignition chamber, an ignition plug, a sealing ring and a nut. The torch igniter and the injector are integrally designed, an ignition medium directly comes from an oxidant cavity and a fuel cavity of the thrust chamber injector, an ignition valve and an ignition pipeline are omitted, an ignition system is simplified, and the weight is reduced. Fuel of the igniter is divided into two paths, one path enters the center of the ignition chamber through the igniter fuel nozzle to be combusted, the other path enters the igniter discharge cooling circular seam through the radial hole to cool the inner wall of the ignition chamber, the flow of the two paths is independently controlled through the nozzle size and the circular seam size, and precise control over working condition parameters of the igniter is facilitated. The structure thermal protection capacity of the igniter under the ignition and main-stage working conditions is improved through emission cooling, after-combustion of oxygen-enriched fuel gas and emission cooling fuel is promoted through retraction of an outlet area, and the ignition energy is improved.

Description

Technical Field

[0001] The invention relates to a torch type electric igniter integrated on a thrust chamber injector, which is suitable for torch ignition of a hydrogen-oxygen rocket engine and can be used in the field of aerospace. Background Art

[0002] Reusable liquid rocket engines and high-performance upper stage engines both place greater demands on the number of engine ignitions. The currently widely used solution is to use a torch-type electric igniter to replace the traditional solid powder igniter. The ignition medium of the torch igniter is generally drawn from the pipeline after the engine pump or the high-pressure ignition gas cylinder, and enters the igniter through the ignition pipeline and ignition valve. The igniter is installed at the head of the thrust chamber as an independent component. Some liquid-liquid igniters generally also require special pre-cooling discharge valves and blow-off valves. The entire ignition system is relatively complex, with more components and heavier weight. Summary of the invention

[0003] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide a torch-type electric igniter integrated on the thrust chamber injector of a hydrogen-oxygen rocket engine, to eliminate the ignition valve and the ignition pipeline, to simplify the ignition system and to reduce the weight.

[0004] The technical solution of the present invention is:

[0005] A torch type electric igniter integrated on a thrust chamber injector comprises: an ignition chamber 3, an electric nozzle 1, a sealing ring 2 and a nut 15;

[0006] The nozzle 1 is installed at the center of the upper end of the ignition chamber 3 through a thread and is sealed by a sealing ring 2. The ignition chamber 3 is fixed to the first bottom 14 of the thrust chamber injector by a nut 15. The ignition chamber 3 is connected to the second bottom 10 and the third bottom 4 of the thrust chamber injector by welding.

[0007] The injector fuel chamber 12 is between the first bottom 14 and the second bottom 10, and the injector oxidant chamber 8 is between the second bottom 10 and the third bottom 4;

[0008] The ignition chamber 3 is provided with an ignition chamber fuel nozzle 5, an ignition chamber fuel nozzle flow channel 7, an ignition chamber fuel nozzle inlet 9, an ignition chamber discharge cooling inlet 11, an ignition chamber discharge cooling annular gap 13 and an ignition chamber oxidant nozzle 17, and the center of the ignition chamber 3 is provided with an ignition chamber central combustion chamber 6 along the axial direction;

[0009] The fuel is sprayed from the injector fuel chamber 12, through the ignition chamber fuel nozzle inlet 9, the ignition chamber fuel nozzle flow channel 7, and the ignition chamber fuel nozzle 5 into the ignition chamber central combustion chamber 6; the oxidant is sprayed into the ignition chamber central combustion chamber 6 along the injector oxidant chamber 8 and the ignition chamber oxidant nozzle 17; the oxidant and the fuel are atomized and mixed in the ignition chamber central combustion chamber 6, and are ignited by the upper electric nozzle 1 to form a high-temperature oxygen-rich combustion gas that is discharged downstream of the ignition chamber;

[0010] The fuel flows from the injector fuel cavity 12, passes through the radially arranged ignition chamber emission cooling inlet 11 and enters the ignition chamber emission cooling annular gap 13 to cool the inner wall of the ignition chamber. This part of the fuel meets the high-temperature oxygen-rich combustion gas in the center of the ignition chamber in the ignition chamber outlet indentation area 16, and is supplementally burned to increase the ignition energy.

[0011] Furthermore, the ignition chamber emission cooling inlets 11 are arranged in n1 layers, the number of the ignition chamber emission cooling inlets 11 in each layer is n2, and the ignition chamber emission cooling inlets 11 between the layers form an angle of 360 / n1 / n2 degrees.

[0012] Furthermore, the total area of ​​the ignition chamber discharge cooling inlet 11 is not less than twice the area of ​​the cooling annular gap;

[0013] The total area of ​​the ignition chamber discharge cooling inlet 11 refers to the sum of the cross-sectional areas of all the ignition chamber discharge cooling inlets 11; the cooling annular gap area refers to the cross-sectional area of ​​the cooling annular gap.

[0014] Furthermore,

[0015] The ignition chamber fuel nozzle 5 and the ignition chamber oxidant nozzle 17 are both direct current nozzles. There are two ignition chamber fuel nozzles 5 and two oxidant nozzles 17. The plane formed by the ignition chamber fuel nozzles 5 and the plane formed by the ignition chamber oxidant nozzles 17 are perpendicular to each other. The angle between the two ignition chamber fuel nozzles 5 is A, and the distance between the intersection of the fuel nozzles and the end face of the nozzle is d1; the angle between the two oxidant nozzles 17 is B, and the distance between the intersection of the oxidant nozzles and the end face of the nozzle is d2.

[0016] Furthermore, the angle A has a value range of 90° to 150°, the angle B has a value range of 90° to 150°, and A≤B≤A+20°, 0.3D≤d1=d2≤D, where D is the diameter of the fuel cavity 6 at the center of the ignition chamber.

[0017] Furthermore, after the oxidant and the fuel are injected into the central fuel cavity 6 of the ignition chamber, they collide with each other and the space.

[0018] Furthermore, the length L of the ignition chamber outlet retracted area 16 is in the range of 0.5D≤L≤1.5D.

[0019] Furthermore, the ignition chamber 3 is integrally formed by 3D printing to achieve the distribution of the ignition medium and the combustion of the torch.

[0020] Furthermore, after the ignition chamber 3 is processed, an independent gas-liquid flow screening inspection is carried out, and then it is welded to the second and third bottoms of the injector, and connected to the first bottom with a nut, becoming a part of the injector, which is used for ignition of the igniter and as a fire guide tube in the center of the injector.

[0021] Furthermore, the ignition chamber fuel nozzle flow is controlled by the ignition chamber fuel nozzle (5) hole size, and the ignition chamber exhaust cooling flow is controlled by the cooling ring gap size.

[0022] Furthermore, when the thrust chamber is ignited and started,

[0023] The thrust chamber oxidizer valve is opened first, and the oxidizer flows into the injector oxidizer chamber and into the central combustion chamber of the ignition chamber through the ignition chamber oxygen nozzle;

[0024] The ignition nozzle starts to energize and ignite;

[0025] The thrust chamber fuel valve is opened, and the fuel enters the injector fuel chamber and the ignition chamber central combustion chamber through the ignition chamber fuel nozzle, and is mixed with the oxidant in the ignition chamber central combustion chamber to form a combustible mixture;

[0026] The combustible mixture is ignited by the spark emitted by the electric nozzle to form an oxygen-rich flame, which is supplemented by the discharged cooled fuel at the outlet of the ignition chamber to increase the ignition energy of the torch. The torch is sprayed into the inner cavity of the thrust chamber to ignite the thrust chamber.

[0027] The beneficial effects of the present invention compared with the prior art are:

[0028] (1) The torch-type electric igniter structure of the present invention is integrated in the injector, and the ignition medium is directly derived from the fuel chamber and the oxidant chamber of the injector. No ignition pipeline and ignition valve are required, which greatly simplifies the ignition system and reduces the weight of the system;

[0029] (2) The ignition chamber of the present invention is produced by 3D printing, which directly prints the ignition chamber nozzle, ignition chamber fuel flow channel and exhaust cooling structure in an integrated manner. There is only one part. Compared with the multi-part welding scheme in the traditional torch-type electric igniter scheme, the ignition chamber structure is simplified; after the ignition chamber is produced, a gas-liquid flow test is carried out separately for inspection and screening, which is beneficial to ensure the mass production of igniter products and control the production quality of igniters.

[0030] (3) The igniter fuel of the present invention is divided into two paths, one path enters the center of the ignition chamber through the igniter fuel nozzle for combustion, and the other path enters the igniter discharge cooling annular gap through the radial hole to cool the inner wall of the ignition chamber. The flow rates of the two paths are independently controlled by the nozzle size and the annular gap size, which is conducive to the precise control of the igniter operating parameters;

[0031] (4) The igniter of the present invention adopts central oxygen-rich combustion. Since the flammable boundary of the fuel in the oxygen-rich range is wider than that in the rich combustion range, the igniter adopts central oxygen-rich combustion to improve the adaptability of the igniter to changes in ignition conditions, allowing the igniter inlet conditions to vary within a certain range, thereby ensuring the ignition reliability of the igniter.

[0032] (5) The igniter of the present invention adopts a DC mutual impact nozzle, which is beneficial to the atomization and mixing of the oxidant and the fuel.

[0033] (6) The igniter of the present invention adopts exhaust cooling, which improves the structural thermal protection capability of the igniter under ignition and main stage conditions. The indentation of the outlet area promotes the supplementary combustion of oxygen-rich fuel gas and exhaust cooling fuel, thereby improving the ignition energy. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 The igniter structure of the present invention is cut away Figure 1 ;

[0035] Figure 2 The igniter structure of the present invention is cut away Figure 2

[0036] Figure 3 for Figure 1 Cross-section along the middle line BB and CC.

[0037] Among them: 1. Electric nozzle; 2. Sealing ring; 3. Ignition chamber; 4. Three bottoms; 5. Ignition chamber fuel nozzle; 6. Ignition chamber central combustion chamber; 7. Ignition chamber fuel nozzle flow channel; 8. Injector fuel chamber; 9. Ignition chamber fuel nozzle inlet; 10. Two bottoms; 11. Ignition chamber discharge cooling inlet; 12. Injector fuel chamber; 13. Ignition chamber discharge cooling ring seam; 14. One bottom; 15. Nut; 16. Indentation area; 17. Ignition chamber oxygen nozzle. DETAILED DESCRIPTION

[0038] The specific embodiments of the present invention are further described in detail below with reference to the accompanying drawings.

[0039] The problem that the present invention aims to solve is to simplify the ignition system and reduce the weight. Based on the above background, the present invention designs a torch-type electric igniter structure integrated on the thrust chamber injector, that is, the torch igniter and the injector are integrated and designed, the ignition medium is directly derived from the oxidant chamber and the fuel chamber of the thrust chamber injector, the ignition valve and the ignition pipeline are eliminated, the ignition system is simplified and the weight is reduced.

[0040] like Figure 1 and Figure 2 As shown, the torch igniter integrated in the injector designed by the present invention includes an ignition chamber 3, an electric nozzle 1, a sealing ring 2 and a nut 15.

[0041] The nozzle 1 is installed at the center of the upper end of the ignition chamber 3 through a thread and is sealed by a sealing ring 2. The ignition chamber 3 is fixed to the first bottom 14 of the thrust chamber injector by a nut 15. The ignition chamber 3 is connected to the second bottom 10 and the third bottom 4 of the thrust chamber injector by welding.

[0042] The injector fuel chamber 12 is between the first bottom 14 and the second bottom 10, and the injector oxidant chamber 8 is between the second bottom 10 and the third bottom 4;

[0043] The ignition chamber 3 is provided with an ignition chamber fuel nozzle 5, an ignition chamber fuel nozzle flow channel 7, an ignition chamber fuel nozzle inlet 9, an ignition chamber discharge cooling inlet 11, an ignition chamber discharge cooling annular gap 13 and an ignition chamber oxidant nozzle 17, and the center of the ignition chamber 3 is provided with an ignition chamber central combustion chamber 6 along the axial direction;

[0044] The fuel is sprayed from the injector fuel chamber 12 through the ignition chamber fuel nozzle inlet 9, the ignition chamber fuel nozzle flow channel 7, and the ignition chamber fuel nozzle 5 into the ignition chamber central combustion chamber 6; the oxidant is sprayed along the injector oxidant chamber 8 and the ignition chamber oxidant nozzle 17 into the ignition chamber central combustion chamber 6, such as Figure 2 As shown; the oxidant and fuel are atomized and mixed in the combustion chamber 6 at the center of the ignition chamber, and are ignited by the electric nozzle 1 above to form a high-temperature oxygen-rich combustion gas that is discharged downstream of the ignition chamber;

[0045] The fuel flows from the injector fuel cavity 12, passes through the radially arranged ignition chamber emission cooling inlet 11 and enters the ignition chamber emission cooling annular gap 13 to cool the inner wall of the ignition chamber. This part of the fuel meets the high-temperature oxygen-rich combustion gas in the center of the ignition chamber in the ignition chamber outlet indentation area 16, and is supplementally burned to increase the ignition energy.

[0046] like Figure 3 As shown, the ignition chamber emission cooling inlet 11 is provided with n1 layers (generally 1 to 3), and each layer has n2 radial holes (i.e., the ignition chamber emission cooling inlet 11) (generally 4 to 8). The radial holes between the layers form an angle of 360 / n1 / n2 degrees, and the total area of ​​the radial holes is required to be not less than twice the area of ​​the cooling annular gap.

[0047] The total area of ​​the ignition chamber discharge cooling inlet 11 refers to the sum of the cross-sectional areas of all the ignition chamber discharge cooling inlets 11; the cooling annular gap area refers to the cross-sectional area of ​​the cooling annular gap.

[0048] The ignition chamber fuel nozzle 5 and the ignition chamber oxidant nozzle 17 are both straight-flow nozzles.

[0049] There are two ignition chamber fuel nozzles 5 and two oxidant nozzles 17, and the number of nozzles can be increased as needed. The plane formed by the ignition chamber fuel nozzles 5 and the plane formed by the ignition chamber oxidant nozzles 17 are perpendicular to each other. The angle between the two fuel nozzles is A, and the distance between the intersection of the fuel nozzles and the end face of the nozzle is d1; the angle between the two oxidant nozzles is B, and the distance between the intersection of the oxidant nozzles and the end face of the nozzle is d2.

[0050] The angle A ranges from 90° to 150°.

[0051] The value range of angle B is 90°~150°.

[0052] And: A≤B≤A+20°, 0.3D≤d1=d2≤D.

[0053] The length L of the ignition chamber indentation area will affect the afterburning and thermal protection effects, and the value range of L is 0.5D≤L≤1.5D.

[0054] Due to the above design, after the oxidant and the fuel are injected into the central fuel cavity 6 of the ignition chamber, they collide with each other at a point in space and can be mixed more evenly.

[0055] The nut 15 adopts a thin nut and a fine pitch thread scheme, and is prevented from loosening by means of gluing, adding a spring washer or an elastic retaining ring, etc.

[0056] After the ignition chamber 3 is produced by 3D printing, only the assembly size is machined, and then the gas-liquid flow test is carried out on the ignition chamber oxidant path, fuel nozzle path, and fuel discharge cooling path respectively to check the flow characteristics of the ignition chamber product nozzle and cooling annular seam to ensure the consistency of the ignition chamber product.

[0057] Working process:

[0058] When the thrust chamber is ignited and started, first, the thrust chamber oxidizer valve opens, and the oxidizer flows into the injector oxidizer chamber and into the central combustion chamber of the ignition chamber through the ignition chamber oxygen nozzle; then the ignition nozzle starts to energize and ignite, and then the thrust chamber fuel valve opens, and the fuel enters the injector fuel chamber and into the central combustion chamber of the ignition chamber through the ignition chamber fuel nozzle, and mixes with the oxidizer in the central combustion chamber of the ignition chamber to form a combustible mixture, which is ignited by the spark emitted by the nozzle to form an oxygen-rich flame, and then supplements with the discharged cooled fuel at the ignition chamber outlet to increase the ignition energy of the torch. The torch is sprayed into the inner cavity of the thrust chamber to ignite the thrust chamber.

[0059] Example:

[0060] The torch-type electric igniter provided in this embodiment is composed of an ignition chamber, an ignition nozzle and a sealing ring. The ignition chamber mainly includes a fuel and oxidant nozzle and a combustion chamber, which are integrally formed by 3D printing to realize the distribution of ignition medium, torch combustion and other functions. After the ignition chamber is processed, an independent gas-liquid flow screening inspection is carried out, and then it is welded to the second and third bottoms of the injector, and connected to the first bottom with a nut to become a part of the injector, which not only assumes the ignition function of the igniter, but also assumes the function of the igniter in the center of the traditional injector. This igniter solution has the characteristics of simple system and light weight, and can adapt to the unlimited number of starting and ignition of the thrust chamber of the liquid rocket engine.

[0061] The igniter and ignition chamber share the propellant supply main line, main valve and blow-off valve, etc. The igniter and ignition chamber ignite at the same time, and there is no need to set up separate ignition valves and ignition lines. The ignition system is greatly simplified and the weight is greatly reduced. According to the engine starting and main stage working conditions, the igniter nozzle size and cooling ring seam size are reasonably adjusted to ensure the mixing ratio of the igniter under ignition and main stage working conditions.

[0062] The ignition chamber adopts an oxygen-enriched combustion and exhaust cooling structure. The oxidant comes from the injector oxidant chamber, and the fuel comes from the injector fuel chamber. The nozzle flow of the ignition chamber is controlled by the nozzle hole size, and the exhaust cooling flow of the ignition chamber is controlled by the cooling ring gap size. The fuel nozzle and the oxidant nozzle in the ignition chamber are both direct-flow nozzles. The planes of the oxidant and fuel nozzles are perpendicular to each other. The oxidant nozzle and the fuel nozzle collide with each other at one point in space, which is conducive to atomization and mixing. Oxygen-enriched combustion is adopted in the center of the ignition chamber, which is conducive to improving ignition reliability and adaptability to working conditions.

[0063] The ignition chamber exhaust cooling fuel enters the cooling ring gap through the radial hole (ignition chamber exhaust cooling inlet 11) on the igniter to exhaust and cool the inner wall of the ignition chamber, thereby ensuring the thermal protection performance of the ignition chamber under ignition conditions and engine main stage conditions.

[0064] The oxygen-rich combustion gas in the center of the ignition chamber is supplemented with the exhaust cooling fuel in the igniter retracted area and outlet to increase the ignition energy. The center mixing ratio of the ignition chamber is oxygen-rich (the center mixing ratio is generally 15-25), and the total mixing ratio is fuel-rich (the total mixing ratio is generally 1-2). When the main stage of the engine is working, the igniter works as an independent small combustion chamber all the time.

[0065] Parts of the present invention that are not described in detail belong to common knowledge among those skilled in the art.

Claims

1. A torch-type electric igniter integrated on the thrust chamber injector, characterized in that include: It comprises an ignition chamber (3), an electric nozzle (1), a sealing ring (2) and a nut (15); The nozzle (1) is installed at the center of the upper end of the ignition chamber (3) through a thread and is sealed by a sealing ring (2). The ignition chamber (3) and a first bottom (14) of the thrust chamber injector are fixed by a nut (15). The ignition chamber (3) and the second bottom (10) and the third bottom (4) of the thrust chamber injector are welded and connected. The injector fuel chamber (12) is between the first bottom (14) and the second bottom (10), and the injector oxidant chamber (8) is between the second bottom (10) and the third bottom (4); An ignition chamber fuel nozzle (5), an ignition chamber fuel nozzle flow channel (7), an ignition chamber fuel nozzle inlet (9), an ignition chamber exhaust cooling inlet (11), an ignition chamber exhaust cooling annular gap (13) and an ignition chamber oxidant nozzle (17) are arranged in the ignition chamber (3), and an ignition chamber central combustion chamber (6) is arranged in the center of the ignition chamber (3) along the axial direction; The fuel is sprayed from the injector fuel chamber (12) through the ignition chamber fuel nozzle inlet (9), the ignition chamber fuel nozzle flow channel (7), and the ignition chamber fuel nozzle (5) into the ignition chamber central combustion chamber (6); the oxidant is sprayed along the injector oxidant chamber (8) and the ignition chamber oxidant nozzle (17) into the ignition chamber central combustion chamber (6); the oxidant and the fuel are atomized and mixed in the ignition chamber central combustion chamber (6), and are ignited by the upper electric nozzle (1) to form a high-temperature oxygen-rich combustion gas which is discharged downstream of the ignition chamber; The fuel enters the ignition chamber discharge cooling annular gap (13) from the injector fuel cavity (12) through the radially arranged ignition chamber discharge cooling inlet (11) to cool the inner wall of the ignition chamber. This part of the fuel meets the high-temperature oxygen-rich combustion gas at the center of the ignition chamber in the ignition chamber outlet indentation area (16) to perform supplementary combustion, thereby increasing the ignition energy.

2. The torch-type electric igniter integrated on the thrust chamber injector according to claim 1, characterized in that: The ignition chamber discharge cooling inlets (11) are arranged in n1 layers, the number of the ignition chamber discharge cooling inlets (11) in each layer is n2, and the ignition chamber discharge cooling inlets (11) between the layers form an angle of 360 / n1 / n2 degrees.

3. The torch-type electric igniter integrated on the thrust chamber injector according to claim 2, characterized in that: The total area of ​​the ignition chamber discharge cooling inlet (11) is not less than twice the area of ​​the cooling annular gap; The total area of ​​the ignition chamber discharge cooling inlet (11) refers to the sum of the cross-sectional areas of all the ignition chamber discharge cooling inlets (11); the cooling annular gap area refers to the cross-sectional area of ​​the cooling annular gap.

4. The torch-type electric igniter integrated on the thrust chamber injector according to claim 2, characterized in that: The ignition chamber fuel nozzle (5) and the ignition chamber oxidant nozzle (17) are both direct current nozzles. There are two ignition chamber fuel nozzles (5) and two oxidant nozzles (17). The plane formed by the ignition chamber fuel nozzles (5) and the plane formed by the ignition chamber oxidant nozzles (17) are perpendicular to each other. The angle between the two ignition chamber fuel nozzles (5) is A, and the distance between the intersection of the fuel nozzles and the end face of the nozzle is d1; the angle between the two oxidant nozzles (17) is B, and the distance between the intersection of the oxidant nozzles and the end face of the nozzle is d2.

5. The torch-type electric igniter integrated on the thrust chamber injector according to claim 4, characterized in that: The angle A has a value range of 90° to 150°, the angle B has a value range of 90° to 150°, and A≤B≤A+20°, 0.3D≤d1=d2≤D, and D is the diameter of the fuel cavity (6) at the center of the ignition chamber.

6. The torch-type electric igniter integrated on the thrust chamber injector according to claim 5, characterized in that: After the oxidant and the fuel are injected into the central fuel cavity (6) of the ignition chamber, they collide with each other at a point in space.

7. The torch-type electric igniter integrated on the thrust chamber injector according to claim 1, characterized in that: The length L of the ignition chamber outlet indentation area (16) has a value range of 0.5D≤L≤1.5D.

8. The torch-type electric igniter integrated on the thrust chamber injector according to claim 1, characterized in that: The ignition chamber (3) is integrally formed by 3D printing to achieve the distribution of the ignition medium and the combustion of the torch.

9. The torch-type electric igniter integrated on the thrust chamber injector according to claim 1, characterized in that: After the ignition chamber (3) is processed, an independent gas-liquid flow screening inspection is carried out, and then it is welded to the second and third bottoms of the injector, and connected to the first bottom with a nut to become a part of the injector, which is used for ignition of the igniter and serves as a spark pipe in the center of the injector.

10. The torch-type electric igniter integrated on the thrust chamber injector according to claim 1, characterized in that: The ignition chamber fuel nozzle flow is controlled by the ignition chamber fuel nozzle (5) hole size, and the ignition chamber exhaust cooling flow is controlled by the cooling ring gap size.

11. The torch-type electric igniter integrated on the thrust chamber injector according to claim 1, characterized in that: When the thrust chamber is ignited and started, The thrust chamber oxidizer valve is opened first, and the oxidizer flows into the injector oxidizer chamber and into the central combustion chamber of the ignition chamber through the ignition chamber oxygen nozzle; The ignition nozzle starts to energize and ignite; The thrust chamber fuel valve is opened, and the fuel enters the injector fuel chamber and the ignition chamber central combustion chamber through the ignition chamber fuel nozzle, and is mixed with the oxidant in the ignition chamber central combustion chamber to form a combustible mixture; The combustible mixture is ignited by the spark emitted by the electric nozzle to form an oxygen-rich flame, which is supplemented by the discharged cooled fuel at the outlet of the ignition chamber to increase the ignition energy of the torch. The torch is sprayed into the inner cavity of the thrust chamber to ignite the thrust chamber.

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