Dual-swirl torch igniter and rocket engine

Abstract

The present application relates to the technical field of liquid rocket engine, in particular to a double-swirl torch igniter and a rocket engine. The double-swirl torch igniter comprises a head cavity shell, a first side peripheral wall and a second side peripheral wall are arranged along the radial direction, an oxidizer collection cavity is formed between the first side peripheral wall and the second side peripheral wall, an oxidizer swirl channel is formed between the first side peripheral wall and the outer side peripheral wall of a high-energy igniter, an oxidizer swirl injection hole is arranged on the first side peripheral wall, an inner wall of a combustion chamber shell surrounds to form an ignition combustion chamber, the ignition combustion chamber is communicated with the oxidizer swirl channel, an inner wall of a fuel collection cavity shell is spaced from an outer wall of the combustion chamber shell to form a fuel collection cavity, and a fuel injection hole is arranged on the combustion chamber shell. The double-swirl torch igniter provided by the present application has small ignition flow, high heat flux density and high energy, and can realize reliable ignition of the engine thrust chamber and the pre-combustion chamber under small flow conditions.

Description

Technical Field

[0001] The invention relates to the technical field of liquid rocket engines, and in particular to a double-swirl torch igniter and a rocket engine. Background Art

[0002] With the development of commercial space technology, the need for rocket recovery is increasing to reduce launch costs. The rocket recovery process requires the rocket engine to be able to restart multiple times, so the ability to ignite multiple times during a single mission is a key technology.

[0003] Among existing mature engine ignition technologies, gunpowder igniters are single-use only. Parallel connections can be used for multiple ignitions, but these occupy a large space, limit multiple ignitions, and pose the risk of clogging the ignition channel. Self-igniting igniters are reusable and effective, but require additional ignition agent storage equipment, which is typically toxic and presents safety risks. Flare igniters, on the other hand, can achieve multiple ignitions and use the same ignition agent as rocket propellant, reducing system complexity and offering certain application advantages.

[0004] In order to reduce the combustion temperature inside the igniter, existing torch igniters generally use oxygen-rich or fuel-rich combustion. The ignition propellant mixture ratio deviates from the theoretical combustion mixture ratio, the fuel / oxidizer utilization is insufficient, the ignition propellant flow rate is large, and the ignition system burden is increased. At the same time, the ignition propellant is basically diffusion combustion, the mixing uniformity is poor, and local hot spots are prone to occur during the combustion process. During use, the igniter is at risk of ablation. Some types of torch igniters use exhaust cooling to reduce the igniter wall temperature and increase the igniter outlet combustion temperature. However, this method requires additional ignition agent supply pipelines, resulting in a complex igniter structure and a large volume, which is not conducive to flexible igniter layout.

[0005] Therefore, the existing torch igniter has a large ignition propellant flow rate but poor mixing uniformity, and is prone to the risk of igniter ablation due to the presence of local hot spots during the combustion process. There is an urgent need for a torch igniter that can reduce the ignition flow rate, improve the mixing uniformity of the ignition propellant, and avoid the generation of local hot spots during the combustion process that may cause igniter ablation. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to overcome the defects of the existing torch igniter in the prior art that the ignition propellant flow rate is large but the mixing uniformity is poor, and the risk of igniter ablation is easily caused by the presence of local hot spots during the combustion process, thereby providing a double-swirl torch igniter with a small ignition flow rate, high ignition propellant mixing uniformity, and the ability to avoid igniter ablation due to the generation of local hot spots during the combustion process.

[0007] In order to solve the above technical problems, the present invention provides a dual swirl torch igniter, comprising:

[0008] A head cavity housing, one axial end of which is connected to the high-energy igniter, and the other end of which is connected to the combustion chamber housing and / or the fuel collection chamber housing;

[0009] The head cavity housing includes a first side circumferential wall and a second side circumferential wall spaced apart in a radial direction, an oxidant collecting chamber is formed between the first side circumferential wall and the second side circumferential wall; an oxidant swirl channel is formed between the first side circumferential wall and the outer circumferential wall of the high-energy igniter; an oxidant swirl injection hole is formed on the first side circumferential wall, which is suitable for connecting the oxidant collecting chamber with the oxidant swirl channel;

[0010] The inner wall of the combustion chamber housing surrounds and forms an ignition combustion chamber, and the ignition combustion chamber is communicated with the oxidant swirl channel;

[0011] The fuel collecting chamber shell circumferentially surrounds the combustion chamber shell, and a fuel collecting chamber is formed between the inner wall of the fuel collecting chamber shell and the outer wall of the combustion chamber shell; a fuel injection hole is opened on the combustion chamber shell, which is suitable for connecting the ignition combustion chamber with the fuel collecting chamber.

[0012] Optionally, the central axis of the fuel injection hole is set at an angle to the radial line of the combustion chamber shell, and the diameter of the inscribed circle of the regular polygon formed by the intersection of the central axis of the fuel injection hole is d, and d satisfies d=1 / 4·D, where D is the diameter of the ignition combustion chamber.

[0013] Optionally, the central axis of the oxidant swirl injection hole is set at an angle to the radial line of the first side wall; the swirl direction of the oxidant swirl injection hole is the same as the swirl direction of the fuel injection hole.

[0014] Optionally, in the working state, the outlet plane of the oxidant swirl channel exceeds the discharge end face of the high-energy igniter, and the distance between the outlet plane of the oxidant swirl channel and the discharge end face of the high-energy igniter is L, and L satisfies 2mm≤L≤3mm.

[0015] Optionally, a cylindrical wall is provided between the first side circumferential wall and the second side circumferential wall, defining the wall surface at one axial end of the oxidant collecting chamber as the first wall, and the wall surface at the other end as the second wall. Then, one axial end of the cylindrical wall is connected to the first wall, and the other end is spaced apart from the second wall. The cylindrical wall is suitable for dividing the oxidant collecting chamber into a U-shaped cross-section channel.

[0016] Optionally, the second side circumferential wall is radially arranged on a side of the first side circumferential wall away from the high-energy igniter; an oxidant inlet pipe is radially connected to the second side circumferential wall, and the oxidant inlet pipe is communicated with the oxidant collecting chamber.

[0017] Optionally, the combustion chamber housing includes:

[0018] A first straight cylindrical section is connected to one axial end of the head cavity housing; a plurality of fuel injection holes are formed on a side circumferential wall of the first straight cylindrical section close to the head cavity housing in the axial direction; the central axes of the fuel injection holes are perpendicular to the central axis of the first straight cylindrical section;

[0019] a second straight section connected to the first straight section via the first conical section; the diameter of the second straight section is smaller than that of the first straight section, and the second straight section is suitable for collecting and accelerating high-temperature combustion gas;

[0020] The cone angle of the first cone section is α, and the value range of α is 45°≤α≤70°.

[0021] Optionally, the fuel assembly chamber housing includes:

[0022] a third straight section connected to one axial end of the head cavity housing, the third straight section being spaced apart from the first straight section; a fuel inlet pipe being radially connected to the third straight section, the fuel inlet pipe being in communication with the fuel collecting chamber;

[0023] The mounting joint is connected to the third straight section through the second conical section; the mounting joint is spaced apart from the second straight section, and an injection channel is formed between the inner circumferential wall of the mounting joint and the outer circumferential wall of the second straight section.

[0024] Optionally, a cooling sleeve is connected to one end of the mounting joint axially away from the second cone section;

[0025] The outlet plane of the cooling jacket is higher than the outlet plane of the second straight section. The distance between the outlet plane of the cooling jacket and the outlet plane of the second straight section is H, and H satisfies 1mm≤H≤2mm.

[0026] The present invention also provides a rocket engine, comprising:

[0027] The rocket engine body, and the dual swirl torch igniter as described above.

[0028] The technical solution of the present invention has the following advantages:

[0029] 1. The dual-swirl torch igniter provided by the present invention achieves a total mixing ratio of the ignition agent close to the theoretical combustion mixing ratio through a primary oxygen-enriched combustion plus a secondary supplementary combustion. Under the condition of providing the same energy, the ignition agent flow rate is lower, the combustion torch temperature is high, the flame volume is small, and the operating condition changes during the starting process of the thrust chamber or pre-combustion chamber have little effect on the ignition effect of the igniter. At the same time, during operation, the oxidant is uniformly distributed through the U-shaped cross-section channel, the oxidant swirl effect of the oxidant swirl injection hole and the oxidant swirl channel, and the fuel swirl effect of the fuel injection hole, and the oxidant and fuel collide with each other in the ignition combustion chamber to form a central swirl, thereby greatly improving the mixing rate and uniformity of the oxidant and fuel, and avoiding the generation of local hot spots during the combustion process to cause igniter ablation.

[0030] 2. In the dual-swirl torch igniter provided by the present invention, the central axes of several of the fuel injection holes are arranged at an angle to the radial line of the combustion chamber shell, and the diameter of the inscribed circle of the regular polygon formed by the intersection of the central axes of several of the fuel injection holes is d, and d satisfies d=1 / 4·D, wherein D is the diameter of the ignition combustion chamber, so that the fuel injection holes form an ideal swirl direction in the ignition combustion chamber, thereby improving the success rate and reliability of ignition.

[0031] 3. The double swirl torch igniter provided by the present invention has a swirl direction of the oxidant swirl injection hole that is the same as the swirl direction of the fuel injection hole, thereby forming a double swirl structure. The momentum difference between the fuel and the oxidant is utilized to make the fuel form a swirl after passing through the oxidant. During the fuel passage, the fuel entrains the oxidant and mixes with the oxidant in advance, which ensures the mixing effect while increasing the flow field stability. The air film generated by the oxidant swirl protects the high-energy igniter and the combustion chamber wall. At the same time, the cold fuel in the fuel collecting cavity cools the outer wall of the combustion chamber shell, thereby further reducing the temperature of the combustion chamber shell.

[0032] 4. The dual-swirl torch igniter provided by the present invention has an outlet plane of the oxidant swirl channel exceeding the discharge end face of the high-energy igniter, and a distance L between the outlet plane of the oxidant swirl channel and the discharge end face of the high-energy igniter satisfies 2mm≤L≤3mm, thereby forming the recirculation zone between the outlet plane of the oxidant swirl channel and the discharge end face of the high-energy igniter to ensure combustion stability.

[0033] 5. In the double-swirl torch igniter provided by the present invention, a cylindrical wall is arranged between the first side circumferential wall and the second side circumferential wall, one axial end of the cylindrical wall is connected to the first wall, and the other end is spaced apart from the second wall. By setting the cylindrical wall, the oxidant collecting cavity is divided into a U-shaped cross-section channel. Through the flow equalization effect of the U-shaped cross-section channel, the oxidant flow is made more uniform, which is conducive to the full mixing of the oxidant and the fuel, and thus makes the combustion more complete.

[0034] 6. In the double-swirl torch igniter provided by the present invention, the diameter of the second straight section is smaller than the diameter of the first straight section, and the second straight section is suitable for collecting and accelerating high-temperature combustion gas; the cone angle of the first conical section is α, and the value range of α is 45°≤α≤70°. Under working conditions, the fuel and oxidant in the ignition combustion chamber swirl together and burn in the same direction, and the generated high-temperature combustion gas is accelerated by the convergent section formed by the first conical section, thereby enhancing the fluidity of the medium and helping to improve combustion efficiency.

[0035] 7. In the double-swirl torch igniter provided by the present invention, the outlet plane of the cooling sleeve is higher than the outlet plane of the second straight-cylinder section, and the distance between the outlet plane of the cooling sleeve and the outlet plane of the second straight-cylinder section is H, and H satisfies 1mm≤H≤2mm, thereby increasing the mixing rate of the high-temperature combustion gas discharged from the ignition combustion chamber and the fuel flowing out of the fuel collecting chamber, thereby improving the combustion efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0037] Figure 1 This is a schematic diagram of the working principle of the double swirl torch igniter of the present invention;

[0038] Figure 2 It is a cross-sectional schematic diagram of the double swirl torch igniter of the present invention;

[0039] Figure 3 Schematic cross-sectional view of the combustion chamber shell of the dual swirl torch igniter of the present invention;

[0040] Figure 4 This is a schematic diagram of the structure of the dual-swirl torch igniter of the present invention after the combustion chamber shell and the fuel collection chamber shell are hidden;

[0041] Figure 5 for Figure 4Dimensional diagram at P in the middle;

[0042] Figure 6 This is a schematic diagram of the structure of the double swirl torch igniter of the present invention after the head cavity shell and the high-energy igniter are hidden;

[0043] Figure 7 for Figure 6 Dimensional diagram at Q in the middle.

[0044] Description of reference numerals:

[0045] 1. Head cavity housing; 10. Oxidant collecting chamber; 11. First side peripheral wall; 110. Oxidant swirl injection hole; 12. Second side peripheral wall; 13. Oxidant swirl channel; 14. Cylindrical wall; 15. Oxidant inlet pipe; 16. Mounting seat; 17. Outer boss; 18. Inner boss;

[0046] 2. Combustion chamber shell; 20. Ignition combustion chamber; 21. First straight section; 210. Fuel injection hole; 22. First conical section; 23. Second straight section;

[0047] 3. Fuel manifold housing; 30. Fuel manifold; 31. Third straight section; 32. Second conical section; 33. Mounting joint; 34. Fuel inlet pipe; 35. Injection channel; 36. Cooling jacket;

[0048] 4. High-energy igniter. DETAILED DESCRIPTION

[0049] The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0050] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0051] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0052] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0053] Example 1

[0054] Combine Figure 1-Figure 7 As shown, the dual swirl torch igniter provided in this embodiment includes:

[0055] The head cavity housing 1 has one axial end connected to the high-energy igniter 4 and the other end connected to the combustion chamber housing 2 and / or the fuel collection chamber housing 3;

[0056] The head cavity housing 1 includes a first side circumferential wall 11 and a second side circumferential wall 12 spaced apart in a radial direction, wherein an oxidant collecting chamber 10 is formed between the first side circumferential wall 11 and the second side circumferential wall 12; an oxidant swirl channel 13 is formed between the first side circumferential wall 11 and the outer circumferential wall of the high-energy igniter 4; an oxidant swirl injection hole 110 is formed on the first side circumferential wall 11, which is suitable for connecting the oxidant collecting chamber 10 with the oxidant swirl channel 13;

[0057] The inner wall of the combustion chamber housing 2 is surrounded to form an ignition combustion chamber 20, and the ignition combustion chamber 20 is connected to the oxidant swirl channel 13;

[0058] The fuel collecting chamber shell 3 circumferentially surrounds the combustion chamber shell 2, and a fuel collecting chamber 30 is formed between the inner wall of the fuel collecting chamber shell 3 and the outer wall of the combustion chamber shell 2; a fuel injection hole 210 is opened on the combustion chamber shell 2, which is suitable for connecting the ignition combustion chamber 20 with the fuel collecting chamber 30.

[0059] Optionally, a mounting seat 16 is provided at one end of the head cavity housing 1 axially close to the high-energy igniter 4 , and the mounting seat 16 is suitable for being threadedly connected to the high-energy igniter 4 .

[0060] See Figure 4As shown, in this embodiment, an outer boss 17 and an inner boss 18 are provided at one end of the head cavity shell 1 axially away from the high-energy igniter 4, and the outer boss 17 is suitable for positioning the fuel collecting chamber shell 3, and the inner boss 18 is suitable for positioning the combustion chamber shell 2.

[0061] Please note that, see Figure 1 As shown, in the double swirl torch igniter provided in this embodiment, the oxidant is supplied to the oxidant collecting chamber 10 through the oxidant inlet pipe 15, and evenly enters the oxidant swirl injection hole 110 through the uniform flow effect of the U-shaped cross-section channel formed by the cylindrical wall 14, and then enters the oxidant swirl channel 13 through the swirl effect of the oxidant swirl injection hole 110. Under the action of the swirl, the oxidant enters the ignition combustion chamber 20 along the oxidant swirl channel 13 for mixing and combustion. In this process, the air film generated by the oxidant swirl protects the high-energy igniter 4 and the wall surface of the combustion chamber shell 2; the fuel passes through The fuel inlet pipe 34 enters the fuel collecting chamber 30, and then is divided into two flow rates of different sizes in the fuel collecting chamber 30, wherein a small portion of the flow enters the ignition combustion chamber 20 through the fuel injection hole 210 for oxygen-enriched combustion. The fuel of this small portion of the flow burns in the ignition combustion chamber 20 to form high-temperature combustion gas, while the majority of the flow cools the ignition combustion chamber 20 in the fuel collecting chamber 30 and is ejected through the injection channel 35. After being ejected through the injection channel 35, the fuel of this majority of the flow mixes with the high-temperature combustion gas generated in the ignition combustion chamber 20 and enters the thrust chamber or pre-combustion chamber for secondary combustion. Before the oxidizer enters the ignition combustion chamber 20, a small reflux zone will be formed on the discharge end face of the high-energy igniter 4, and then the oxidizer will swirl into the ignition combustion chamber 20, and under the action of the swirl, it will flow along the inner wall of the combustion chamber shell 2 to the downstream of the ignition combustion chamber 20; the fuel will be injected into the ignition combustion chamber 20 at high speed through the fuel injection hole 210 and pass through the oxidizer layer, and will collide with each other in the ignition combustion chamber 20 to form a central vortex. In the process of the fuel passing through the oxidizer layer, the fuel will entrain the oxidizer and mix with the oxidizer in advance. The fuel inside the ignition combustion chamber 20 and the oxidant outside swirl in the same direction, mixing and burning. The resulting high-temperature combustion gas is accelerated by the convergent section formed by the downstream first conical section 22 and then discharged through the second straight section 23. Due to the excess air in the ignition combustion chamber 20, an air film forms on the inner wall of the combustion chamber shell 2, preventing high-temperature combustion gas ablation. At the same time, the cold fuel in the fuel plenum 30 cools the outer wall of the combustion chamber shell 2, further reducing the temperature of the combustion chamber shell 2. Ultimately, the high-temperature combustion gas discharged from the ignition combustion chamber 20 and the fuel in the fuel plenum 30 mix at the igniter outlet and enter the thrust chamber or pre-combustion chamber for secondary combustion.

[0062] It should be noted that, in order to reduce the combustion temperature, the torch igniter before the improvement generally uses oxygen-rich or fuel-rich combustion, the ignition propellant mixture ratio deviates from the theoretical combustion mixture ratio, the fuel / oxidizer is not fully utilized, the ignition propellant flow is large, the combustion is not complete, and the ignition agent energy is not fully utilized; at the same time, the ignition propellant is basically diffusion combustion, the mixing uniformity is poor, and local hot spots are prone to occur during the combustion process. During use, the igniter is at risk of ablation. The dual-swirl torch igniter provided by the present invention achieves a total mixing ratio of the ignition agent close to the theoretical combustion mixing ratio through primary oxygen-enriched combustion plus secondary supplementary combustion. When providing the same energy, the ignition agent flow rate is lower, the combustion torch temperature is high, the flame volume is small, and the operating condition changes during the starting process of the thrust chamber or pre-combustion chamber have little effect on the ignition effect of the igniter. At the same time, the dual-swirl torch igniter provided by the present invention, during operation, through the uniform flow effect of the U-shaped cross-section channel on the oxidant, the swirl effect of the oxidant swirl injection hole 110 and the oxidant swirl channel 13 on the oxidant, and the swirl effect of the fuel injection hole 210 on the fuel, the oxidant and fuel collide with each other in the ignition combustion chamber 20 to form a central swirl, which greatly improves the mixing rate and uniformity of the oxidant and fuel, and avoids the generation of local hot spots during the combustion process and causes igniter ablation.

[0063] Specifically, the central axis of the fuel injection hole 210 is set at an angle to the radial line of the combustion chamber housing 2, and the diameter of the inscribed circle of the regular polygon formed by the intersection of the central axis of the fuel injection hole 210 is d, and d satisfies d=1 / 4·D, where D is the diameter of the ignition combustion chamber 20.

[0064] Optionally, the number of the fuel injection holes 210 is six, and the six fuel injection holes 210 are evenly arranged along the circumference of the combustion chamber housing 2 .

[0065] Please note that, see Figure 3 As shown, the central axes of several of the fuel injection holes 210 are set at an angle to the radial line of the combustion chamber shell 2, and the diameter of the inscribed circle of the regular polygon formed by the intersection of the central axes of several of the fuel injection holes 210 is d, and d satisfies d=1 / 4·D, wherein D is the diameter of the ignition combustion chamber 20, so that the fuel injection holes 210 form an ideal swirl direction in the ignition combustion chamber 20, thereby improving the success rate and reliability of ignition.

[0066] Specifically, the central axis of the oxidant swirl injection hole 110 is set at an angle to the radial line of the first side wall 11 ; the swirl direction of the oxidant swirl injection hole 110 is the same as the swirl direction of the fuel injection hole 210 .

[0067] It should be noted that, in the double swirl torch igniter provided by the present invention, the central axis of the oxidant swirl injection hole 110 is set at an angle to the radial line of the first side wall 11; the swirl direction of the oxidant swirl injection hole 110 is the same as the swirl direction of the fuel injection hole 210, thereby forming a double swirl structure, so as to utilize the momentum difference between the fuel and the oxidant to form a swirl after the fuel passes through the oxidant. During the fuel crossing process, the fuel entrains the oxidant and mixes with the oxidant in advance; the air film generated by the oxidant swirl protects the high-energy igniter and the combustion chamber wall, and at the same time, the cold fuel in the fuel collecting cavity 30 cools the outer wall of the combustion chamber shell 2, thereby further reducing the temperature of the combustion chamber shell 2; compared with the mutual impact structure, the double swirl torch igniter adopts a double swirl structure, which ensures the mixing effect while having higher flow field stability. Compared with the coaxial direct current structure, the double swirl torch igniter adopts a double swirl structure to improve the mixing effect and reduce the mixing time.

[0068] Specifically, in the working state, the outlet plane of the oxidant swirl channel 13 exceeds the discharge end surface of the high-energy igniter 4, and the distance between the outlet plane of the oxidant swirl channel 13 and the discharge end surface of the high-energy igniter 4 is L, and L satisfies 2mm≤L≤3mm.

[0069] Please note that, see Figure 4 and Figure 5 As shown, the outlet plane of the oxidant swirl channel 13 exceeds the discharge end surface of the high-energy igniter 4, and the distance L between the outlet plane of the oxidant swirl channel 13 and the discharge end surface of the high-energy igniter 4 satisfies 2mm≤L≤3mm. Figure 1 As shown, a small recirculation zone is formed on the discharge end face of the high-energy igniter 4 before the oxidant enters the ignition combustion chamber 20, so that the oxidant can swirl into the ignition combustion chamber 20, and the oxidant flows along the inner wall of the combustion chamber shell 2 to the downstream of the ignition combustion chamber 20 under the action of the swirl; the fuel is injected into the ignition combustion chamber 20 at high speed through the fuel injection hole 210 and passes through the oxidant layer, and collides with each other in the ignition combustion chamber 20 to form a central vortex, and part of the fuel in the fuel impact area close to the recirculation zone is mixed with the oxidant in the recirculation zone to form a stable ignition source; the recirculation zone is formed between the outlet plane of the oxidant swirl channel 13 and the discharge end face of the high-energy igniter 4, thereby ensuring combustion stability.

[0070] Specifically, a cylindrical wall 14 is provided between the first side circumferential wall 11 and the second side circumferential wall 12, and the wall surface at one axial end of the oxidant collecting chamber 10 is defined as the first wall, and the wall surface at the other end is defined as the second wall. One axial end of the cylindrical wall 14 is connected to the first wall, and the other end is spaced apart from the second wall. The cylindrical wall 14 is suitable for dividing the oxidant collecting chamber 10 to form a U-shaped cross-section channel.

[0071] Please note that, see Figure 4 As shown, a cylindrical wall 14 is provided between the first side circumferential wall 11 and the second side circumferential wall 12, and the wall surface of one axial end of the oxidant collecting chamber 10 is defined as the first wall, and the wall surface of the other end is defined as the second wall. Then, one axial end of the cylindrical wall 14 is connected to the first wall, and the other end is spaced apart from the second wall. By providing the cylindrical wall 14, the oxidant collecting chamber 10 is separated to form a U-shaped cross-section channel. Through the flow-balancing effect of the U-shaped cross-section channel, the oxidant flow is made more uniform, which is beneficial to the full mixing of the oxidant and the fuel, and thus makes the combustion more complete.

[0072] Specifically, the second side circumferential wall 12 is radially arranged on the side of the first side circumferential wall 11 away from the high-energy igniter 4 ; an oxidant inlet pipe 15 is radially connected to the second side circumferential wall 12 , and the oxidant inlet pipe 15 is communicated with the oxidant collecting chamber 10 .

[0073] Specifically, the combustion chamber housing 2 includes:

[0074] A first straight cylindrical section 21 is connected to one axial end of the head cavity housing 1; a plurality of fuel injection holes 210 are formed on the axial side wall of the first straight cylindrical section 21 close to the head cavity housing 1; the central axes of the fuel injection holes 210 are perpendicular to the central axis of the first straight cylindrical section 21;

[0075] The second straight section 23 is connected to the first straight section 21 through the first conical section 22. The diameter of the second straight section 23 is smaller than that of the first straight section 21. The second straight section 23 is suitable for collecting and accelerating high-temperature combustion gas.

[0076] The cone angle of the first cone section 22 is α, and the value range of α is 45°≤α≤70°.

[0077] Please note that, see Figure 6As shown, the combustion chamber shell 2 includes a first straight cylinder section 21 and a second straight cylinder section 23 and a first conical cylinder section 22 located between the first straight cylinder section 21 and the second straight cylinder section 23; the diameter of the second straight cylinder section 23 is smaller than the diameter of the first straight cylinder section 21, and the second straight cylinder section 23 is suitable for gathering and accelerating high-temperature combustion gas; the cone angle of the first conical cylinder section 22 is α, and the value range of α is 45°≤α≤70°. In the working state, the fuel and oxidant in the ignition combustion chamber 20 swirl together and burn in the same direction, and the generated high-temperature combustion gas is accelerated by the convergent section formed by the first conical cylinder section 22, thereby enhancing the fluidity of the medium and helping to improve the combustion efficiency.

[0078] Optionally, the first straight section 21 is welded to the inner boss 18 of the head cavity housing 1 .

[0079] In this embodiment, a plurality of positioning bosses (not shown in the figure) are evenly distributed circumferentially on the outer peripheral wall of the first straight cylinder section 21. The positioning bosses are suitable for ensuring the coaxiality between the combustion chamber shell 2 and the fuel collection chamber shell 3 during the installation and fitting process.

[0080] Specifically, the fuel collecting chamber housing 3 includes:

[0081] A third straight section 31 is connected to one axial end of the head cavity housing 1 and is spaced apart from the first straight section 21 . A fuel inlet pipe 34 is radially connected to the third straight section 31 , and the fuel inlet pipe 34 is in communication with the fuel collecting chamber 30 .

[0082] The mounting joint 33 is connected to the third straight cylinder section 31 through the second conical cylinder section 32; the mounting joint 33 is spaced apart from the second straight cylinder section 23, and an injection channel 35 is formed between the inner circumferential wall of the mounting joint 33 and the outer circumferential wall of the second straight cylinder section 23.

[0083] Optionally, the third straight section 31 is welded to the outer boss 17 of the head cavity shell 1 .

[0084] Optionally, the injection channel 35 is communicated with the thrust chamber or the pre-combustion chamber.

[0085] Specifically, the end of the mounting joint 33 axially away from the second conical cylinder section 32 is connected to a cooling sleeve 36;

[0086] The outlet plane of the cooling sleeve 36 is higher than the outlet plane of the second straight section 23 . The distance between the outlet plane of the cooling sleeve 36 and the outlet plane of the second straight section 23 is H, and H satisfies 1 mm ≤ H ≤ 2 mm.

[0087] Please note that, see Figure 6 and Figure 7 As shown, the outlet plane of the cooling sleeve 36 is higher than the outlet plane of the second straight section 23, and the distance between the outlet plane of the cooling sleeve 36 and the outlet plane of the second straight section 23 is H, and H satisfies 1mm≤H≤2mm, thereby improving the mixing rate of the high-temperature combustion gas discharged from the ignition combustion chamber 20 and the fuel flowing out of the fuel collecting cavity 30, thereby improving the combustion efficiency.

[0088] Optionally, the cooling sleeve 36 and the mounting joint 33 are coaxially arranged, and the cooling sleeve 36 and the mounting joint 33 are welded together.

[0089] Optionally, the inner diameter of the cooling sleeve 36 is the same as that of the mounting joint 33 .

[0090] The working principle of the dual swirl torch igniter is described below in conjunction with a specific embodiment:

[0091] Oxygen is supplied to the oxidizer manifold 10 through the oxidizer inlet pipe 15. Oxygen flows evenly into the oxidizer swirl injection hole 110 through the uniform flow of the U-shaped cross-section channel formed by the cylindrical wall 14. Then, through the swirl of the oxidizer swirl injection hole 110, it enters the oxidizer swirl channel 13. Under the swirl, the oxygen flows along the oxidizer swirl channel 13 into the ignition combustion chamber 20 for mixing and combustion. Methane flows into the fuel manifold 30 through the fuel inlet pipe 34 and is then divided into two flows within the fuel manifold 30. Ten percent of the methane flows through the fuel injection hole 210 and into the ignition combustion chamber 20 for combustion. The remaining 90 percent of the methane flows cools the ignition combustion chamber 20 within the fuel manifold 30 and is ejected through the injection channel 35. There, it mixes with the high-temperature combustion gas generated within the ignition combustion chamber 20 and enters the thrust chamber or pre-combustion chamber for secondary combustion. Before entering the ignition combustion chamber 20, the gaseous oxygen forms a small recirculation zone at the discharge end face of the high-energy igniter 4. It then swirls into the ignition combustion chamber 20 and, under the action of the swirl, flows along the inner wall of the combustion chamber shell 2 toward the downstream side of the ignition combustion chamber 20. Gaseous methane is injected into the ignition combustion chamber 20 at high speed through the fuel injection hole 210 and passes through the oxidizer layer. Within the ignition combustion chamber 20, they impact each other to form a central swirl. In the recirculation zone formed near the discharge end face of the high-energy igniter 4 in the fuel impact area, some methane mixes with the oxygen in the recirculation zone to form a stable ignition source. The methane inside the ignition combustion chamber 20 and the oxygen outside swirl in the same direction and mix and burn. The resulting high-temperature combustion gas is accelerated through the convergent section formed by the downstream first conical section 22 and then discharged through the second straight section 23. Due to the excess oxygen in the ignition combustion chamber 20, an air film is formed on the inner wall of the combustion chamber shell 2, preventing high-temperature combustion gas from ablation. At the same time, the cold methane in the fuel gas collection chamber 30 cools the outer wall of the combustion chamber shell 2, thereby further reducing the temperature of the combustion chamber shell 2. Ultimately, the high-temperature combustion gas exhausted from the ignition combustion chamber 20 and the methane in the fuel gas collection chamber 30 mix at the igniter outlet and enter the thrust chamber or pre-combustion chamber for secondary combustion. In the above embodiment, the mixing ratio of oxygen and methane in the ignition combustion chamber 20 is γ1, and γ1 satisfies 20≤γ1≤40. The mixing ratio of the entire dual-swirl flare igniter is γ2, and γ2 satisfies 3≤γ2≤3.5. Through numerical simulation analysis, it is found that there is no high-temperature area on the wall surface temperature of the dual-swirl torch igniter of the present invention, the mixing at the igniter outlet is uniform, and the combustion effect is good; through multiple experimental tests, the ignition success rate of the dual-swirl torch igniter of the present invention has been greatly improved compared with before the improvement, and it can ignite stably for a long time without any ablation problems.

[0092] Example 2

[0093] This embodiment provides a rocket engine, comprising:

[0094] The rocket engine body, and the dual swirl torch igniter as described above.

[0095] In this embodiment, the rocket engine is provided with the dual swirl torch igniter, thereby achieving reliable ignition of the engine thrust chamber and / or pre-combustion chamber under low flow conditions.

[0096] Obviously, the above embodiments are merely examples for clarity of explanation and are not intended to limit the implementation methods. Those skilled in the art will readily appreciate that other variations or modifications based on the above descriptions are possible. It is not necessary and impossible to enumerate all implementation methods here. Obvious variations or modifications arising therefrom remain within the scope of protection of the present invention.

Claims

1. A double swirl torch igniter, characterized in that: include: A head cavity housing (1), one axial end of which is connected to a high-energy igniter (4), and the other end of which is connected to a combustion chamber housing (2) and / or a fuel collection chamber housing (3); The head cavity shell (1) comprises a first side circumferential wall (11) and a second side circumferential wall (12) spaced apart in a radial direction, an oxidant collecting chamber (10) is formed between the first side circumferential wall (11) and the second side circumferential wall (12); an oxidant swirl channel (13) is formed between the first side circumferential wall (11) and the outer circumferential wall of the high-energy igniter (4); an oxidant swirl injection hole (110) is provided on the first side circumferential wall (11), which is suitable for connecting the oxidant collecting chamber (10) with the oxidant swirl channel (13); The inner wall of the combustion chamber housing (2) surrounds and forms an ignition combustion chamber (20), and the ignition combustion chamber (20) is communicated with the oxidant swirl channel (13); The fuel collecting chamber housing (3) circumferentially surrounds the combustion chamber housing (2), and a fuel collecting chamber (30) is formed between the inner wall of the fuel collecting chamber housing (3) and the outer wall of the combustion chamber housing (2); a fuel injection hole (210) is provided on the combustion chamber housing (2), suitable for connecting the ignition combustion chamber (20) with the fuel collecting chamber (30); The combustion chamber housing (2) comprises: a first straight cylinder section (21) connected to one axial end of the head cavity housing (1); a second straight cylinder section (23) connected to the first straight cylinder section (21) via a first conical cylinder section (22); The fuel collecting chamber housing (3) comprises: a third straight section (31) connected to one axial end of the head chamber housing (1), the third straight section (31) being spaced apart from the first straight section (21); a fuel inlet pipe (34) being radially connected to the third straight section (31), the fuel inlet pipe (34) being in communication with the fuel collecting chamber (30); a mounting joint (33) being connected to the third straight section (31) via a second conical section (32); the mounting joint (33) being spaced apart from the second straight section (23), and an injection channel (35) being formed between the inner peripheral wall of the mounting joint (33) and the outer peripheral wall of the second straight section (23).

2. The dual swirl torch igniter according to claim 1, characterized in that: The central axis of the fuel injection hole (210) is arranged at an angle to the radial line of the combustion chamber housing (2); the diameter of the inscribed circle of the regular polygon formed by the intersection of the central axis of the fuel injection hole (210) is d, and d satisfies d=1 / 4·D, wherein D is the diameter of the ignition combustion chamber (20).

3. The dual swirl torch igniter according to claim 2, characterized in that: The central axis of the oxidant swirl injection hole (110) is arranged at an angle to the radial line of the first side peripheral wall (11); the swirl direction of the oxidant swirl injection hole (110) is the same as the swirl direction of the fuel injection hole (210).

4. The dual swirl torch igniter according to claim 1, characterized in that: In the working state, the outlet plane of the oxidant swirl channel (13) exceeds the discharge end surface of the high-energy igniter (4), and the distance between the outlet plane of the oxidant swirl channel (13) and the discharge end surface of the high-energy igniter (4) is L, and L satisfies 2mm≤L≤3mm.

5. The dual swirl torch igniter according to claim 1, characterized in that: A cylindrical wall (14) is provided between the first side circumferential wall (11) and the second side circumferential wall (12), defining the wall surface at one axial end of the oxidant collecting chamber (10) as the first wall and the wall surface at the other end as the second wall. One axial end of the cylindrical wall (14) is connected to the first wall, and the other end is spaced apart from the second wall. The cylindrical wall (14) is suitable for dividing the oxidant collecting chamber (10) into a U-shaped cross-section channel.

6. The dual swirl torch igniter according to any one of claims 1 to 5, characterized in that: The second side circumferential wall (12) is radially arranged on a side of the first side circumferential wall (11) away from the high-energy igniter (4); an oxidant inlet pipe (15) is radially connected to the second side circumferential wall (12), and the oxidant inlet pipe (15) is communicated with the oxidant collecting chamber (10).

7. The dual swirl torch igniter according to any one of claims 1 to 5, characterized in that: The first straight section (21) is provided with a plurality of fuel injection holes (210) on a side peripheral wall close to the head cavity housing (1) along the axial direction; the central axes of the fuel injection holes (210) are arranged perpendicular to the central axis of the first straight section (21); The diameter of the second straight-cylinder section (23) is smaller than the diameter of the first straight-cylinder section (21), and the second straight-cylinder section (23) is suitable for gathering and accelerating high-temperature combustion gas; The cone angle of the first cone section (22) is α, and the value range of α is 45°≤α≤70°.

8. The dual swirl torch igniter according to claim 7, characterized in that: One end of the mounting joint (33) axially away from the second conical cylinder section (32) is connected to a cooling sleeve (36); The outlet plane of the cooling sleeve (36) is higher than the outlet plane of the second straight section (23), and the distance between the outlet plane of the cooling sleeve (36) and the outlet plane of the second straight section (23) is H, and H satisfies 1mm≤H≤2mm.

9. A rocket engine, characterized in that: include: A rocket engine body, and a dual swirl torch igniter as described in any one of claims 1 to 8.

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