CN112240570B - Swirl torch igniter based on 3D printing forming - Google Patents
Swirl torch igniter based on 3D printing forming Download PDFInfo
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- CN112240570B CN112240570B CN202011124063.XA CN202011124063A CN112240570B CN 112240570 B CN112240570 B CN 112240570B CN 202011124063 A CN202011124063 A CN 202011124063A CN 112240570 B CN112240570 B CN 112240570B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
Abstract
The invention discloses a 3D printing forming-based rotational flow torch igniter, which comprises an electric spark plug rod, a torch ignition tube and a red copper sealing gasket; the torch ignition tube comprises a head tube section, a body tube section, a throat spray tube section and a tail tube section which are integrally formed in a 3D printing mode; the main working principle is as follows: the ignition combustion is carried out in the ignition chamber in the head pipe section, the secondary combustion is carried out in the secondary combustion chamber of the body pipe section, the tertiary mixing combustion is carried out in the throat spray pipe section, thereby the ignition starting process is stable, the combustion process is sufficient, the reliability of the combustion work of the igniter is greatly improved, and the head pipe section can form oxidant rotational flow to protect an electric spark plug rod, the rotational flow field is formed in the secondary combustion chamber to form gas film protection on the body pipe section, the reasonable design and the connection and fastening part of the thrust chamber are adopted, the appearance structure of the torch igniter is simplified, the miniaturized design of the torch igniter is realized, the process complexity is reduced, the cost is reduced, and the manufacturing period is shortened.
Description
Technical Field
The invention relates to a torch igniter, in particular to a 3D printing forming-based rotational flow torch igniter which can be applied to ignition of a liquid oxygen methane engine, high-performance attitude and orbit control propulsion power or other combustion chambers needing miniaturization.
Background
The control difficulty of the transient starting process of the liquid oxygen/methane engine is high, the mechanism of the ignition process is complex, and the method is one of the technical difficulties for developing the liquid oxygen/methane engine. In order to quickly adapt to the development requirement of a liquid oxygen/methane engine, more experimental research works are carried out at home and abroad aiming at the ignition technology: the power development of a morning glory moon lander and a service cabin of a hunting seat airship is taken as a target in the United states, the research is mainly carried out around two ignition modes of an electric spark and a glow plug of LOX/LCH4, and a multi-type double-low-temperature propellant liquid rocket engine adopts a torch igniter, such as Vinci, RD-0120, SSME and the like.
The ignition technology of the liquid oxygen/methane engine is less researched in China, and the electric spark and laser ignition of an attitude and orbit control engine and the ignition of a gunpowder igniter of a hundred-ton-class inner liquid oxygen/methane main engine are mainly researched. From the research and development experience of liquid oxygen methane and hydrogen oxygen engine ignition technology at home and abroad, methane is difficult to ignite compared with other low-temperature propellants, ignition delay time is long, and ignition energy requirement is high.
The torch igniter has the advantages of repeated ignition, simple structure, large ignition energy, adjustable ignition energy and the like, and can be used as one of ignition schemes developed by a reusable variable thrust adjusting liquid oxygen/methane engine. The ignition energy and the temperature of the igniter determine whether the thrust chamber can be ignited normally and reliably, and the heat protection difficulty needs to be reduced while the ignition reliability is guaranteed.
At present, a torch igniter at home and abroad mainly takes a single-nozzle combustion chamber as a main part, the igniter takes a central nozzle as an ignition and main combustion nozzle, body thermal protection is carried out by arranging a cooling air film hole at an edge area or a body part of an injection surface, and an ignition position, namely a main combustion backflow area, is caused due to the layout limitation of a spark plug and the single nozzle, so that the ignition reliability is low, the thermal protection of the spark plug is difficult, and the problem of large structural size exists.
In another type of torch igniter, a plurality of impacts of fuel and oxidant are applied to an ignition nozzle and a main combustion nozzle which are used as the igniter, cooling fuel is mixed through a body direct current nozzle for thermal protection, the igniter does not perform active cooling on a spark plug, the end ablation of the spark plug is easy to occur, the build-up pressure before fuel injection may cause poor ignition starting stability and narrow adaptability range to variable working conditions, and the igniter is manufactured in a machining and welding mode, so that the product quality reliability is poor due to welding deformation.
In addition, the existing torch igniter and the thrust chamber are connected through an ignition guide pipe, a straight joint is arranged on the thrust chamber, and a spherical joint and a sleeve nut are arranged on the ignition guide pipe, so that the structural connection is complex, and the miniaturization design is not facilitated.
Disclosure of the invention
The invention provides a swirl torch igniter based on 3D printing forming, aiming at solving the problems of low ignition reliability, easy ablation of a spark plug tip, narrow working condition changing adaptation range, poor thermal protection performance, serious welding deformation, difficulty in realizing miniaturization design and the like of the existing torch igniter.
The technical solution of the invention is as follows:
the invention provides a 3D printing forming-based rotational flow torch igniter, which comprises an electric spark plug rod and a torch ignition tube, wherein the electric spark plug rod is connected with the torch ignition tube through a connecting rod;
the torch ignition tube comprises a head tube section, a body tube section, a throat spray tube section and a tail tube section which are integrally formed in a 3D printing mode;
the head pipe section is provided with a central hole, an oxidant interface, an oxidant annular gas collecting cavity, an oxidant nozzle, a fuel interface, an ignition fuel annular gas collecting cavity, an ignition fuel nozzle and a chamber pressure measuring interface communicated with the front end of the body pipe section; the top end of the head pipe section is of a square structure;
the center hole is axially arranged along the head pipe section, the front part of the center hole is in threaded connection with the threaded section of the electric spark plug rod, the middle part of the center hole and the cylindrical section of the electric spark plug rod form an oxidant circumferential seam flow channel, and the rear part of the center hole is used as an ignition chamber;
the oxidant interface is arranged along the radial direction of the head pipe section and is communicated with the oxidant circumferential weld flow channel sequentially through the oxidant annular gas collecting cavity and the oxidant nozzles; the oxidant nozzles are uniformly arranged along the circumferential direction, and each oxidant nozzle is tangent to the central hole, so that oxidant rotational flow is formed by the oxidant in the oxidant circumferential seam flow channel;
the fuel interface is arranged along the radial direction of the head pipe section, and the fuel interface is communicated with the ignition chamber through the ignition fuel annular gas collecting cavity and the plurality of ignition fuel nozzles in sequence; the ignition fuel nozzles are uniformly arranged along the circumferential direction, each ignition fuel nozzle is vertically communicated with the ignition chamber, and the oxidant rotational flow is mixed with the ignition fuel and then is combusted in the ignition chamber for the first time to realize ignition;
the body part pipe section is provided with a secondary combustion chamber, a first cooling fuel annular gas collecting cavity, a first cooling fuel nozzle, a second cooling fuel annular gas collecting cavity, a second cooling fuel nozzle and a plurality of regenerative cooling channels;
the secondary combustion chamber is arranged along the axial direction of the body pipe section and is coaxially communicated with the ignition chamber;
the first cooling fuel annular gas collecting cavity and the second cooling fuel annular gas collecting cavity are sequentially arranged in the pipe wall of the body pipe section along the axial direction;
the first cooling fuel annular gas collecting cavity is communicated with the fuel interface through a constant throttling hole and is communicated with the secondary combustion chamber through a plurality of first cooling fuel nozzles, each first cooling fuel nozzle is tangent to the secondary combustion chamber to form a fuel rotational flow with the same rotational direction as the rotational direction of the oxidant rotational flow, and the fuel sprayed by the first cooling fuel nozzles is subjected to secondary mixing combustion in the secondary combustion chamber;
the second cooling fuel annular gas collecting cavity is communicated with the first cooling fuel annular gas collecting cavity through a plurality of regenerative cooling channels; the plurality of regenerative cooling channels are uniformly arranged in the pipe wall of the body pipe section along the circumferential direction, and each regenerative cooling channel is isolated from each other; the second cooling fuel annular gas collecting cavity is communicated with the secondary combustion chamber through second cooling fuel nozzles, each second cooling fuel nozzle is tangent to the secondary combustion chamber, an outlet of each second cooling fuel nozzle is obliquely arranged towards the throat spray pipe section, and fuel sprayed out of the second cooling fuel nozzles forms fuel rotational flow with the same rotational direction as the rotational direction of the oxidant rotational flow in the throat spray pipe section to perform third mixing combustion to generate high-temperature fuel gas;
high-temperature fuel gas enters the thrust chamber through the tail pipe section to complete ignition.
Further, the tail pipe section comprises a threaded part and a step part which are arranged in sequence;
the thread part of the tail pipe section is opposite to the thread turning direction of the standard joint of the thrust chamber and is connected with the standard joint of the thrust chamber through a locking nut with double turning directions, and the step part of the tail pipe section is matched with the standard joint of the thrust chamber to form a concave-convex step sealing structure.
Furthermore, the throat spray pipe section is provided with a lead sealing hole, and the corresponding locking nut with double rotation directions is also provided with a lead sealing hole.
Further, the chamber pressure measurement interface comprises a vertical section and an inclined section; the vertical section is radially arranged along the head pipe section, one end of the inclined section is communicated with the vertical section, and the other end of the inclined section is communicated with the front end of the body pipe section.
Furthermore, the axial depth of the ignition chamber is 1/2-4/5 of the diameter of the electric spark plug rod, the diameter of the secondary combustion chamber is 2-2.5 times of the diameter of the ignition chamber, the axial depth of the secondary combustion chamber is 0.8-1.2 times of the diameter of the secondary combustion chamber, and the convergence angle and the diffusion angle of the throat spray pipe section are both 70-90 degrees.
Further, the number of the oxidant nozzles is 3-6, the number of the ignition fuel nozzles is 2-4, the number of the first cooling fuel nozzles is 4-6, the number of the second cooling fuel nozzles is 4-6, and the inclination angle of the throat spray pipe section is 15-40 degrees.
Furthermore, the outlet flow velocity of the oxidant nozzle, the ignition fuel nozzle, the first cooling fuel nozzle and the second cooling fuel nozzle is 80-150 m/s.
Furthermore, the ignition chamber adopts an oxygen-enriched combustion ignition mode, and the mixing ratio of an oxidant to fuel in the ignition chamber is 20-30; if the positions of the oxidant interface and the fuel interface are exchanged, the mixing ratio of the oxidant to the fuel in the ignition chamber is 0.8-1.5.
Furthermore, a red copper sealing gasket is adopted between the torch ignition tube and the electric spark plug rod for end face sealing.
Further, the torch igniter tube is sequentially printed and formed from the head tube section to the tail tube section.
Compared with the prior art, the invention has the beneficial effects that:
1. the swirl torch igniter provided by the invention is designed based on the principle of zone combustion and gas swirl cooling, fuel enters the ignition chamber and the secondary combustion chamber through proportion flow division, and is ignited with oxidant in the ignition chamber to form an oxygen-enriched primary main combustion zone, and the zone is a stable backflow zone, and the cooling fuel and the oxygen-enriched gas in the primary main combustion zone are subjected to secondary mixing combustion in the secondary combustion chamber and three times of mixing combustion in a throat spray pipe section, so that the ignition starting process is stable, the combustion process is sufficient, and the reliability of the ignition torch combustion work is greatly improved.
2. According to the swirl torch igniter, an oxidant enters the ignition chamber through the swirl of the tangentially arranged oxidant nozzle, gas film protection is formed on the surface of the electric spark plug, and cooling fuel enters the secondary combustion chamber through the two rows of tangential holes of the body pipe section, so that effective gas film protection is formed on the body pipe section and the throat spray pipe section, the problem of thermal protection of torch ignition design is solved, meanwhile, the gas retention time is prolonged, the body length is shortened, and miniaturization design is facilitated.
3. The swirl torch igniter is integrally formed by adopting an additive manufacturing process, so that a generated tangential nozzle can form swirl and play a role in protection, the regenerative cooling channel is arranged in the pipe wall of the body pipe section to effectively provide thermal protection, when swirl airflow flows in a combustion chamber, a radially distributed pressure gradient can be formed due to the action of centrifugal force and is sequentially increased from inside to outside, the numerical value is larger in the radial measurement chamber of the body, the combustion chamber measurement channel is designed by virtue of 3D printing advantages, the measurement channel is arranged at the head pipe section of the ignition torch and is communicated with the body pipe section, and measurement and integration design are facilitated.
Therefore, the invention has obvious design advantages in the aspects of miniaturization and complication of the torch igniter by adopting the 3D printing technology, highly integrated parts and compact structure, realizes the miniaturization design of the torch igniter, avoids the influence of welding deformation, greatly reduces the process complexity and cost and shortens the manufacturing period.
Drawings
FIG. 1 is a schematic perspective view of an embodiment;
FIG. 2 is a sectional view of the embodiment;
FIG. 3 is a cross-sectional view with oxidant swirl and swirl flow fields;
FIG. 4 is a cross-sectional view of a chamber pressure measurement interface;
fig. 5 is a perspective sectional view of a structure having a regenerative cooling passage.
The reference numbers are as follows:
1-electric spark plug rod, 2-torch ignition tube, 3-red copper sealing gasket, 4-head tube section, 5-body tube section, 6-throat spray tube section, 7-tail tube section, 8-center hole, 9-oxidant interface, 10-oxidant annular gas collection cavity, 11-oxidant nozzle, 12-fuel interface, 13-ignition fuel annular gas collection cavity, 14-ignition fuel nozzle, 15-room pressure measuring interface, 16-oxidant annular seam flow channel, 17-ignition chamber, 18-oxidant rotational flow, 19-secondary combustion chamber, 20-first cooling fuel annular gas collection cavity, 21-first cooling fuel nozzle, 22-second cooling fuel annular gas collection cavity, 23-second cooling fuel nozzle, 24-regeneration cooling channel, 25-constant throttling hole, 26-rotational flow field, 27-threaded part, 28-step part, 29-lead sealing hole, 30-vertical section and 31-inclined section.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Examples
As shown in fig. 1 and fig. 2, the basic structure of the swirling torch igniter based on 3D printing forming of the invention comprises an electric spark plug rod 1, a torch igniter tube 2 and a red copper sealing gasket 3;
the electric spark plug rod 1 is connected with the torch ignition tube 2 through threads, and high-pressure sealing is realized by a red copper sealing gasket 3;
the torch ignition tube 2 comprises a head tube section 4, a body tube section 5, a throat spray tube section 6 and a tail tube section 7 which are integrally formed in a 3D printing mode;
as shown in fig. 2, 3 and 4, the head pipe section 4 comprises a central hole 8, an oxidant port 9, an oxidant annular gas collecting cavity 10, an oxidant nozzle 11, a fuel port 12, an ignition fuel annular gas collecting cavity 13, an ignition fuel nozzle 14 and a chamber pressure measuring port 15 communicated with the front end of the body pipe section 5;
the center hole 8 is axially arranged along the head pipe section 4, the front part of the center hole 8 is in threaded connection with the threaded section of the electric spark plug rod 1, the middle part of the center hole 8 and the cylindrical section of the electric spark plug rod 1 form an oxidant circumferential seam flow channel 16, and the rear part of the center hole 8 is used as an ignition chamber 17;
the oxidant interface 9 is radially arranged along the head pipe section 4, and the oxidant interface 9 is communicated with the oxidant circumferential seam flow channel 16 sequentially through the oxidant annular gas collecting cavity 10 and the oxidant nozzles 11; a plurality of oxidant nozzles 11 are uniformly arranged in the circumferential direction, and each oxidant nozzle 11 is tangential to the central hole 8, so that the oxidant forms an oxidant swirl 18 in the oxidant circumferential seam flow channel 16;
the fuel interface 12 is arranged along the radial direction of the head pipe section 4, and the fuel interface 12 is communicated with the ignition chamber 17 sequentially through the ignition fuel annular gas collecting cavity 13 and the ignition fuel nozzles 14; the ignition fuel nozzles 14 are uniformly arranged along the circumferential direction, each ignition fuel nozzle 14 is vertically communicated with the ignition chamber 17, and the oxidant rotational flow 18 is mixed with ignition fuel and then is combusted in the ignition chamber 17 for the first time to realize ignition;
as shown in fig. 2-5, a secondary combustion chamber 19, a first cooling fuel annular gas collecting cavity 20, a first cooling fuel nozzle 21, a second cooling fuel annular gas collecting cavity 22, a second cooling fuel nozzle 23 and a plurality of regenerative cooling channels 24 are arranged in the body section 5;
the secondary combustion chamber 19 is arranged along the axial direction of the body pipe section 5 and is coaxially communicated with the ignition chamber 17;
the first cooling fuel annular gas collecting cavity 20 and the second cooling fuel annular gas collecting cavity 22 are sequentially arranged in the pipe wall of the body pipe section 5 along the axial direction;
the first cooling fuel annular gas collecting cavity 20 is communicated with the fuel interface 12 through a constant throttling hole 25, is communicated with the secondary combustion chamber 19 through a plurality of first cooling fuel nozzles 21, each first cooling fuel nozzle 21 is tangent to the secondary combustion chamber 19 to form a swirling flow field 26 having the same swirling direction as the oxidant swirling flow 18, and the fuel sprayed out of the first cooling fuel nozzles 21 is subjected to second mixing combustion in the secondary combustion chamber 19;
the second cooling fuel annular gas collecting cavity 22 is communicated with the first cooling fuel annular gas collecting cavity 20 through a plurality of regenerative cooling channels 24; the plurality of regenerative cooling channels 24 are uniformly arranged in the pipe wall of the body pipe section 5 along the circumferential direction, and each regenerative cooling channel 24 is isolated from each other; the second cooling fuel annular gas collecting cavity 22 is communicated with the secondary combustion chamber 19 through second cooling fuel nozzles 23, each second cooling fuel nozzle 23 is tangent to the secondary combustion chamber 19, the outlet of each second cooling fuel nozzle 23 faces the direction of the throat spray pipe section 6 and is obliquely arranged, and fuel sprayed by the second cooling fuel nozzles 23 forms a swirling flow field 26 which has the same swirling direction as the oxidant swirling flow 18 in the throat spray pipe section 6 to perform third mixing combustion to generate high-temperature fuel gas;
high-temperature fuel gas enters the thrust chamber through the tail pipe section 7 to complete ignition work.
When the igniter works, the flow conditions of the oxidant are as follows:
oxidant medium flows into an oxidant annular gas collecting cavity 10 from an oxidant interface 9 to form uniform pressure before spraying, enters an oxidant annular seam flow passage 16 through an oxidant nozzle 11 and then enters an ignition chamber 17;
when the igniter works, the flowing condition of the fuel is as follows:
the fuel medium enters from the fuel interface 12 and is divided into an ignition fuel circuit and a cooling fuel circuit; the flow dividing ratio of the ignition fuel path and the cooling fuel path is controlled by the flow area of the constant orifice 25;
ignition fuel in the ignition fuel path enters the ignition fuel annular gas collecting cavity 13 and then enters the ignition chamber 17 through the ignition fuel nozzle 14, and the oxidant and the ignition fuel are ignited in the ignition chamber 17 to form a main combustion area of the torch igniter.
Ignition fuel in the cooling fuel path firstly enters the first cooling fuel annular gas collecting cavity 20 through the constant throttling hole 25, enters the secondary combustion chamber 19 through the first cooling fuel nozzle 21 for secondary mixing combustion, and the rest of fuel flows through the regeneration cooling channel 24, enters the second cooling fuel annular gas collecting cavity 22 and is sprayed to the throat spray pipe section 6 through the second cooling fuel nozzle 23 for third mixing combustion. High-temperature fuel gas enters the thrust chamber through the tail pipe section 7 to complete torch ignition work, and meanwhile isolation is formed between the supersonic speed working state of the jet pipe and the thrust chamber.
The specific ignition, combustion and cooling mechanism of the igniter is shown in figures 2, 3 and 4:
the 3D printing torch igniter is designed based on the principle of zone combustion and gas swirl cooling, oxidant enters an oxidant circumferential weld flow channel 16 through an oxidant nozzle 11 arranged tangentially to form an oxidant swirl 18, an electric spark plug rod 1 is cooled and protected by the oxidant swirl 18 formed by the oxidant in the oxidant circumferential weld flow channel 16, and ignition fuel injected by an ignition fuel nozzle 14 arranged radially is mixed in an ignition chamber 17, and the electric spark plug rod 1 discharges at the position to perform ignition combustion to form a stable ignition backflow zone.
After the fuel sprayed by the first cooling fuel nozzle 21 and the fuel sprayed by the second cooling fuel nozzle 23 enter the combustion chamber, a swirling flow field 26 surrounding the secondary combustion chamber 19 is formed, the gas flows from top to bottom in the secondary combustion chamber 19, and the gas film protection is formed on the body pipe section 5 and the afterburning is carried out at the same time. The direction of the oxidant rotational flow 18 formed by the oxidant is the same as that of the rotational flow field 26 in the secondary combustion chamber 19, the inner and outer circles form a stable double rotational flow field, if the directions of the inner and outer circles are opposite, the stable structure is damaged, and the stable structure is cooled and mixed to gradually turn into rich fuel gas.
The fuel enters the ignition chamber 17, the secondary combustion chamber 19 and the throat spray pipe section 6 in sequence, ignition, secondary blended fuel afterburning and tertiary blended fuel afterburning are sequentially carried out, the combustion chamber is changed into rich combustion flame from an oxygen-enriched main combustion area, and the small-flow ignition realizes the stable transition of the ignition process.
The igniter structure of the embodiment is also optimally designed as follows:
1. as shown in fig. 1, when the spark plug rod 1 is installed, the wrench position (a position in the drawing) is used as the fastening tool output position and is arranged in a polygonal structure, so that the operation is convenient and fast, and the overall weight reduction of the igniter structure is facilitated. When the torch ignition tube 2 is connected with the thrust chamber, the tail tube section 7 comprises a threaded part 27 and a step part 28 which are arranged in sequence; the thread part 27 of the tail pipe section 7 is opposite to the thread direction of the standard joint of the thrust chamber and is connected by a locking nut with double rotation directions, and the step part 28 of the tail pipe section 7 is matched with the standard joint of the thrust chamber to form a concave-convex step sealing structure and is locked by the locking nut with double rotation directions;
in addition, the throat spray pipe section 7 and the double-rotation-direction locking nut are both provided with lead sealing holes 29, and an iron wire penetrates through the two lead sealing holes 29 to be cured and prevented from loosening. The design combines with a 3D printing process, and effectively simplifies the connection mode of the torch igniter and the thrust chamber.
2. As shown in fig. 3, when the swirling air field 26 flows in the secondary combustion chamber 19, due to the action of centrifugal force, a radially distributed pressure gradient is formed, which increases from inside to outside in sequence, if the secondary combustion chamber 19 chamber pressure is measured directly on the body pipe section 5, the value is larger, in this embodiment, the chamber pressure measuring interface 15 is designed to be located on the head pipe section 4 as a whole by means of 3D printing advantages, and the specific structure includes a vertical section 30 and an inclined section 31; the vertical section 30 is radially opened along the head pipe section 4, and the inclined section 31 is inclined at a certain angle with respect to the axial direction of the head pipe section 4, and has one end communicating with the vertical section 30 and the other end communicating with the front end of the body pipe section 5, thereby avoiding the above-mentioned problems and providing an accurate chamber pressure.
3. The axial depth of the ignition chamber 17 is 1/2-4/5 of the diameter of the spark plug rod 1, if the depth is too small, the backflow zone can ablate the end of the spark plug, and if the depth is too large, ignition is not easy to perform. The diameter of the secondary combustion chamber 19 is 2-2.5 times of the diameter of the ignition chamber 17, the axial depth of the secondary combustion chamber 19 is 0.8-1.2 times of the diameter of the secondary combustion chamber 19, when the diameter of the secondary combustion chamber 19 is too large, the secondary combustion is not easy to mix, fuel can be concentrated in the throat spray pipe section 7, when the diameter is too small, the double swirl fields formed by the oxidant rotating airflow 18 and the swirl flow field 26 interfere with each other, and the cooling of the body pipe section 5 is not facilitated; the convergence angle and the diffusion angle of the throat spray pipe section 6 are both 70-90 degrees, the smaller the angle is, the cooling is not facilitated, and when the angle is larger, the swirl air film is stagnant on the end face, the momentum is too small, and the cooling is also not facilitated. The outlet flow rates of the oxidant nozzle 11, the ignition fuel nozzle 14, the first cooling fuel nozzle 20 and the second cooling fuel nozzle 22 are all 80-150 m/s, if the nozzle speed is too high, the injection pressure drop is too high, the gas mixing and combustion residence time is short, the combustion organization is not facilitated, and if the nozzle speed is too low, the mixing and combustion process is fast, and the thermal protection is not facilitated.
4. 3-6 oxidant nozzles 11, 2-4 ignition fuel nozzles 14, and the fuel injected by the ignition fuel nozzles 14 and oxidant swirling flow formed by the oxidant nozzles 11 are mixed at an included angle of 90 degrees, so that a backflow area is formed. First cooling fuel nozzle 20 is 4 ~ 6, is located near the top of body section 5, and second cooling fuel nozzle 23 is 4 ~ 6, and is 15 ~ 40 to the angle of 6 slopes of throat nozzle section, and swirl gas can prolong gaseous dwell time in the combustion chamber, is favorable to shortening body length, realizes miniaturized design, and certain angle of slope is favorable to cooling the throat in the section of expanding of receipts.
5. In addition, the torch igniter of the embodiment adopts an oxygen-enriched combustion ignition mode, if the oxidant port 9 and the fuel port 12 are arranged as shown in fig. 2, the mixing ratio of the oxidant and the fuel in the ignition chamber is 20-30, if the positions of the oxidant port 9 and the fuel port 12 are reversed, the fuel gas film protects the electric spark plug rod 1, and the mixing ratio of the oxidant and the fuel in the ignition chamber needs to be adjusted to be 0.8-1.5.
6. The torch igniter in the embodiment is integrally realized through an additive manufacturing process, the printing and forming are sequentially carried out from the head pipe section 4 to the tail pipe section 7, the limitation and the advantage of the printing process are fully considered, the structural arrangement not only meets the requirement of the printing process, but also is highly integrated in parts and compact in structure.
Test verification
The torch igniter of the embodiment is subjected to numerical simulation, and the simulation result is that effective gas film protection is formed inside the torch igniter tube, so that the partitioned combustion effect is realized;
after 10 thermal state test tests, the torch igniter works normally, the flame at the outlet is stable, the thermal protection is effective, the spark plug is not ablated, the expected effect of design is achieved, and the defects of the existing torch igniter are overcome.
The above description of the embodiments and the accompanying drawings represent preferred embodiments of the present invention, and those skilled in the art will appreciate that various additions, modifications and substitutions are possible, in accordance with different design requirements and design parameters, without departing from the scope of the present invention as defined in the accompanying claims.
Claims (10)
1. The utility model provides a swirl torch point firearm based on 3D prints fashioned which characterized in that: comprises an electric spark plug rod and a torch ignition tube;
the torch ignition tube comprises a head tube section, a body tube section, a throat spray tube section and a tail tube section which are integrally formed in a 3D printing mode;
the head pipe section is provided with a central hole, an oxidant interface, an oxidant annular gas collecting cavity, an oxidant nozzle, a fuel interface, an ignition fuel annular gas collecting cavity, an ignition fuel nozzle and a chamber pressure measuring interface communicated with the front end of the body pipe section; the top end of the head pipe section is of a square structure;
the center hole is axially arranged along the head pipe section, the front part of the center hole is in threaded connection with the threaded section of the electric spark plug rod, the middle part of the center hole and the cylindrical section of the electric spark plug rod form an oxidant circumferential seam flow channel, and the rear part of the center hole is used as an ignition chamber;
the oxidant interface is arranged along the radial direction of the head pipe section and is communicated with the oxidant circumferential weld flow channel sequentially through the oxidant annular gas collecting cavity and the oxidant nozzles; the oxidant nozzles are uniformly arranged along the circumferential direction, and each oxidant nozzle is tangent to the central hole, so that oxidant rotational flow is formed by the oxidant in the oxidant circumferential seam flow channel;
the fuel interface is arranged along the radial direction of the head pipe section, and the fuel interface is communicated with the ignition chamber through the ignition fuel annular gas collecting cavity and the plurality of ignition fuel nozzles in sequence; the ignition fuel nozzles are uniformly arranged along the circumferential direction, each ignition fuel nozzle is vertically communicated with the ignition chamber, and the oxidant rotational flow is mixed with the ignition fuel and then is combusted in the ignition chamber for the first time to realize ignition;
the body part pipe section is provided with a secondary combustion chamber, a first cooling fuel annular gas collecting cavity, a first cooling fuel nozzle, a second cooling fuel annular gas collecting cavity, a second cooling fuel nozzle and a plurality of regenerative cooling channels;
the secondary combustion chamber is arranged along the axial direction of the body pipe section and is coaxially communicated with the ignition chamber;
the first cooling fuel annular gas collecting cavity and the second cooling fuel annular gas collecting cavity are sequentially arranged in the pipe wall of the body pipe section along the axial direction;
the first cooling fuel annular gas collecting cavity is communicated with the fuel interface through a constant throttling hole and is communicated with the secondary combustion chamber through a plurality of first cooling fuel nozzles, each first cooling fuel nozzle is tangent to the secondary combustion chamber to form a fuel rotational flow with the same rotational direction as the rotational direction of the oxidant rotational flow, and the fuel sprayed by the first cooling fuel nozzles is subjected to secondary mixing combustion in the secondary combustion chamber;
the second cooling fuel annular gas collecting cavity is communicated with the first cooling fuel annular gas collecting cavity through a plurality of regenerative cooling channels; the plurality of regenerative cooling channels are uniformly arranged in the pipe wall of the body pipe section along the circumferential direction, and each regenerative cooling channel is isolated from each other; the second cooling fuel annular gas collecting cavity is communicated with the secondary combustion chamber through second cooling fuel nozzles, each second cooling fuel nozzle is tangent to the secondary combustion chamber, an outlet of each second cooling fuel nozzle is obliquely arranged towards the throat spray pipe section, and fuel sprayed out of the second cooling fuel nozzles forms fuel rotational flow with the same rotational direction as the rotational direction of the oxidant rotational flow in the throat spray pipe section to perform third mixing combustion to generate high-temperature fuel gas;
high-temperature fuel gas enters the thrust chamber through the tail pipe section to complete ignition.
2. The swirl torch igniter based on 3D printing forming of claim 1, wherein: the tail pipe section comprises a threaded part and a step part which are arranged in sequence;
the thread part of the tail pipe section is opposite to the thread turning direction of the standard joint of the thrust chamber and is connected with the standard joint of the thrust chamber through a locking nut with double turning directions, and the step part of the tail pipe section is matched with the standard joint of the thrust chamber to form a concave-convex step sealing structure.
3. 3D print modeling based swirl torch igniter of claim 2, wherein: and the throat spray pipe section is provided with a lead sealing hole, and the corresponding double-rotation-direction locking nut is also provided with a lead sealing hole.
4. 3D print molding based swirl torch igniter of claim 3, wherein: the chamber pressure measurement interface comprises a vertical section and an inclined section; the vertical section is radially arranged along the head pipe section, one end of the inclined section is communicated with the vertical section, and the other end of the inclined section is communicated with the front end of the body pipe section.
5. The swirl torch igniter based on 3D printing forming of claim 4, wherein: the axial depth of the ignition chamber is 1/2-4/5 of the diameter of an electric spark plug rod, the diameter of the secondary combustion chamber is 2-2.5 times of the diameter of the ignition chamber, the axial depth of the secondary combustion chamber is 0.8-1.2 times of the diameter of the secondary combustion chamber, and the convergence angle and the diffusion angle of the throat spray pipe section are both 70-90 degrees.
6. The swirl torch igniter based on 3D printing forming of claim 5, wherein: oxidant nozzle is 3 ~ 6, and ignition fuel nozzle is 2 ~ 4, and first cooling fuel nozzle is 4 ~ 6, and second cooling fuel nozzle is 4 ~ 6, and is 15 ~ 40 to the angle of throat spray pipe section slope.
7. The swirl torch igniter based on 3D printing forming of claim 6, wherein: and the outlet flow velocities of the oxidant nozzle, the ignition fuel nozzle, the first cooling fuel nozzle and the second cooling fuel nozzle are all 80-150 m/s.
8. The swirl torch igniter based on 3D printing forming of claim 7, wherein: the ignition chamber adopts an oxygen-enriched combustion ignition mode, and the mixing ratio of an oxidant to fuel in the ignition chamber is 20-30; if the positions of the oxidant interface and the fuel interface are exchanged, the mixing ratio of the oxidant to the fuel in the ignition chamber is 0.8-1.5.
9. The swirl torch igniter based on 3D printing forming of claim 8, wherein: and a red copper sealing gasket is adopted between the torch ignition tube and the electric spark plug rod for end face sealing.
10. The swirl torch igniter based on 3D printing forming of claim 9, wherein: and the torch ignition tube is sequentially printed and formed from the head tube section to the tail tube section.
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| CN202011124063.XA CN112240570B (en) | 2020-10-20 | 2020-10-20 | Swirl torch igniter based on 3D printing forming |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113669161A (en) * | 2021-08-24 | 2021-11-19 | 中国航发贵阳发动机设计研究所 | Igniter with oxygen supplementing structure |
| CN114483380B (en) * | 2021-12-23 | 2023-07-14 | 北京航天动力研究所 | Small-sized gas generator capable of being started for multiple times |
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