CN113217196A - Self-air-entraining sliding arc plasma jet igniter of concave cavity flame stabilizer and ignition method - Google Patents
Self-air-entraining sliding arc plasma jet igniter of concave cavity flame stabilizer and ignition method Download PDFInfo
- Publication number
- CN113217196A CN113217196A CN202110233589.XA CN202110233589A CN113217196A CN 113217196 A CN113217196 A CN 113217196A CN 202110233589 A CN202110233589 A CN 202110233589A CN 113217196 A CN113217196 A CN 113217196A
- Authority
- CN
- China
- Prior art keywords
- igniter
- air
- tangential
- inlet
- shell
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
- F02C7/266—Electric
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/14—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines with external combustion, e.g. scram-jet engines
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
The utility model provides a cavity flame holder is from bleed sliding arc plasma efflux point firearm, and the whole cylindrical shape that is of some firearm is provided, including some firearm base hypoplastron (201), some firearm base upper plate (202), some firearm shell (203), tangential air inlet (204), tangential fuel inlet (205), high-voltage electrode (206) and cylindrical electrode insulation base (207). A method of self-bleed sliding arc plasma jet ignition of a re-entrant flame holder is also provided. The device and the method improve the ignition capability of the concave cavity flame stabilizer, widen the stable combustion range of the combustion cavity, have the characteristics of simple structure, strong stability and the like, can further overcome the defect of small energy when ignition is carried out by independently depending on a sliding arc plasma exciter through the coupling amplification effect of the flame with strong rotational flow, and optimize the ignition effect.
Description
Technical Field
The invention belongs to the technical field of aerospace, and particularly relates to a self-air-entraining sliding arc plasma jet igniter for a concave cavity flame stabilizer and an ignition method.
Background
The sliding arc plasma is a non-equilibrium plasma generated by a heat loss cycle between two or more diverging electrodes with gradually increasing spacing under the action of a gas flow.
The swirl flame has the obvious characteristics of stable flame, low lean combustion limit, more control parameters and the like, and is widely applied to industrial combustion design. The invention discloses an atomized flame nanoparticle synthesis system based on multi-swirl enhanced mixing, which applies swirl stagnation flame to the field of flame synthesis (publication number: CN207745881U), and realizes the common regulation of swirl gas fuel flame and axial liquid fuel flame and the control of the particle size, the shape and the crystalline phase of synthesized nanoparticles by designing tangential and axial precursor feeding modes.
For a pure sliding discharge igniter, due to the limited discharge power, the ignition requirement under extreme conditions cannot be met, and the structure and parameters of the sliding arc ignition device need to be further adjusted and optimized. With the further development of flame synthesis technology, a swirl flame burner and sliding arc plasma discharge are hopefully combined to design a novel ignition device.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a self-air-entraining sliding arc plasma jet igniter for a concave cavity flame stabilizer and an ignition method, which are used for improving the ignition and stable working capacity of an engine under ground and air ignition and severe working conditions. The air source required by the sliding arc work is provided by the air entraining device, and the coupling amplification function of the sliding arc and the strong swirling flame is realized during the tangential fuel feeding by designing the tangential fuel feeding mode.
The cavity flame stabilizer self-air-entraining sliding arc plasma jet igniter is provided, the igniter is integrally cylindrical and comprises an igniter base lower plate 201, an igniter base upper plate 202, an igniter shell 203, a tangential air inlet 204, a tangential fuel inlet 205, a high-voltage electrode 206 and a cylindrical electrode insulating base 207; wherein
The igniter shell 203 is a hollow cylindrical tube, the top of the igniter shell is fixedly connected with the bottom of the cavity flame stabilizer 103, and the igniter shell 203 is communicated with the inside of the cavity flame stabilizer 103;
the igniter base upper plate 202 is shaped as a hollow circular flat plate; the lower plate 201 of the igniter base is also of a hollow circular ring structure, and the inner diameters of the two are the same; the inner wall of the ring of the igniter base upper plate 202 wraps the outer wall of the bottom of the igniter shell 203 and continuously extends downwards, and the igniter base lower plate 201 is arranged next to the igniter base upper plate 202, is positioned below the igniter base upper plate and is fixedly connected with the igniter base upper plate; through holes leading to the inside of the igniter shell 203 are machined at the junction of the igniter base lower plate 201 and the igniter base upper plate 202, the shape and the size of each through hole are determined by the external size of a round pipe used by the corresponding tangential air inlet 204 and the tangential fuel inlet 205, the number of the through holes is determined by the number of the tangential air inlets 204 and the tangential fuel inlets 205, and the axes of the through holes in the opening direction are all parallel to the tangential direction of the circumference of the inner side of the igniter shell 203; respectively machining half through holes at corresponding positions of the igniter base upper plate 202 and the igniter base lower plate 201, wherein the upper edges of the through holes machined in the igniter base upper plate 202 are flush with the lower edges of the igniter shell 203;
the tangential air inlets 204 and the tangential fuel inlets 205 are independent round pipes, the number of outlets of the tangential air inlets 204 is equal to that of outlets of the tangential fuel inlets 205, the outlets are alternately distributed on the same horizontal plane at intervals, and the tangential air inlets 204 and the tangential fuel inlets 205 are vertically clamped by the igniter base lower plate 201 and the igniter base upper plate 202 and are fixedly arranged between the igniter base lower plate 201 and the igniter base upper plate 202; the air and fuel flow from the tangential air inlet 204 and the tangential fuel inlet 205 are both tangential to the inside circumference of the igniter housing 203;
the cylindrical electrode insulation base 207 is concentrically arranged in the middle of the hollow circular ring of the igniter base lower plate 201 and is wrapped by the inner wall of the circular ring of the igniter base lower plate 201;
the lower end of the high voltage electrode 206 is connected to the high voltage end of the igniter power supply and the upper end extends through the center of the cylindrical electrode insulator base 207 and into the igniter housing 203.
In one embodiment of the invention, the igniter housing 203 is a metal or ceramic tube; the tangential air inlet 204 and the tangential fuel inlet 205 are both stainless steel round pipes and are uniformly spaced on the same horizontal plane, and the outlets of the tangential air inlet 204 and the tangential fuel inlet 205 are round holes or are processed into slits on the basis of round pipes; the upper end of the high voltage electrode 206 passes through the center of the cylindrical electrode insulator base 207 to the middle of the igniter housing 203.
In another embodiment of the invention, the igniter housing 203 is a metal or ceramic tube, the igniter housing 203 has an inner diameter of 10mm to 20mm and a height in the range of 30mm to 100 mm; the total number of tangential air inlets 204 is 2-6; the total number of tangential fuel inlets 205 is 2-6; the cylindrical electrode insulation base 207 is made of ceramic; the high voltage electrode 206 extends 0-40mm deep inside the igniter housing 203.
In one embodiment of the invention, the igniter housing 203 is a ceramic tube, the igniter housing 203 has an inner diameter of 16mm and a height of 40 mm; the total number of tangential air inlets 204 is 4; the total number of tangential fuel inlets 205 is 4; the cylindrical electrode insulating base 207 is made of zirconia ceramic; the high voltage electrode 206 extends 30mm deep inside the igniter housing 203.
In yet another embodiment of the present invention, when the outlet of the tangential air inlet 204 is shaped as a slit, it is a vertical slit with a height of 1-5mm and a width of 0.5-2 mm; when the circular hole is formed, the circular hole is formed with the radius of 1-4 mm; when the shape of the inner side outlet of the tangential fuel inlet 205 is a slit, the slit is a vertical slit with the height of 0.5-3mm and the width of 0.1-2 mm; when the diameter is round, the diameter is 0.1-2 mm.
In another embodiment of the present invention, the outlet of the tangential air inlet 204 is in the shape of a slit, with a height of 3mm and a width of 1 mm; when the circular hole is a circular hole, the circular hole has a radius of 2 mm; when the shape of the inner outlet of the tangential fuel inlet 205 is a slit, the slit is 1mm high and 0.3mm wide; when the diameter is a circular hole, the diameter is 0.3 mm.
Still provide a cavity flame holder from bleed sliding arc plasma efflux ignition, its characterized in that includes: a bleed air pipe 111, an air conveying pipeline 112, a bleed air pipeline adjusting valve 113 and an igniter 114; the air guide pipe 111 is a hollow metal elbow, an inlet is vertical to the incoming flow direction, and an outlet is fixedly connected with the air transmission pipeline 112; the inlet of the bleed air pipe 111 introduces air from the main flow in a total pressure collection manner, and the air flow flows into the air delivery pipeline 112 through the outlet; an air-bleed pipeline regulating valve 113 is arranged in the air pipeline 112, and the flow in the air pipeline is regulated in an electric control mode; the outlet of the air transmission pipeline 112 is provided with a one-to-N connector which divides the air from the air transmission pipeline 112 into N outputs, and the N outputs are respectively and fixedly connected with the inlet of each tangential air inlet 204 of the igniter 114, so that the quantity of N is the quantity of the tangential air inlets 204.
In one embodiment of the invention, the installation position of the inlet of the bleed air pipe 111 is selected to be installed on the wall surface of the isolated section or the air inlet; the diameter of the air guide pipe 111 is 4mm-10 mm; the diameter of the air transmission pipeline 112 is 4mm-10 mm.
In one embodiment of the invention, the inlet of the bleed air duct 111 is mounted to the air inlet wall; the diameter of the air guide pipe 111 is 6 mm; the diameter of the gas transmission pipeline 112 is 6 mm; n is 4.
In addition, a self-air-entraining sliding arc plasma jet ignition method of the cavity flame stabilizer is provided, which is characterized in that the ignition working mode of the device is determined by the working condition requirement of the cavity flame stabilizer, and the two modes of a and b are provided;
mode a. single sliding arc ignition mode involving only tangential air feed
Mode b Co-ignition mode involving tangential fuel flame and sliding arc
In the mode a operation, the bleed air pipeline adjusting valve 113 is opened, air flowing in from the bleed air pipeline 111 at the total pressure flows into the tangential air inlet 204 through the air pipeline 112, and because the outlet of the tangential air inlet 204 is a slit or a round hole with a small size, the gas flowing out of the outlet forms a tangential airflow with a high speed on the inner side of the igniter shell 203 and moves towards the outlet of the igniter shell 203 in a spiral track under the constraint of the igniter shell 203; the igniter shell 203 is connected with the low-pressure end of the igniter power supply through a lead, the igniter power supply is turned on, discharge is carried out between the high-voltage electrode 206 and the igniter shell 203 to form plasma, the plasma moves towards the outlet of the igniter shell 203 under the blowing of tangential spiral airflow to form sliding arc plasma 301 generated by discharge, and the sliding arc plasma 301 is ejected out of the igniter outlet to ignite the flame stabilizer in the cavity;
in the mode b, when the air guide pipeline adjusting valve 113 is opened, the air flowing in from the air guide pipeline 111 at the total pressure flows into the tangential air inlet 204 through the air conveying pipeline 112, and because the outlet of the tangential air inlet 204 is a slit or a round hole with a small size, the gas flowing out of the outlet forms a tangential airflow with a higher speed on the inner side of the igniter shell 203 and moves towards the outlet in a spiral track under the constraint of the igniter shell 203; fuel oil entering from the tangential fuel inlet 205 is atomized and sprayed into the inner side of the igniter through the outlet circular hole and mixed with tangential air to form combustible mixed gas; the igniter shell 203 is connected with the low-voltage end of the igniter power supply through a lead, the igniter power supply is turned on, the discharge is formed between the high-voltage electrode 206 and the igniter shell 203, the plasma moves towards the igniter outlet under the blowing of tangential spiral airflow to form sliding arc plasma 301 generated by the discharge, and the sliding arc plasma 301 is ejected out of the igniter outlet; the sliding arc plasma 301 simultaneously ignites the combustible mixed gas in spiral motion to form strong swirl flame 302, the tail end of the flame and high-temperature fuel gas are sprayed out from an igniter outlet, and in addition, air entering tangentially can form an air film on the inner wall of a cylindrical shell of the igniter shell 203 to play a role in protecting the tube wall; the sliding arc plasma 301 in combination with the highly swirling flame 302 ignites the re-entrant flame holder.
Compared with the prior art, the invention has the following advantages and outstanding technical effects:
the tangential inlet of the combustion cavity in the self-air-entraining jet igniter and the ignition method combining the sliding arc and the rotational flow comprises the tangential inlet of fuel and the tangential inlet of air, and after the fuel enters the rotational flow flame burner from the tangential fuel inlet, the fuel is quickly mixed with the air entering from the tangential inlet of air in the base of the igniter, so that the tempering risk of forming premixed flame by the fuel oil and the air is effectively avoided.
Aiming at different working conditions, the sliding arc device supplies air by adopting different air-entraining modes, realizes air supply through a total pressure air-entraining pipe positioned at the upstream of an air inlet channel during high-speed flight, and supplies air through an onboard compressed air cylinder during insufficient speed or in a static state.
The technical scheme of the invention is that air is introduced into a tangential air inlet of a base of the swirl igniter, swirl gas is formed in a combustion cavity, an electrode holder is connected with a high-voltage power supply, and plasma generated after breakdown moves towards an outlet and is elongated until the plasma is extinguished under the pushing of swirl gas flow, so that continuous sliding arc plasma discharge is formed among the electrode holder, a burner base body and a columnar shell. When fuel oil is fed through the tangential inlet, the sliding arc ignites tangential rotational flow air-fuel mixed gas to form stable strong rotational flow flame under the limitation of the cylindrical shell, the strong rotational flow flame and the sliding arc are sprayed out by the igniter together, and the length and the temperature of the strong rotational flow flame can be adjusted by adjusting the flow of the air and the flow of the tangential fuel.
The strong rotational flow flame formed by tangential injection has high rotational flow number and good stability, and is coupled with the sliding arc jet flow, thereby being beneficial to successfully igniting the main cavity combustion chamber.
Drawings
FIG. 1 is a schematic diagram of a bleed air system for a re-entrant flame holder self-bleed air sliding arc plasma jet igniter and ignition method;
FIG. 2 is a schematic diagram of a re-entrant flame holder self-bleed sliding arc plasma jet igniter 114, where FIG. 2(a) is a side view and FIG. 2(b) is a top view of the self-bleed sliding arc plasma jet igniter 114;
fig. 3 is a schematic diagram of the operational modes of a re-entrant flame holder self-bleed sliding arc plasma jet igniter and ignition method, where fig. 3(a) is mode a and fig. 3(b) is mode b.
Reference numerals:
an air inlet channel 101, a combustion chamber 102, a concave cavity stabilizer 103, a bleed air pipe 111, an air conveying pipeline 112, a bleed air pipeline adjusting valve 113, a self-bleed sliding arc plasma jet igniter 114
Igniter base lower plate 201, igniter base upper plate 202, igniter housing 203, tangential air inlet 204, tangential fuel inlet 205, high voltage electrode 206, electrode insulation base 207
A sliding arc plasma 301 and a strong vortex flame 302 generated by discharge
Detailed Description
The invention is explained in detail below with reference to the figures and with reference to embodiments.
The present invention provides a re-entrant flame holder self-bleeding sliding arc plasma jet igniter (hereinafter referred to as "igniter"). During ignition, the igniter can be switched between two modes of sliding arc ignition and sliding arc strong vortex flame coupling. The sliding arc strong swirl flame coupling mode can further overcome the defect of small energy when the sliding arc plasma exciter is used for ignition through the coupling amplification effect of the sliding arc strong swirl flame, optimizes the ignition effect, improves the fire capability of the concave cavity flame stabilizer and widens the stable working range of the igniter.
As shown in fig. 1(a), the igniter is cylindrical in shape as a whole, and includes an igniter base lower plate 201, an igniter base upper plate 202, an igniter housing 203, a tangential air inlet 204, a tangential fuel inlet 205, a high voltage electrode 206, and a cylindrical electrode insulation base 207. The igniter base upper plate 202 is shaped as a hollow circular ring-shaped flat plate. The igniter base lower plate 201 is also a hollow ring structure. 201. 202 have the same inner diameter and the same or different outer diameters. The igniter housing 203 is a hollow cylindrical metal or ceramic tube, the bottom part of the igniter housing is tightly and fixedly connected with the inner side of the igniter base upper plate 202 through connecting means such as threads, glue or bayonet, the top part of the igniter housing is fixedly connected with the bottom part of the cavity flame stabilizer 103 through connecting means such as threads, glue or bayonet, and the igniter housing 203 is communicated with the inside of the cavity flame stabilizer 103. The tangential air inlets 204 and the tangential fuel inlets 205 are independent stainless steel round pipes and are alternately distributed on the same horizontal plane at intervals, the tangential air inlets 204 and the tangential fuel inlets 205 are vertically clamped by the igniter base lower plate 201 and the igniter base upper plate 202 and are fixed between the igniter base lower plate 201 and the igniter base upper plate 202 in a bolt or welding mode, for example, and outlets (i.e., openings leading to the inside of the igniter shell 203) of the tangential air inlets 204 and the tangential fuel inlets 205 are in the shape of vertical slits or round holes; the outlets of the tangential air inlets 204 and the outlets of the tangential fuel inlets 205 are equal in number and arranged alternately, as shown in fig. 1 (b); the air and fuel flow from the tangential air inlet 204 and the tangential fuel inlet 205 are both tangential to the inside circumference of the igniter housing 203; the air flowing in from the tangential air inlet 204 provides a working air source for mainly the sliding arc; the tangential fuel inlet 205 is connected to an oil supply system for supplying fuel to the igniter. A cylindrical electrode insulator mount 207 is concentrically mounted in the middle of the hollow ring of the igniter base lower plate 201 by means of a mounting means such as threads or snaps. The lower end of the high voltage electrode 206 is connected to the high voltage end of the igniter power supply and the upper end of the high voltage electrode passes through the center of the cylindrical electrode insulator base 207 and extends into the igniter housing 203 to the middle of the igniter housing 203.
As shown in fig. 2, the re-entrant flame holder self-bleed sliding arc plasma jet ignition device of the present invention comprises: a bleed air pipe 111, an air conveying pipe 112, a bleed air pipe regulating valve 113 and an igniter 114. The intake port 101 (not included in the present invention), the scramjet combustor 102 (not included in the present invention), and the re-entrant flame stabilizer 103 (not included) in the scramjet combustor are shown as being added to fig. 2 as an essential part of the supplementary explanation. The intake passage 101 is a common scramjet intake passage. The bleed air pipe 111 is a hollow metal elbow with an inlet perpendicular to the incoming flow direction and an outlet fixedly connected to the air line 112, for example by threading or welding. The bleed air conduit 111 inlet introduces air from the main flow in a total pressure pick-up manner and the air flow flows through the outlet into the air delivery conduit 112. A bleed air line regulating valve 113 is installed in the air line 112 to regulate the flow rate in the air line in an electrically controlled manner. The outlet of the air delivery conduit 112 is provided with a one-to-N connection that divides the air from the air delivery conduit 112 into N outputs that are respectively connected to each of the tangential air inlets 204 by, for example, welding or screwing, so that the number of N is the number of tangential air inlets 204.
In one embodiment of the invention, the igniter housing 203 is a hollow cylindrical metal or ceramic tube, preferably a ceramic material; the inner diameter phi of the igniter shell 203 is 10mm-20mm, and preferably 16 mm; the height ranges from 30 to 100mm, preferably 40 mm. The bottom of the igniter housing 203 is fixedly attached to the igniter base upper plate 202, such as by welding, and the top of the igniter housing 203 is fixedly attached to the bottom of the re-entrant flame holder 103, such as by threading, which is well known to those skilled in the art and will not be described in detail. The tangential fuel inlet 205 is connected to the oil supply system by a phi 1mm-4mm oil supply pipe, preferably 2 mm. The joint surface of the igniter base lower plate 201 and the igniter base upper plate 202 is provided with grooves which are suitable for the tangential shapes of the tangential air inlet 204 and the tangential fuel inlet 205, so that the tangential air inlet 204 and the tangential fuel inlet 205 can pass through the grooves and lead to the inside of the igniter shell 203; in one embodiment of the invention, the joining surfaces of the igniter base lower plate 201 and the igniter base upper plate 202 are each formed with a semicircular groove having a corresponding size, and the igniter base lower plate 201 and the igniter base upper plate 202 fix the tangential air inlet 204 and the tangential fuel inlet 205 in the grooves by, for example, welding. The outlet of the tangential air inlet 204 is in the shape of a slit or a round hole, is tangential to the round cavity on the inner side of the igniter shell 203 (as described above), and is a slit with the height of 1-5mm and the width of 0.5-2mm, preferably a slit with the height of 3mm and the width of 1 mm; when the circular hole is a circular hole, the circular hole has a radius of 1-4mm, and preferably a circular hole with a radius of 2 mm. The inner side outlet of the tangential fuel inlet 205 is in the shape of a slit or a round hole, and when the slit is formed, the slit is 0.5-3mm high and 0.1-2mm wide, and preferably 1mm high and 0.3mm wide; when the diameter of the circular hole is 0.1-2mm, the diameter of the circular hole is preferably 0.3 mm. The number of the outlets of the tangential air inlets 204 and the outlets of the tangential fuel inlets 205 are equal and are arranged at equal intervals, or the tangential fuel inlets 205 are tightly attached to the downstream of the outlets of the tangential air inlets 204, preferably, the outlets of the tangential air inlets 204 and the outlets of the tangential fuel inlets 205 are arranged at equal intervals; the total number of tangential air inlets 204 is 2-6, preferably 4; the total number of tangential fuel inlets 205 is 2-6, preferably 4. The cylindrical electrode insulator mount 207 is made of ceramic, preferably zirconia ceramic, and is concentrically mounted, such as by threading or snapping, in the middle of the igniter base lower plate 201, preferably by M16x1mm threading. The high voltage electrode 206 is made of a metal, preferably a superalloy, threaded or snapped through the center of 207 and into the middle of the igniter housing 203, preferably by M10x1mm threads, 0-40mm, preferably 30mm, into the igniter housing 203. The outer diameter of the high voltage electrode 206 is 6-10mm, preferably 10 mm.
In one embodiment of the present invention, the inlet of the bleed air pipe 111 may be selectively installed on the wall of the isolation section or the air inlet, preferably on the wall of the air inlet. The diameter of the bleed air pipe 111 is 4mm to 10mm, preferably 6 mm. The diameter of the gas transmission pipeline 112 is phi 4mm-10mm, preferably 6 mm. The bleed air tube 111 is fixedly connected to the air line 112, for example by means of a thread or by welding, preferably by means of a threaded bayonet coupling. The bleed air line regulating valve 113 is fixedly connected with the air line 112 by means of, for example, threads or welding, preferably by means of a threaded sleeve. The outlet of the air delivery pipeline 112 is provided with a one-to-N joint, the bleed air is divided into N paths by the one-to-N joint, preferably N-4, and each path is fixedly connected with the tangential air inlet 204 of the igniter 114, preferably by a phi 4mm corrugated pipe, for example, by welding or screwing, and preferably by a threaded sleeve.
The ignition method of the igniter of the invention is shown in figure 3, the ignition working mode of the device is determined by the working condition requirement of the cavity flame stabilizer, and the ignition working mode comprises a mode and a mode.
Mode a. single sliding arc ignition mode involving only tangential air feed
Mode b Co-ignition mode involving tangential fuel flame and sliding arc
In mode a operation, the bleed air line regulator 113 is opened, and air flowing in from the bleed air line 111 at the total pressure flows through the air line 112 into the tangential air inlet 204, and since the outlet of the tangential air inlet 204 is a slit or a circular hole with a small size, the gas flowing out from the outlet forms a tangential air flow with a high speed inside the igniter housing 203 and moves in a spiral trajectory toward the outlet of the igniter housing 203 under the constraint of the igniter housing 203. The igniter shell 203 is connected with the low-pressure end of the igniter power supply through a lead, the igniter power supply is turned on, electric discharge is carried out between the high-voltage electrode 206 and the igniter shell 203 to form plasma, the plasma moves towards the outlet of the igniter shell 203 under the blowing of tangential spiral airflow to form sliding arc plasma 301 generated by electric discharge, and the sliding arc plasma 301 is sprayed out of the igniter outlet to ignite the concave cavity flame stabilizer.
In mode b operation, the bleed air line regulator 113 is opened and air flowing from the bleed air line 111 at total pressure flows through the air line 112 into the tangential air inlet 204, and because the outlet of the tangential air inlet 204 is a slit or circular hole of relatively small size, the gas flowing from the outlet forms a relatively high velocity tangential air flow inside the igniter housing 203 and travels in a spiral path toward the outlet under the constraint of the igniter housing 203. The fuel oil entering from the tangential fuel inlet 205 is atomized and sprayed into the inner side of the igniter through the outlet circular hole, and is mixed with the tangential air to form combustible mixed gas. The igniter shell 203 is connected with the low-pressure end of the igniter power supply through a lead, the igniter power supply is turned on, the discharge is formed between the high-voltage electrode 206 and the igniter shell 203, the plasma moves towards the igniter outlet under the blowing of the tangential spiral airflow, the sliding arc plasma 301 generated by the discharge is formed, and the sliding arc plasma 301 is sprayed out of the igniter outlet. The sliding arc plasma 301 simultaneously ignites the combustible mixed gas in spiral motion to form strong swirl flame 302, the tail end of the flame and high-temperature gas are sprayed out from an igniter outlet, and in addition, air entering tangentially can form an air film on the inner wall of a cylindrical shell of the igniter shell 203 to play a role in protecting the tube wall. The sliding arc plasma 301 in combination with the highly swirling flame 302 ignites the re-entrant flame holder.
The above embodiments are only used to help understand the method of the present invention and its core idea. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (10)
1. The cavity flame stabilizer self-bleed sliding arc plasma jet igniter is characterized in that the igniter is integrally cylindrical and comprises an igniter base lower plate (201), an igniter base upper plate (202), an igniter shell (203), a tangential air inlet (204), a tangential fuel inlet (205), a high-voltage electrode (206) and a cylindrical electrode insulating base (207); wherein
The igniter shell (203) is a hollow cylindrical tube, the top of the igniter shell is fixedly connected with the bottom of the cavity flame stabilizer (103), and the igniter shell (203) is communicated with the inside of the cavity flame stabilizer (103);
the shape of the igniter base upper plate (202) is a hollow circular ring-shaped flat plate; the lower plate (201) of the igniter base is also of a hollow circular ring structure, and the inner diameters of the lower plate and the inner diameter of the lower plate are the same; the inner wall of a circular ring of the igniter base upper plate (202) wraps the outer wall of the bottom of the igniter shell (203) and continuously extends downwards, and the igniter base lower plate (201) is arranged next to the igniter base upper plate (202), is positioned below the igniter base upper plate and is fixedly connected with the igniter base upper plate; through holes leading to the inside of the igniter shell (203) are machined at the junction of the igniter base lower plate (201) and the igniter base upper plate (202), the shape and the size of each through hole are determined by the external size of a round pipe used by the corresponding tangential air inlet (204) and the tangential fuel inlet (205), the number of the through holes is determined by the number of the tangential air inlets (204) and the tangential fuel inlets (205), and the axes of the opening directions of the through holes are parallel to the tangential direction of the inner side circumference of the igniter shell (203); respectively processing half through holes at corresponding positions of an igniter base upper plate (202) and an igniter base lower plate (201), wherein the upper edge of the through hole processed on the igniter base upper plate (202) is flush with the lower edge of an igniter shell (203);
the tangential air inlets (204) and the tangential fuel inlets (205) are independent round pipes, the number of outlets of the tangential air inlets (204) is equal to that of outlets of the tangential fuel inlets (205), the outlets are alternately distributed on the same horizontal plane at intervals, and the tangential air inlets (204) and the tangential fuel inlets (205) are vertically clamped by the igniter base lower plate (201) and the igniter base upper plate (202) and are fixedly arranged between the igniter base lower plate (201) and the igniter base upper plate (202); the tangential air inlet (204) and the tangential fuel inlet (205) are tangential to the inner circumference of the igniter shell (203) along the air and fuel directions flowing from the tangential air inlet (204) and the tangential fuel inlet (205);
the cylindrical electrode insulation base (207) is concentrically arranged in the middle of the hollow circular ring of the igniter base lower plate (201) and is wrapped by the inner wall of the circular ring of the igniter base lower plate (201);
the lower end of the high-voltage electrode (206) is connected with the high-voltage end of the igniter power supply, and the upper end of the high-voltage electrode penetrates through the center of the cylindrical electrode insulating base (207) and extends into the igniter shell (203).
2. The plasma jet igniter of claim 1 wherein the igniter housing (203) is a metal or ceramic tube; the tangential air inlet (204) and the tangential fuel inlet (205) are both stainless steel round pipes and are uniformly spaced on the same horizontal plane, and the outlets of the tangential air inlet (204) and the tangential fuel inlet (205) are round holes or are processed into slits on the basis of the round pipes; the upper end of the high-voltage electrode (206) passes through the center of the cylindrical electrode insulation base (207) and reaches the middle part of the igniter shell (203).
3. The plasma jet igniter of claim 1, wherein the igniter housing (203) is a metal or ceramic tube, the igniter housing (203) having an inner diameter of 10mm to 20mm and a height in the range of 30mm to 100 mm; the total number of the tangential air inlets (204) is 2-6; the total number of tangential fuel inlets (205) is 2-6; the insulating material of the cylindrical electrode insulating base (207) is ceramic; the high-voltage electrode (206) extends into the igniter shell (203) by 0-40mm, and the outer diameter of the high-voltage electrode (206) is 6-10 mm.
4. The plasma jet igniter of claim 3, wherein the igniter housing (203) is a ceramic tube, the igniter housing (203) having an inner diameter of 16mm and a height of 40 mm; the total number of the tangential air inlets (204) is 4; the total number of tangential fuel inlets (205) is 4; the insulating material of the cylindrical electrode insulating base (207) is zirconia ceramic; the high voltage electrode (206) extends into the igniter shell (203) by 30mm, and the outer diameter of the high voltage electrode (206) is 10 mm.
5. The plasma jet igniter of claim 3, wherein the outlet of the tangential air inlet (204) is in the form of a vertical slit having a height of 1-5mm and a width of 0.5-2mm when the slit is formed; when the circular hole is formed, the circular hole is formed with the radius of 1-4 mm; when the shape of the inner side outlet of the tangential fuel inlet (205) is a slit, the tangential fuel inlet is a vertical slit with the height of 0.5-3mm and the width of 0.1-2 mm; when the diameter is round, the diameter is 0.1-2 mm.
6. The plasma jet igniter of claim 5, wherein the outlet of the tangential air inlet (204) is in the form of a slit having a height of 3mm and a width of 1 mm; when the circular hole is a circular hole, the circular hole has a radius of 2 mm; when the shape of the inner side outlet of the tangential fuel inlet (205) is a slit, the slit is 1mm high and 0.3mm wide; when the diameter is a circular hole, the diameter is 0.3 mm.
7. Reentrant flame holder is from bleed sliding arc plasma efflux ignition, its characterized in that includes: a bleed air pipe (111), an air conveying pipeline (112), a bleed air pipeline regulating valve (113) and an igniter (114); the air guide pipe (111) is a hollow metal elbow, an inlet is vertical to the incoming flow direction, and an outlet is fixedly connected with the air transmission pipeline (112); the air is introduced from the main flow by the inlet of the bleed air pipe (111) in a total pressure collection mode, and the airflow flows into the air conveying pipeline (112) through the outlet; an air-bleed pipeline regulating valve (113) is arranged in the air transmission pipeline (112) and used for regulating the flow in the air transmission pipeline in an electric control mode; the outlet of the air transmission pipeline (112) is provided with a one-to-N connector which divides the air from the air transmission pipeline (112) into N outputs, and the N outputs are respectively and fixedly connected with the inlet of each tangential air inlet (204) of the igniter (114), so that the number of N is the number of the tangential air inlets (204).
8. The plasma jet ignition device of claim 7, characterized in that the inlet of the bleed air pipe (111) is selectively installed on the wall surface of the isolated section or the inlet channel; the diameter of the air-entraining pipe (111) is 4mm-10 mm; the diameter of the gas transmission pipeline (112) is 4mm-10 mm.
9. Plasma jet ignition device according to claim 8, characterized in that the inlet of the bleed air duct (111) is mounted to the inlet channel wall; the diameter of the air guide pipe (111) is 6 mm; the diameter of the gas transmission pipeline (112) is 6 mm; n is 4.
10. The self-air-entraining sliding arc plasma jet ignition method of the concave cavity flame stabilizer is characterized in that the ignition working mode of the device is determined by the working condition requirement of the concave cavity flame stabilizer, and the ignition working mode has two modes, namely a mode and b mode;
mode a. single sliding arc ignition mode involving only tangential air feed
Mode b Co-ignition mode involving tangential fuel flame and sliding arc
In the mode a, when the air-guiding pipeline adjusting valve (113) is opened, air flowing in from the air-guiding pipeline (111) at the total pressure flows into the tangential air inlet (204) through the air conveying pipeline (112), and because the outlet of the tangential air inlet (204) is a slit or a round hole with a smaller size, gas flowing out of the outlet forms a tangential airflow with higher speed on the inner side of the igniter shell (203) and moves towards the outlet of the igniter shell (203) in a spiral track under the constraint of the igniter shell (203); the igniter shell (203) is connected with the low-voltage end of the igniter power supply through a lead, the igniter power supply is turned on, discharge is carried out between the high-voltage electrode (206) and the igniter shell (203) to form plasma, the plasma moves towards the outlet of the igniter shell (203) under the blowing of tangential spiral airflow to form sliding arc plasma (301) generated by discharge, and the sliding arc plasma (301) is sprayed out of the outlet of the igniter to ignite the flame stabilizer in the concave cavity;
in the mode b, when the air-guiding pipeline adjusting valve (113) is opened, air flowing in from the air-guiding pipeline (111) at the total pressure flows into the tangential air inlet (204) through the air conveying pipeline (112), and because the outlet of the tangential air inlet (204) is a slit or a round hole with a smaller size, gas flowing out of the outlet forms a tangential airflow with higher speed on the inner side of the igniter shell (203) and moves towards the outlet in a spiral track under the constraint of the igniter shell (203); fuel oil entering from the tangential fuel inlet (205) is atomized and sprayed into the inner side of the igniter through the round hole of the outlet and is mixed with tangential air to form combustible mixed gas; the igniter shell (203) is connected with the low-voltage end of the igniter power supply through a lead, the igniter power supply is turned on, the discharge is formed between the high-voltage electrode (206) and the igniter shell (203), the plasma moves towards the igniter outlet under the blowing of the tangential spiral airflow to form sliding arc plasma (301) generated by the discharge, and the sliding arc plasma (301) is ejected out of the igniter outlet; the sliding arc plasma (301) simultaneously ignites the combustible mixed gas in spiral motion to form strong swirl flame (302), the tail end of the flame and high-temperature fuel gas are sprayed out from an igniter outlet, and in addition, air entering tangentially can form an air film on the inner wall of a cylindrical shell of an igniter shell (203) to play a role in protecting the tube wall; the re-entrant flame holder is ignited by the interaction of a sliding arc plasma (301) and a highly swirled flame (302).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110233589.XA CN113217196B (en) | 2021-03-03 | 2021-03-03 | Self-air-entraining sliding arc plasma jet igniter of concave cavity flame stabilizer and ignition method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110233589.XA CN113217196B (en) | 2021-03-03 | 2021-03-03 | Self-air-entraining sliding arc plasma jet igniter of concave cavity flame stabilizer and ignition method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113217196A true CN113217196A (en) | 2021-08-06 |
| CN113217196B CN113217196B (en) | 2022-09-20 |
Family
ID=77084810
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110233589.XA Active CN113217196B (en) | 2021-03-03 | 2021-03-03 | Self-air-entraining sliding arc plasma jet igniter of concave cavity flame stabilizer and ignition method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113217196B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113623685A (en) * | 2021-09-10 | 2021-11-09 | 中国航发湖南动力机械研究所 | Swirler structure for ignition of rotating sliding arc |
Citations (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1071785A (en) * | 1962-11-27 | 1967-06-14 | Ass Elect Ind | Improvements relating to electric igniters for jet engines |
| US4766855A (en) * | 1983-07-20 | 1988-08-30 | Cummins Engine Co., Inc. | Plasma jet ignition apparatus |
| WO2003041854A1 (en) * | 2001-08-02 | 2003-05-22 | Plasmasol Corp. | Electrode discharge, non thermal plasma device (reactor) for the pre-treatment of combustion air |
| US20040031257A1 (en) * | 2002-08-13 | 2004-02-19 | Schmotolocha Stephen N. | Torch igniter |
| US20040206089A1 (en) * | 2003-04-18 | 2004-10-21 | Venkataramani Kattalaicheri Srinivasan | Integral pulse detonation system for a gas turbine engine |
| CN1675501A (en) * | 2002-08-09 | 2005-09-28 | 杰富意钢铁株式会社 | Tubular flame burner and method for controlling combustion |
| US20070196249A1 (en) * | 2003-06-20 | 2007-08-23 | Alexander Fridman | Vortex reactor and method of using it |
| US20120100497A1 (en) * | 2009-06-23 | 2012-04-26 | Sung Ho Joo | Burner using plasma |
| US20140080072A1 (en) * | 2012-09-14 | 2014-03-20 | Eclipse, Inc. | Method and apparatus for a dual mode burner yielding low nox emission |
| WO2014148804A1 (en) * | 2013-03-22 | 2014-09-25 | 한국기계연구원 | Plasma burner |
| CN104879780A (en) * | 2014-02-28 | 2015-09-02 | 北京大学 | Multichannel plasma area igniting burner |
| US20160244683A1 (en) * | 2013-10-10 | 2016-08-25 | Plasco Energy Group Inc. | A Non-Equilibrium Plasma-Assisted Method and System for Reformulating and/or Reducing Tar Concentration in Gasification Derived Gas Product |
| CN107218623A (en) * | 2017-05-25 | 2017-09-29 | 航天神洁（北京）环保科技有限公司 | A kind of sliding arc auxiliary combustion equipment for producing atmospheric non-equilibrium plasma |
| CN107420199A (en) * | 2017-03-31 | 2017-12-01 | 中国人民解放军空军工程大学 | The combustion-supporting driver of aeroengine combustor buring room rotational slide arc plasma |
| CN107842427A (en) * | 2017-10-30 | 2018-03-27 | 西安交通大学 | A kind of preheating type plasma igniter and ignition method |
| CN108005790A (en) * | 2017-11-29 | 2018-05-08 | 中国人民解放军空军工程大学 | Based on the aero-engine plasma jet igniter from bleed |
| CN207745881U (en) * | 2017-09-29 | 2018-08-21 | 清华大学 | It is a kind of to strengthen mixed atomization flame nano particle synthesis system based on more eddy flows |
| CN110145400A (en) * | 2019-05-21 | 2019-08-20 | 大连民族大学 | A kind of double mode plasma igniter |
| CN110439691A (en) * | 2019-08-06 | 2019-11-12 | 中国人民解放军空军工程大学 | Plasma flame on duty igniter based on aeroengine thrust augmentation combustion chamber |
| CN110886657A (en) * | 2019-10-30 | 2020-03-17 | 北京动力机械研究所 | Plasma ignition system of air-breathing engine |
| CN111120112A (en) * | 2019-12-04 | 2020-05-08 | 中国人民解放军空军工程大学 | Multi-anode sliding arc plasma igniter based on combustion chamber secondary flow and ignition method |
| US20200224877A1 (en) * | 2016-10-21 | 2020-07-16 | Fgc Plasma Solutions | Apparatus and method for using plasma to assist with the combustion of fuel |
| CN111734532A (en) * | 2020-06-21 | 2020-10-02 | 中国人民解放军空军工程大学 | Filament arc plasma exciter based on swirl hole |
-
2021
- 2021-03-03 CN CN202110233589.XA patent/CN113217196B/en active Active
Patent Citations (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1071785A (en) * | 1962-11-27 | 1967-06-14 | Ass Elect Ind | Improvements relating to electric igniters for jet engines |
| US4766855A (en) * | 1983-07-20 | 1988-08-30 | Cummins Engine Co., Inc. | Plasma jet ignition apparatus |
| WO2003041854A1 (en) * | 2001-08-02 | 2003-05-22 | Plasmasol Corp. | Electrode discharge, non thermal plasma device (reactor) for the pre-treatment of combustion air |
| CN1675501A (en) * | 2002-08-09 | 2005-09-28 | 杰富意钢铁株式会社 | Tubular flame burner and method for controlling combustion |
| US20040031257A1 (en) * | 2002-08-13 | 2004-02-19 | Schmotolocha Stephen N. | Torch igniter |
| US20040206089A1 (en) * | 2003-04-18 | 2004-10-21 | Venkataramani Kattalaicheri Srinivasan | Integral pulse detonation system for a gas turbine engine |
| US20070196249A1 (en) * | 2003-06-20 | 2007-08-23 | Alexander Fridman | Vortex reactor and method of using it |
| US20120100497A1 (en) * | 2009-06-23 | 2012-04-26 | Sung Ho Joo | Burner using plasma |
| US20140080072A1 (en) * | 2012-09-14 | 2014-03-20 | Eclipse, Inc. | Method and apparatus for a dual mode burner yielding low nox emission |
| WO2014148804A1 (en) * | 2013-03-22 | 2014-09-25 | 한국기계연구원 | Plasma burner |
| US20160244683A1 (en) * | 2013-10-10 | 2016-08-25 | Plasco Energy Group Inc. | A Non-Equilibrium Plasma-Assisted Method and System for Reformulating and/or Reducing Tar Concentration in Gasification Derived Gas Product |
| CN104879780A (en) * | 2014-02-28 | 2015-09-02 | 北京大学 | Multichannel plasma area igniting burner |
| US20200224877A1 (en) * | 2016-10-21 | 2020-07-16 | Fgc Plasma Solutions | Apparatus and method for using plasma to assist with the combustion of fuel |
| CN107420199A (en) * | 2017-03-31 | 2017-12-01 | 中国人民解放军空军工程大学 | The combustion-supporting driver of aeroengine combustor buring room rotational slide arc plasma |
| CN107218623A (en) * | 2017-05-25 | 2017-09-29 | 航天神洁（北京）环保科技有限公司 | A kind of sliding arc auxiliary combustion equipment for producing atmospheric non-equilibrium plasma |
| CN207745881U (en) * | 2017-09-29 | 2018-08-21 | 清华大学 | It is a kind of to strengthen mixed atomization flame nano particle synthesis system based on more eddy flows |
| CN107842427A (en) * | 2017-10-30 | 2018-03-27 | 西安交通大学 | A kind of preheating type plasma igniter and ignition method |
| CN108005790A (en) * | 2017-11-29 | 2018-05-08 | 中国人民解放军空军工程大学 | Based on the aero-engine plasma jet igniter from bleed |
| CN110145400A (en) * | 2019-05-21 | 2019-08-20 | 大连民族大学 | A kind of double mode plasma igniter |
| CN110439691A (en) * | 2019-08-06 | 2019-11-12 | 中国人民解放军空军工程大学 | Plasma flame on duty igniter based on aeroengine thrust augmentation combustion chamber |
| CN110886657A (en) * | 2019-10-30 | 2020-03-17 | 北京动力机械研究所 | Plasma ignition system of air-breathing engine |
| CN111120112A (en) * | 2019-12-04 | 2020-05-08 | 中国人民解放军空军工程大学 | Multi-anode sliding arc plasma igniter based on combustion chamber secondary flow and ignition method |
| CN111734532A (en) * | 2020-06-21 | 2020-10-02 | 中国人民解放军空军工程大学 | Filament arc plasma exciter based on swirl hole |
Non-Patent Citations (3)
| Title |
|---|
| 于锦禄等: "等离子体点火与助燃技术在航空发动机上的应用", 《航空发动机》 * |
| 冯戎等: "多路滑动弧的放电特性实验研究", 《高电压技术》 * |
| 刘雄等: "直流滑动弧等离子体点火器特性的实验研究", 《推进技术》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113623685A (en) * | 2021-09-10 | 2021-11-09 | 中国航发湖南动力机械研究所 | Swirler structure for ignition of rotating sliding arc |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113217196B (en) | 2022-09-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108005790B (en) | Aero-engine plasma jet igniter based on self-air-entraining | |
| US4303386A (en) | Parallel flow burner | |
| CN106438158B (en) | Aero-engine main chamber based on plasma jet ignition | |
| CN109057972A (en) | A kind of preheating type aero-engine plasma igniter | |
| CN113217196B (en) | Self-air-entraining sliding arc plasma jet igniter of concave cavity flame stabilizer and ignition method | |
| JPH0325685B2 (en) | ||
| CN112963273B (en) | Self-air-entraining kerosene pre-combustion cracking activation device and method for concave cavity flame stabilizer | |
| RU2605166C2 (en) | Universal mixing head swirl atomizer for gas burner | |
| JPH08502810A (en) | burner | |
| RU131455U1 (en) | BURNER | |
| CA1142576A (en) | High stability gas-electric pilot-ignitor | |
| CN115288861A (en) | Self-air-leading kerosene pre-burning type plasma jet igniter | |
| RU2396488C1 (en) | Burner for gas burning | |
| CN110793060B (en) | Controllable plasma igniter in atmospheric pressure environment | |
| RU2152558C1 (en) | Burner | |
| CN105783031A (en) | Integrated plasma exciter, nozzle array and burner | |
| RU2515909C2 (en) | Gas turbine engine annular low-emission combustion chamber | |
| RU2216690C2 (en) | Facility to ignite pulverized coal fuel | |
| WO1998001703A2 (en) | Turbo-flame burner design | |
| CN110173687A (en) | A kind of combustion gas air register and burner | |
| RU2216689C1 (en) | Burning facility | |
| RU2406934C1 (en) | Air-and-fuel burner of combustion chamber of gas turbine engine | |
| CN114922756B (en) | Electronic fuel injection system of motorcycle | |
| CN220017367U (en) | Coal and oil mixed burner | |
| US20240125468A1 (en) | Burners and components for use in burners |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |