CN107091474A - Ignition burner device - Google Patents
Ignition burner device Download PDFInfo
- Publication number
- CN107091474A CN107091474A CN201710400304.0A CN201710400304A CN107091474A CN 107091474 A CN107091474 A CN 107091474A CN 201710400304 A CN201710400304 A CN 201710400304A CN 107091474 A CN107091474 A CN 107091474A
- Authority
- CN
- China
- Prior art keywords
- combustion chamber
- nozzle wall
- nozzle
- ignition burner
- gas
- 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.)
- Withdrawn
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/48—Nozzles
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Abstract
A kind of ignition burner device, including nozzle wall cylinder and blast tube, combustion chamber is formed in the nozzle wall cylinder, the nozzle wall cylinder includes front-end and back-end opposite in the axial direction, the blast tube be arranged on nozzle wall cylinder front end and with the combustion chamber, the blast tube for one to treat that firing device is lighted a fire, in addition to hagioscope, the hagioscope is arranged on the nozzle wall tube rear end, so that cause can be by the hagioscope it was observed that the combustion chamber and treating the inside of firing device.The ignition burner apparatus structure of the present invention is simple, easy for installation, practical, suitable for popularization and application.
Description
Technical field
The present invention relates to a kind of ignition burner, more particularly to one kind can spy on ignition burner device.
Background technology
Its combustion chamber of existing ignition burner is mostly totally-enclosed installation, and the burning in combustion chamber can not be observed from the external world
After situation, firing action, it can not be made for igniting success or not and accurately judge and control.
The content of the invention
In view of this, the present invention proposes a kind of ignition burner device for spying on ignition burner flame combustion position.
The present invention provides in a kind of ignition burner device, including nozzle wall cylinder and blast tube, the nozzle wall cylinder and forms combustion
Room is burnt, the nozzle wall cylinder includes front-end and back-end opposite in the axial direction, and the blast tube is arranged on before nozzle wall cylinder
Hold and with the combustion chamber, the blast tube for one to treat that firing device is lighted a fire, in addition to hagioscope, the hagioscope
The nozzle wall tube rear end is arranged on, so that cause can be by the hagioscope it was observed that the combustion chamber and treating in firing device
Portion.
In one embodiment, the nozzle wall cylinder includes nozzle inner walls and the outer nozzle wall diametrically separated, the spray
The combustion chamber is formed in mouth inwall, the air flow channel with ft connection, institute are formed between the nozzle inner walls and outer nozzle wall
If nozzle inner walls are stated provided with dry hole, if to cause the air flow channel to pass through the dry hole and the combustion chamber.
In one embodiment, the nozzle wall cylinder is provided with through the outer nozzle wall and the fuel air of nozzle inner walls dress
Put, the fuel air device is to provide fuel gas into the combustion chamber, and the fuel air device is close to the nozzle
The rear end of wall cylinder, the injection direction of the fuel air device deviates the diametric(al) of the nozzle wall cylinder so that the fuel
The combustion gas that inlet duct is ejected strikes the internal face of combustion chamber, so as to circumferentially form the combustion gas of rotation along the combustion chamber
Flow field.
In one embodiment, the nozzle inner walls are provided with end plate, the blast tube in the side of nozzle wall cylinder front end
It is arranged on the end plate, the blast tube includes inlet end and firing tip, the inlet end and the combustion chamber, described
Firing tip treats that firing device is connected with described.
In one embodiment, described to treat that firing device is gas turbine, the gas turbine includes gas-turbine combustion chamber,
The firing tip of the blast tube, which is stretched into, thinks that it is lighted a fire in the gas-turbine combustion chamber.
In one embodiment, the hagioscope includes transparent panel and the transparent panel is fixed into the nozzle wall cylinder
The fixing device of rear end.
In one embodiment, the fixing device is to be arranged at the fixed plate on the outside of the transparent panel, and the fixed plate is certainly
Its outer rim is extends in the vertical direction out two-stage step, including first order step and second level step, and the transparent panel is embedded in institute
In the groove for stating the formation of first order step, the second level step is fixedly connected with the outer nozzle wall, is set in the fixed plate
There is the peep-hole the intermediate region of the transparent panel to be exposed.
In one embodiment, be screwed connection between the second level step and the outer nozzle wall.
In one embodiment, if being uniformly distributed in circumference of the dry hole along the nozzle inner walls, if the dry hole includes
The many collar aperture arranged vertically.
In one embodiment, the transparent panel is suprasil piece.
In summary, the present invention provides a kind of ignition burner device spied on, by being installed in the rear end of nozzle wall cylinder
One transparent panel so that staff can observe the flame in ignition burner combustion chamber by the transparent panel when ignition burner works
Combustion position, and real-time judge is made according to combustion position.Transparent panel and blast tube coaxial line are installed, the firing tip of blast tube
It is connected with gas-turbine combustion chamber and thinks that its is lighted a fire so that by transparent panel it can also be seen that flame in gas-turbine combustion chamber
Combustion case, more intuitively pre- test and appraisal are carried out to the running status of gas turbine according to the briliancy of combustion flame, stability etc.
Estimate, so as to realize the accurate control to gas turbine, stabilize it operation, reduce contingency occurrence probability.The point fire-fighting of the present invention
Mouth apparatus structure is simple, easy for installation, practical, suitable for popularization and application.
Brief description of the drawings
Fig. 1 is the axial sectional view of ignition burner device of the present invention.
Fig. 2 is the radial cross-section of ignition burner device of the present invention.
Embodiment
Before describing the embodiments in more detail, it should be understood that the invention is not restricted to institute hereafter or in accompanying drawing in the application
The detailed construction or arrangement of elements of description.The embodiment that the present invention can realize for other manner.Furthermore, it is to be understood that this paper institutes
The wording and term used is solely for describing purposes, should not the explanation of being construed as limiting property." comprising " used herein, "comprising",
The similar wording such as " having " is meant comprising items listed thereafter, its equivalent and other additional things.Particularly, description is worked as
When " certain element ", the quantity that the present invention does not limit the element can also include multiple as one.
As depicted in figs. 1 and 2, the present invention provides a kind of ignition burner device 10, and the ignition burner device 10 includes nozzle
Wall cylinder 12, blast tube 14 and hagioscope 16.Nozzle wall cylinder 12 has opposite front end 18 and rear end 20, nozzle wall cylinder in the axial direction
Combustion chamber 22 is formed in 12, blast tube 14 is arranged on the front end 18 of nozzle wall cylinder 12 and connected with combustion chamber 22, to be treated for one
Firing device is lighted a fire, and for example, the device such as gas turbine, aero-engine, boiler, natural gas vent torch is lighted a fire, and is implemented herein
In example, it is introduced by taking gas turbine as an example.Hagioscope 16 is arranged on the rear end 20 of nozzle wall cylinder 12, so that cause can be by peeping
Form 16 sees the flame combustion situation inside combustion chamber 22 and gas turbine.
In an illustrated embodiment, nozzle wall cylinder 12 includes nozzle inner walls 24 and the outer nozzle wall 26 diametrically separated,
Cavity formation combustion chamber 22 in nozzle inner walls 24, is formed and ignition burner device 10 between nozzle inner walls 24 and outer nozzle wall 26
The air flow channel 28 of ft connection.
If nozzle inner walls 24 are provided with dry hole 30, if air flow channel 28 is connected by dry hole 30 with combustion chamber 22.This implementation
In example, if being uniformly distributed in circumference of the dry hole 30 along nozzle inner walls 24, and multi-turn, such as 3 circles are arranged into vertically.
Air flow channel 28 includes front-end and back-end, and the front end of air flow channel 28 is with for outside air air inlet runner
28, the back-end closure of air flow channel 28, if to cause the air in air inlet runner 28 passes through dry hole 30 to enter in combustion chamber 22
With combustion gas mixing.
Nozzle wall cylinder 12 is provided with the fuel air device 32 through outer nozzle wall 26 and nozzle inner walls 24, fuel air dress
Putting 32 includes fuel air mouthful 33, and air inlet 33 is connected with combustion chamber 22, to provide fuel gas into combustion chamber 22.
Fuel air device 32 is close to the rear end 20 of nozzle wall cylinder 12, the injection direction offset nozzle of fuel air device 32
The diametric(al) of wall cylinder 12 so that the combustion gas that fuel air device 32 is ejected strikes the internal face of combustion chamber 22, so that along combustion
The circumferential gas flow field for forming rotation in room 22 is burnt, while into the combustion gas direction on the whole axially towards blast tube 14 of combustion chamber
It is mobile, promote combustion gas to be mixed with the uniform of air.
In an illustrated embodiment, the end of air inlet 33 is close to the internal face of combustion chamber 22, so that the combustion gas being injected into
It can be rotated along Inner Wall of Combustion Chamber.When air inlet 33 sprays combustion gas into combustion chamber 22, influence of the combustion gas stream in nozzle inner walls 24
Under around nozzle wall cylinder 12 axial direction formation rotation gas flow field, if while uniformly being mixed with the air that enters from dry hole 30
Close, shorten the incorporation time of combustion gas and air, improve ignition effectiveness.
In an illustrated embodiment, nozzle inner walls 24 are provided with end plate 34 in the side of nozzle wall cylinder front end 18, end plate 34
Edge is tightly connected with nozzle inner walls 24, and the middle position of end plate 34 is provided with the through hole worn for blast tube 14, to cause burning
Room 22 is connected with the inside of blast tube 14.Blast tube 14 includes inlet end 36 and firing tip 38, and wherein inlet end 36 is located at combustion chamber
In 22, firing tip 38 is connected to the gas turbine.Specifically, gas turbine includes gas-turbine combustion chamber, blast tube 14
Firing tip 38 stretch into gas-turbine combustion chamber think its light a fire.
It should be appreciated that in above-described embodiment, treat that firing device is embodied as gas turbine only exemplary, in other realities
Apply in example, treat that firing device can also be embodied as other equipment, the present invention is not limited this.
Igniter installation position 39 is additionally provided with nozzle wall cylinder 12, for installing an igniter (not shown), is burnt to entering
Fuel and air mixture in room 22 is lighted.
Hagioscope 16 is arranged on the rear end 20 of nozzle wall cylinder 12, and hagioscope 16 includes transparent panel 17 and consolidates transparent panel 17
The fixing device 40 of the fixed rear end 20 to nozzle wall cylinder 12.In the present embodiment, transparent panel 17 implements into suprasil piece 17, at it
In his embodiment, other transparent materials can also be implemented into.
In an illustrated embodiment, suprasil piece 17 is resisted against outer nozzle wall 26 and nozzle inner walls 24 are located at nozzle wall cylinder
The end of rear end 20, to cause combustion chamber 22 and air flow channel 28 in a side seal of nozzle wall tube rear end 20.Fixing device 40
To be arranged at the fixed plate 40 in the outside of suprasil piece 17, fixed plate 40 is extended from its outer rim along the direction of vertical fixing plate 40
Two-stage step, the two-stage step includes first order step 42 and second level step 44, and the thickness of first order step 42 is more than second
The thickness of level step 44.The inner side of first order step 42 is surrounded to form a groove 46 jointly with the inner surface of fixed plate 40, transparent
Quartz plate 17 is embedded in groove 46, and the inner side of second level step 44 is fixedly connected with outer nozzle wall 26.Fixed plate 40 is provided with
To the peep-hole 48 for exposing the intermediate region of suprasil piece 17, peep-hole 48 is coaxial with blast tube 14, to pass through
Peep-hole 48 and blast tube 14 are observed that the combustion case in gas-turbine combustion chamber.
When ignition burner device 10 works, pass through the observable of peep-hole 48 (for example, taken pictures or imaged by camera)
The situation burnt to the flame of combustion chamber 22.After the completion of igniting, by peep-hole 48 it is observed that in gas-turbine combustion chamber
The situation of subregion flame combustion, such as can directly confirm the briliancy of burned flame, stability, is conducive to combustion gas
The working order of turbine is judged in time, is accurately controlled so as to realize.
In an illustrated embodiment, be screwed connection between second level step 44 and outer nozzle wall 26.Specifically,
The inner side of two stage steps 44 and screw thread of the corresponding outside wall surface of outer nozzle wall 26 provided with mutual cooperation, make it that fixed plate 40 can
It is threadedly coupled by rotation with outer nozzle wall 26, is easy to the installation and removal of ignition burner device 10.In other embodiments,
Two stage steps 44 can also be fixedly connected by other means with outer nozzle wall 26, for example, outside second level step 44 and nozzle
Screw is set on the correspondence position of wall 26, the two is fixedly connected with using screw.
It should be appreciated that in the above-described embodiments, suprasil piece 17 is fixed into nozzle wall cylinder using fixed plate 40
12 rear end 20, in other embodiments, it would however also be possible to employ other fixing devices, the present invention are not limited this.
In summary, the present invention provides a kind of ignition burner device spied on, by being installed in the rear end of nozzle wall cylinder
One hagioscope so that the flame combustion shape in ignition burner combustion chamber can be observed when ignition burner works by the hagioscope
Condition, and real-time judge is made according to combustion position.Transparent panel and blast tube coaxial line are installed, the firing tip of blast tube and combustion gas
The connection of turbine combustion room thinks that its is lighted a fire so that by transparent panel it can also be observed that flame combustion in gas-turbine combustion chamber
Situation, more intuitively forecast assessment is carried out to the running status of gas turbine according to the briliancy of combustion flame, stability etc., from
And the accurate control to gas turbine is realized, operation is stabilized it, reduces contingency occurrence probability.The ignition burner device of the present invention
It is simple in construction, it is easy for installation, it is practical, suitable for popularization and application.
Concepts described herein may be embodied to other forms in the case of without departing from its spirit and characteristic.It is disclosed
Specific embodiment should be considered as exemplary rather than restricted.Therefore, the scope of the present invention be by appended claim,
Rather than be determined according to these descriptions before.Any change in the letter and equivalency range of claim is all
The scope of these claims should be belonged to.
Claims (10)
1. form combustion chamber, the nozzle in a kind of ignition burner device, including nozzle wall cylinder and blast tube, the nozzle wall cylinder
Wall cylinder include front-end and back-end opposite in the axial direction, the blast tube be arranged on the nozzle wall cylinder front end and with the burning
Room is connected, and the blast tube for one to treat that firing device is lighted a fire, it is characterised in that also including hagioscope, the hagioscope is set
Put in the nozzle wall tube rear end, so that cause can be by the hagioscope it was observed that the combustion chamber and treating in firing device
Portion.
2. ignition burner device as claimed in claim 1, it is characterised in that the nozzle wall cylinder includes what is diametrically separated
The combustion chamber, shape between the nozzle inner walls and outer nozzle wall are formed in nozzle inner walls and outer nozzle wall, the nozzle inner walls
Into the air flow channel with ft connection, if the nozzle inner walls are provided with dry hole, if to cause the air flow channel passes through described
Dry hole and the combustion chamber.
3. ignition burner device as claimed in claim 2, it is characterised in that the nozzle wall cylinder, which is provided with, runs through the nozzle
The fuel air device of outer wall and nozzle inner walls, the fuel air device is to provide fuel gas, institute into the combustion chamber
Fuel air device is stated close to the rear end of nozzle wall cylinder, the injection direction of the fuel air device deviates the nozzle wall
The diametric(al) of cylinder so that the combustion gas that the fuel air device is ejected strikes the internal face of combustion chamber, so that along institute
State the gas flow field that combustion chamber circumferentially forms rotation.
4. ignition burner device as claimed in claim 2, it is characterised in that the nozzle inner walls are in nozzle wall cylinder front end
Side be provided with end plate, the blast tube is arranged on the end plate, and the blast tube includes inlet end and firing tip, it is described enter
Gas end and the combustion chamber, the firing tip treat that firing device is connected with described.
5. ignition burner device as claimed in claim 4, it is characterised in that described to treat that firing device is gas turbine, described
Gas turbine includes gas-turbine combustion chamber, and the firing tip of the blast tube, which is stretched into, thinks its point in the gas-turbine combustion chamber
Fire.
6. ignition burner device as claimed in claim 2, it is characterised in that the hagioscope includes transparent panel and will be described
Transparent panel is fixed to the fixing device of the rear end of the nozzle wall cylinder.
7. ignition burner device as claimed in claim 6, it is characterised in that the fixing device is to be arranged at the transparent panel
The fixed plate in outside, the fixed plate is extends in the vertical direction out two-stage step, including first order step and second from its outer rim
Level step, the transparent panel is embedded in the groove of the first order step formation, outside the second level step and the nozzle
Wall is fixedly connected, and the fixed plate is provided with the peep-hole the intermediate region of the transparent panel to be exposed.
8. ignition burner device as claimed in claim 7, it is characterised in that the second level step and the outer nozzle wall it
Between be screwed connection.
9. ignition burner device as claimed in claim 2, it is characterised in that if circumference of the dry hole along the nozzle inner walls
On be uniformly distributed, if the dry hole includes many collar aperture for arranging vertically.
10. the ignition burner device as described in claim 6-9 any one, it is characterised in that the transparent panel is transparent stone
English piece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710400304.0A CN107091474A (en) | 2017-05-31 | 2017-05-31 | Ignition burner device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710400304.0A CN107091474A (en) | 2017-05-31 | 2017-05-31 | Ignition burner device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107091474A true CN107091474A (en) | 2017-08-25 |
Family
ID=59639920
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710400304.0A Withdrawn CN107091474A (en) | 2017-05-31 | 2017-05-31 | Ignition burner device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107091474A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018218528A1 (en) * | 2017-05-31 | 2018-12-06 | 深圳智慧能源技术有限公司 | Ignition nozzle device |
| WO2018218527A1 (en) * | 2017-05-31 | 2018-12-06 | 深圳智慧能源技术有限公司 | Ignition nozzle device capable of improving ignition stability |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2511500A1 (en) * | 1975-03-15 | 1976-09-23 | Smit Nijmegen Bv | Stoichiometric combustion burner - has mechanical fuel atomisation tangential atomising media feed and coaxial laminar feed of air |
| US4860533A (en) * | 1987-09-17 | 1989-08-29 | Prutech Ii | Torch igniter for a combustor having U.V. flame detection |
| US5167116A (en) * | 1989-07-07 | 1992-12-01 | Fuel Systems Textron Inc. | Small airblast fuel nozzle with high efficiency inner air swirler |
| CN2769701Y (en) * | 2004-01-29 | 2006-04-05 | 香港中华煤气有限公司 | Gas burner |
| JP2014503740A (en) * | 2010-12-14 | 2014-02-13 | テイラー，ジャック，アール． | Full expansion internal combustion engine |
| CN103835837A (en) * | 2014-03-07 | 2014-06-04 | 南京航空航天大学 | Thermojet generating device based on rotational flow mixing and continuous combustion of gaseous fuels |
| CN203628650U (en) * | 2013-12-27 | 2014-06-04 | 李兵岗 | High speed burning torch of oil burning boiler |
| CN206875428U (en) * | 2017-05-31 | 2018-01-12 | 深圳智慧能源技术有限公司 | Ignition burner device |
-
2017
- 2017-05-31 CN CN201710400304.0A patent/CN107091474A/en not_active Withdrawn
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2511500A1 (en) * | 1975-03-15 | 1976-09-23 | Smit Nijmegen Bv | Stoichiometric combustion burner - has mechanical fuel atomisation tangential atomising media feed and coaxial laminar feed of air |
| US4860533A (en) * | 1987-09-17 | 1989-08-29 | Prutech Ii | Torch igniter for a combustor having U.V. flame detection |
| US5167116A (en) * | 1989-07-07 | 1992-12-01 | Fuel Systems Textron Inc. | Small airblast fuel nozzle with high efficiency inner air swirler |
| CN2769701Y (en) * | 2004-01-29 | 2006-04-05 | 香港中华煤气有限公司 | Gas burner |
| JP2014503740A (en) * | 2010-12-14 | 2014-02-13 | テイラー，ジャック，アール． | Full expansion internal combustion engine |
| CN203628650U (en) * | 2013-12-27 | 2014-06-04 | 李兵岗 | High speed burning torch of oil burning boiler |
| CN103835837A (en) * | 2014-03-07 | 2014-06-04 | 南京航空航天大学 | Thermojet generating device based on rotational flow mixing and continuous combustion of gaseous fuels |
| CN206875428U (en) * | 2017-05-31 | 2018-01-12 | 深圳智慧能源技术有限公司 | Ignition burner device |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018218528A1 (en) * | 2017-05-31 | 2018-12-06 | 深圳智慧能源技术有限公司 | Ignition nozzle device |
| WO2018218527A1 (en) * | 2017-05-31 | 2018-12-06 | 深圳智慧能源技术有限公司 | Ignition nozzle device capable of improving ignition stability |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20170825 |
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| WW01 | Invention patent application withdrawn after publication |