CN104819466A - Burner of aircraft fire protection testing apparatus - Google Patents
Burner of aircraft fire protection testing apparatus Download PDFInfo
- Publication number
- CN104819466A CN104819466A CN201510212188.0A CN201510212188A CN104819466A CN 104819466 A CN104819466 A CN 104819466A CN 201510212188 A CN201510212188 A CN 201510212188A CN 104819466 A CN104819466 A CN 104819466A
- Authority
- CN
- China
- Prior art keywords
- housing
- lower port
- mixing
- burner
- hybrid network
- 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.)
- Pending
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
- F23D14/62—Mixing devices; Mixing tubes
-
- 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
- F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
- F23D14/78—Cooling burner parts
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The invention belongs to an aviation testing technique and relates to improvement of a burner of aircraft fire protection testing apparatus. The burner comprises a housing (1), a burning chamber (3) and a mixing base (4) and is characterized in that a mixing net module (5) is arranged in a lower port of the housing (1) and located on an air outlet of the mixing base (4), an annular cooling sleeve (7) is arranged on the outer surface of the housing (1), at least three compressed air inlet connecting nozzles (9) evenly distributed in the circumference are formed in the lower surface of the cooling sleeve (7), and a circle of cooling air inlet holes (8) evenly distributed in the circumference are formed in the outer surface of the housing (1). By means of the burner of the improved aircraft fire protection testing apparatus, the flame temperature uniformity of the burner is greatly improved, and the flame temperature of the burner meets the standard requirement.
Description
Technical field
The invention belongs to Aeronautical Test Technology, relate to the improvement to aircraft fire protection experimental rig burner.
Background technology
The burner of current a kind of aircraft fire protection experimental rig is see Fig. 1, and it is made up of housing 1, combustion chamber 3 and mixing base 4.Housing 1 has bowl-shape profile, the external diameter of housing 1 upper port is greater than the external diameter of lower port, from the upper port of housing 1 to lower port rounding off, combustion chamber 3 is welded in the upper port of housing 1, mixing base 4 is welded as entirety with the lower port of housing 1 or is threaded connection as entirety, mixing base 4 there is fuel gas inlet 4a and compressed air inlet 4b, the gas outlet of mixing base 4 is positioned at the lower port of housing 1, the outer surface of housing 1 has 4 cold gas connect mouth 2, cold gas connects the inner space of mouth 2 and combustion chamber 3.Its operation principle is: combustion gas enters housing 1 inside with compressed air by mixing base 4, after the two mixing, enters combustion chamber and sprays burning by upper head plate, form thermal-flame.Cold gas connects mouth 2 by the cold gas of the sidewall of flame front to enter in the gap of the copper pipe between the top board of combustion chamber 3 and base plate, then via the Cooling Holes ejection on top board, realize temperature and regulate.Its shortcoming is: the uniformity of combustor flame temperature is poor, and flame temperature often exceeds 1100 DEG C ± 80 DEG C scopes.Skewness.Main cause is: 1. combustion gas mixes abundant not with compressed air; 2. cold gas local pressure is too high.Above factor causes the uniformity of the flame temperature of burner poor, cannot reach standard-required.
Summary of the invention
The object of the invention is: the aircraft fire protection experimental rig burner proposing a kind of improvement, to improve the uniformity of the flame temperature of burner, make the flame temperature of burner reach standard-required.
Technical scheme of the present invention is: a kind of aircraft fire protection experimental rig burner, comprises housing 1, combustion chamber 3 and mixing base 4; Housing 1 has bowl-shape profile, the external diameter of housing 1 upper port is greater than the external diameter of lower port, from the upper port of housing 1 to lower port rounding off, combustion chamber 3 is welded in the upper port of housing 1, mixing base 4 is welded as entirety with the lower port of housing 1 or is threaded connection as entirety, mixing base 4 has fuel gas inlet 4a and compressed air inlet 4b, and the gas outlet of mixing base 4 is positioned at the lower port of housing 1; It is characterized in that: in the lower port of housing 1, mixing base 4 gas outlet above have a hybrid network assembly 5, hybrid network assembly 5 is stacked by 2 layers to 6 layers hybrid network and forms, the mesh size of hybrid network is 100 order to 300 orders, and the inwall of the lower port of hybrid network assembly 5 and housing 1 is by welding or being threaded to entirety; In the lower port of housing 1, above hybrid network assembly 5, there is one to mix cover 6, mixing cover 6 is cylinders of an open at its lower end, upper end closed, the lower port of mixing cover 6 is connected for overall by welding or screw thread with the inwall of the lower port of housing 1, uniform passage 6a on the face of cylinder of mixing cover 6, the aperture of passage 6a is 2mm ~ 4mm, and the percent opening of mixing cover 6 is 50% ~ 70%; An annular coolant jacket 7 is welded with on the outer surface of housing 1, near the position of upper port, the inner chamber of coolant jacket 7 is closed annular chamber, the lower surface of coolant jacket 7 has at least 3 the compressed air air inlet connecting mouths 9 be uniformly distributed along the circumference, the outer surface of housing 1 has the circle cooling air admission hole 8 be uniformly distributed along the circumference, the quantity of cooling air admission hole 8 is 10 ~ 20, the aperture of cooling air admission hole 8 is 1mm ~ 2mm, and cooling air admission hole 8 makes the annular chamber of coolant jacket 7 and the inner space of combustion chamber 3.
Advantage of the present invention is: the aircraft fire protection experimental rig burner proposing a kind of improvement, considerably increases the homogeneous flame temperature of burner, makes the flame temperature of burner reach standard-required.One embodiment of the present of invention, prove through test, the homogeneous flame temperature of burner increases substantially, and flame temperature is stabilized within the scope of 1100 DEG C ± 60 DEG C.
Accompanying drawing explanation
Fig. 1 is the structural principle block diagram of current a kind of aircraft fire protection experimental rig burner.
Fig. 2 is structural principle block diagram of the present invention.
Detailed description of the invention
Below the present invention is described in further details.See Fig. 2, a kind of burner of aircraft fire protection experimental rig, comprises housing 1, combustion chamber 3 and mixing base 4; Housing 1 has bowl-shape profile, the external diameter of housing 1 upper port is greater than the external diameter of lower port, from the upper port of housing 1 to lower port rounding off, combustion chamber 3 is welded in the upper port of housing 1, mixing base 4 is welded as entirety with the lower port of housing 1 or is threaded connection as entirety, mixing base 4 has fuel gas inlet 4a and compressed air inlet 4b, and the gas outlet of mixing base 4 is positioned at the lower port of housing 1; It is characterized in that: in the lower port of housing 1, mixing base 4 gas outlet above have a hybrid network assembly 5, hybrid network assembly 5 is stacked by 2 layers to 6 layers hybrid network and forms, the mesh size of hybrid network is 100 order to 300 orders, and the inwall of the lower port of hybrid network assembly 5 and housing 1 is by welding or being threaded to entirety; In the lower port of housing 1, above hybrid network assembly 5, there is one to mix cover 6, mixing cover 6 is cylinders of an open at its lower end, upper end closed, the lower port of mixing cover 6 is connected for overall by welding or screw thread with the inwall of the lower port of housing 1, uniform passage 6a on the face of cylinder of mixing cover 6, the aperture of passage 6a is 2mm ~ 4mm, and the percent opening of mixing cover 6 is 50% ~ 70%; An annular coolant jacket 7 is welded with on the outer surface of housing 1, near the position of upper port, the inner chamber of coolant jacket 7 is closed annular chamber, the lower surface of coolant jacket 7 has at least 3 the compressed air air inlet connecting mouths 9 be uniformly distributed along the circumference, the outer surface of housing 1 has the circle cooling air admission hole 8 be uniformly distributed along the circumference, the quantity of cooling air admission hole 8 is 10 ~ 20, the aperture of cooling air admission hole 8 is 1mm ~ 2mm, and cooling air admission hole 8 makes the annular chamber of coolant jacket 7 and the inner space of combustion chamber 3.
Operation principle of the present invention is: the uniformity that increase combustion gas mixes with air effectively can improve the uniformity of flame temperature.In order to increase the uniformity that combustion gas mixes with air, adding hybrid network assembly 5 and mixing cover 6, by increasing mixing link, greatly improving the uniformity that combustion gas mixes with compressed air, thus improve the uniformity of flame temperature.
Partial high pressure phenomenon in cold gas distribution, the effective uniformity improving flame temperature, increases coolant jacket 7 outward at flame front sidewall, and adds the cooling air admission hole quantity on housing 1 sidewall.External compression air first enters coolant jacket 7 by compressed air air inlet connecting mouth 9, obtain preliminarily stabilised in coolant jacket 7 after, between the top board entering combustion chamber 3 by the cooling air admission hole 8 on housing 1 sidewall again and base plate, such structure, substantially increase the uniformity of cold gas distribution, thus improve the uniformity of flame temperature.
One embodiment of the present of invention, the mesh size of the hybrid network in hybrid network assembly 5 is 100 orders, and the inwall of the lower port of hybrid network assembly 5 and housing 1 is threaded connection as entirety; The aperture of passage 6a is 2mm, and the percent opening of mixing cover 6 is 70%; The quantity of cooling air admission hole 8 is 12, and the aperture of cooling air admission hole 8 is 2mm.
Second embodiment of the present invention, the mesh size of the hybrid network in hybrid network assembly 5 is 300 orders, and the inwall of the lower port of hybrid network assembly 5 and housing 1 is threaded connection as entirety; The aperture of passage 6a is 3mm, and the percent opening of mixing cover 6 is 60%; The quantity of cooling air admission hole 8 is 15, and the aperture of cooling air admission hole 8 is 1.5mm.
Claims (1)
1. a burner for aircraft fire protection experimental rig, comprises housing (1), combustion chamber (3) and mixing base (4), housing (1) has bowl-shape profile, the external diameter of housing (1) upper port is greater than the external diameter of lower port, from the upper port of housing (1) to lower port rounding off, combustion chamber (3) is welded in the upper port of housing (1), mixing base (4) is welded as entirety with the lower port of housing (1) or is threaded connection as entirety, mixing base (4) has fuel gas inlet (4a) and compressed air inlet (4b), and the gas outlet of mixing base (4) is positioned at the lower port of housing (1), it is characterized in that: in the lower port of housing (1), mixing base (4) gas outlet above have a hybrid network assembly (5), hybrid network assembly (5) is stacked by 2 layers to 6 layers hybrid network and forms, the mesh size of hybrid network is 100 order to 300 orders, and the inwall of the lower port of hybrid network assembly (5) and housing (1) is by welding or being threaded to entirety, in the lower port of housing (1), above hybrid network assembly (5), there is one to mix cover (6), mixing cover (6) is the cylinder of an open at its lower end, upper end closed, the lower port of mixing cover (6) is connected for overall by welding or screw thread with the inwall of the lower port of housing (1), uniform passage (6a) on the face of cylinder of mixing cover (6), the aperture of passage (6a) is 2mm ~ 4mm, and the percent opening of mixing cover (6) is 50% ~ 70%, on the outer surface of housing (1), an annular coolant jacket (7) is welded with near the position of upper port, the inner chamber of coolant jacket (7) is closed annular chamber, the lower surface of coolant jacket (7) has at least 3 the compressed air air inlet connecting mouths (9) be uniformly distributed along the circumference, the outer surface of housing (1) has circle cooling air admission hole (8) be uniformly distributed along the circumference, the quantity of cooling air admission hole (8) is 10 ~ 20, the aperture of cooling air admission hole (8) is 1mm ~ 2mm, cooling air admission hole (8) makes the annular chamber of coolant jacket (7) and the inner space of combustion chamber (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510212188.0A CN104819466A (en) | 2015-04-29 | 2015-04-29 | Burner of aircraft fire protection testing apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510212188.0A CN104819466A (en) | 2015-04-29 | 2015-04-29 | Burner of aircraft fire protection testing apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104819466A true CN104819466A (en) | 2015-08-05 |
Family
ID=53729847
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510212188.0A Pending CN104819466A (en) | 2015-04-29 | 2015-04-29 | Burner of aircraft fire protection testing apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104819466A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2241815Y (en) * | 1995-05-11 | 1996-12-04 | 上海市机电设计研究院 | Gas sub-high speed burner nozzle |
| US5749720A (en) * | 1995-04-21 | 1998-05-12 | Nkk Corporation | Gas heating apparatus with dual burners |
| JP2002250508A (en) * | 2001-02-26 | 2002-09-06 | Sanyo Electric Co Ltd | Burner for reforming device |
| CN101413684A (en) * | 2008-12-02 | 2009-04-22 | 曾文洲 | Cooking stove |
| RU2355948C2 (en) * | 2007-05-07 | 2009-05-20 | Общество с ограниченной ответственностью Финансово-промышленная компания "Космос-Нефть-Газ" | Flare burner |
| CN201246744Y (en) * | 2008-08-06 | 2009-05-27 | 余家健 | Pre-mixing catalyzing energy saving burner |
| CN202328235U (en) * | 2011-09-15 | 2012-07-11 | 长沙华润节能科技有限公司 | Energy-saving explosion resistance gas burner |
| CN104315514A (en) * | 2014-11-18 | 2015-01-28 | 中冶南方(武汉)威仕工业炉有限公司 | Partially premixed gas fuel burner of bi-layer porous foamed ceramic plate |
-
2015
- 2015-04-29 CN CN201510212188.0A patent/CN104819466A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5749720A (en) * | 1995-04-21 | 1998-05-12 | Nkk Corporation | Gas heating apparatus with dual burners |
| CN2241815Y (en) * | 1995-05-11 | 1996-12-04 | 上海市机电设计研究院 | Gas sub-high speed burner nozzle |
| JP2002250508A (en) * | 2001-02-26 | 2002-09-06 | Sanyo Electric Co Ltd | Burner for reforming device |
| RU2355948C2 (en) * | 2007-05-07 | 2009-05-20 | Общество с ограниченной ответственностью Финансово-промышленная компания "Космос-Нефть-Газ" | Flare burner |
| CN201246744Y (en) * | 2008-08-06 | 2009-05-27 | 余家健 | Pre-mixing catalyzing energy saving burner |
| CN101413684A (en) * | 2008-12-02 | 2009-04-22 | 曾文洲 | Cooking stove |
| CN202328235U (en) * | 2011-09-15 | 2012-07-11 | 长沙华润节能科技有限公司 | Energy-saving explosion resistance gas burner |
| CN104315514A (en) * | 2014-11-18 | 2015-01-28 | 中冶南方(武汉)威仕工业炉有限公司 | Partially premixed gas fuel burner of bi-layer porous foamed ceramic plate |
Non-Patent Citations (1)
| Title |
|---|
| 欧育湘等: "《材料阻燃性能测试方法》", 31 January 2007, 化学工业出版社 * |
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| C06 | Publication | ||
| PB01 | Publication | ||
| EXSB | Decision made by sipo to initiate substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150805 |
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| WD01 | Invention patent application deemed withdrawn after publication |