JPH0217770B2 - - Google Patents
Info
- Publication number
- JPH0217770B2 JPH0217770B2 JP60225710A JP22571085A JPH0217770B2 JP H0217770 B2 JPH0217770 B2 JP H0217770B2 JP 60225710 A JP60225710 A JP 60225710A JP 22571085 A JP22571085 A JP 22571085A JP H0217770 B2 JPH0217770 B2 JP H0217770B2
- Authority
- JP
- Japan
- Prior art keywords
- burner
- flow path
- air flow
- nozzle
- fuel
- 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.)
- Expired - Lifetime
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C9/00—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
- F23C9/006—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber the recirculation taking place in the combustion chamber
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C7/00—Combustion apparatus characterised by arrangements for air supply
- F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
- F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
-
- 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
- F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
- F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
- F23D14/24—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other at least one of the fluids being submitted to a swirling motion
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Description
【発明の詳細な説明】
（産業上の利用分野）
本発明は、耐火物からなるバーナタイルを加熱
し、バーナタイルからの輻射熱を利用する輻射バ
ーナに関するものである。DETAILED DESCRIPTION OF THE INVENTION (Field of Industrial Application) The present invention relates to a radiant burner that heats burner tiles made of refractory material and utilizes radiant heat from the burner tiles.
（従来技術とその問題点）
従来、前記輻射バーナとしては、種々のものが
提示されているが、たとえば、実開昭59−37930
号公報に示されるものがある。(Prior art and its problems) Conventionally, various types of radiation burners have been proposed.
There is something shown in the publication.
これは、第６図、第７図に示すように、ガスバ
ーナ２は、そのバーナ軸中心部に、内部に空気を
供給するセンタノズル６を有する燃料ガスノズル
３からなる。 As shown in FIGS. 6 and 7, the gas burner 2 includes a fuel gas nozzle 3 having a center nozzle 6 at the center of the burner shaft for supplying air to the inside.
そして、前記センタノズル６と燃料ガスノズル
３とで形成される燃料ガス通路４の先端部には、
前方拡大方向に開口する噴出部５が、また、セン
タノズル６の先端にも前方拡大方向に開口する噴
出部７が設けてある。なお、前記センタノズル６
には、常時最大燃焼時の理論空気量の1.0〜15％
の空気が噴出するようになつている。 At the tip of the fuel gas passage 4 formed by the center nozzle 6 and the fuel gas nozzle 3,
A jetting portion 5 that opens in the forward expanding direction is provided, and a jetting portion 7 that opens in the forward expanding direction is also provided at the tip of the center nozzle 6. Note that the center nozzle 6
1.0 to 15% of the theoretical air amount at maximum combustion at all times.
The air is now gushing out.
一方、燃料ガスノズル３の外周部とバーナタイ
ル１とで形成される燃焼用エア通路８には旋回羽
根９が設けてある。 On the other hand, swirl vanes 9 are provided in the combustion air passage 8 formed by the outer peripheral portion of the fuel gas nozzle 3 and the burner tile 1 .
そして、バーナ２を運転すると、燃料ガスは前
方に拡大して噴出するとともに、旋回羽根９によ
つて旋回流となつた燃焼用エアと混合しつつ燃焼
し、その火炎は前方拡大方向に形成され、いわゆ
るラジアルフレームを形成する。また、センタノ
ズル６からエアが、バーナのターンダウンに関係
なく火炎の伸展方向に噴出しているため、火炎が
これら空気によりその広がりを強制されるととも
に、燃料ガスが空気と十分混合し、低過剰空気特
性で良好な燃焼性を維持するものである。 When the burner 2 is operated, the fuel gas expands forward and is ejected, and is combusted while mixing with the combustion air that has become a swirling flow due to the swirling vanes 9, and the flame is formed in the forward expanding direction. , forming a so-called radial frame. In addition, since air is ejected from the center nozzle 6 in the direction of flame extension regardless of burner turndown, the flame is forced to spread by the air, and the fuel gas is sufficiently mixed with the air, resulting in low It maintains good combustibility with excess air characteristics.
しかしながら、前記燃料ガスノズル３が、バー
ナスロート部１０より距離l1だけ引つ込めてあ
り、またバーナスロート部１０での燃料との良好
な混合を図るよう噴出部５が密に設けてあるため
に、火炎は、第５図に示すように、円周方向に均
一に形成され、バーナタイル１を高温赤熱し、こ
のため、NOxは、第３図にイで示すように多量
のNOxを発生する。 However, since the fuel gas nozzle 3 is retracted from the burner throat portion 10 by a distance l 1 and the jetting portions 5 are closely arranged to ensure good mixing with the fuel in the burner throat portion 10, As shown in Fig. 5, the flame is formed uniformly in the circumferential direction and makes the burner tile 1 red hot at a high temperature . Occur.
また、センタノズル６の噴出部７は、角度αc
が一般に60〜100゜であり、バーナスロート部１０
の上流部でセンタエアと燃料とが混合するので、
排ガスの火炎への巻込みがなく火炎温度は高温で
ある。 Further, the jetting portion 7 of the center nozzle 6 has an angle αc
is generally 60 to 100°, and the burner throat portion 10
Since the center air and fuel mix in the upstream part of
There is no entrainment of exhaust gas into the flame, and the flame temperature is high.
しかも、低負荷になるにつれて、センタエアと
燃料との混合が急速に行なわれるので、第３図に
イで示すように低負荷域でのNOxの増加が著し
いという問題点を有する。このことは燃焼用空気
通路８を同心円で１次、２次エア通路に分割して
もほぼ同様である。 Furthermore, as the load decreases, the center air and fuel are rapidly mixed, so there is a problem in that NO x increases significantly in the low load range, as shown by A in FIG. 3. This is substantially the same even if the combustion air passage 8 is concentrically divided into primary and secondary air passages.
（問題点を解決すべき手段）
本発明は、前記問題点を解決するために、輻射
バーナを、１次エア流路と、該１次エア流路の外
周部に設けた２次エア流路と、前記各流路に設け
た旋回羽根と、燃料をエア噴出速度の1.2〜2.0倍
で斜め方向に噴射させる複数の噴出孔を有すると
ともに、バーナスロートから突出し、かつ、前記
１次エア流路の中心部に配置された燃料ノズル
と、燃料噴射角度βgに等しいかそれより小さい
角度βTで開いたバーナタイルとで構成したもので
ある。(Means to Solve the Problems) In order to solve the above problems, the present invention provides a radiation burner in a primary air flow path and a secondary air flow path provided on the outer periphery of the primary air flow path. and a swirling vane provided in each of the flow passages, and a plurality of jet holes that inject fuel in an oblique direction at 1.2 to 2.0 times the air jet velocity, protruding from the burner throat, and the primary air flow passage. It consists of a fuel nozzle located at the center of the fuel nozzle, and a burner tile that opens at an angle β T equal to or smaller than the fuel injection angle βg.
（実施例〕
つぎに、本発明を一実施例である第１図〜第２
図にしたがつて説明する。(Example) Next, the present invention will be described in Figures 1 to 2, which are examples.
This will be explained according to the diagram.
第６図、第７図の従来のものと比較すれば明ら
かなように、エア流路８が同心円上の１次エア流
路８ａと２次エア流路８ｂとに区画され、各流路
８ａ，８ｂにそれぞれ旋回羽根９ａ，９ｂを設
け、燃焼用エアを空気配分弁１１にて所定比によ
り供給するようになつている。 As is clear from a comparison with the conventional one shown in FIGS. 6 and 7, the air flow path 8 is divided into a concentric primary air flow path 8a and a secondary air flow path 8b, and each air flow path 8a , 8b are provided with swirl vanes 9a, 9b, respectively, and combustion air is supplied by an air distribution valve 11 at a predetermined ratio.
また、燃料ノズル３は、バーナスロート部１０
からl2だけ突出するとともに、燃料は燃料ノズル
３からβgの角度で噴出するようになつている。 Further, the fuel nozzle 3 includes a burner throat portion 10.
The fuel nozzle 3 protrudes by l 2 from the fuel nozzle 3 at an angle of βg.
一方、センタノズル６の噴出部７はエアが半径
方向に噴出するように設けてある。 On the other hand, the ejection portion 7 of the center nozzle 6 is provided so that air is ejected in the radial direction.
さらに、バーナスロート外径をD0、２次エア
流路８ｂの内径をDi、２次エア流路の旋回羽根
部の外径をd0、内径をd1、２次エア流路の旋回羽
根取付角度をαとして、流体流れ設計において旋
回強さを表す無次元のスワール数を、
２／３［１−（di／d0）3／１−（di／d0）2］・tanα
・D0［１−（Di／D0）2］／d0［１−（di／d0）2］＞0.
8
なる関係にした。 Further, the outer diameter of the burner throat is D 0 , the inner diameter of the secondary air flow path 8b is Di, the outer diameter of the swirling blade portion of the secondary air flow path is d 0 , the inner diameter is d 1 , the swirling blade of the secondary air flow path When the installation angle is α, the dimensionless swirl number that represents the swirling strength in fluid flow design is 2/3 [1-(di/d 0 ) 3 /1-(di/d 0 ) 2 ]・tanα
・D 0 [1-(Di/D 0 ) 2 ]/d 0 [1-(di/d 0 ) 2 ]>0.
8 We established a relationship.
前記構成からなる輻射バーナ２において、35万
kcal／Hr、βT＝βg＝80〜120゜とし、燃料ノズル
３の孔数を従来の半数とし、かつ、燃料ノズル３
のバーナスロート部１０からの突出量l2を、l2＝
0.22×D0とする一方、１次エアにα1＝０〜15゜、
２次エアにα＝40〜60゜の旋回を与えるとともに、
センタエアノズル６からエアを、常時バーナの定
格容量時における理論空気量の1.5〜2.5％を70〜
85ｍ／ｓの流速で噴出させて操業すると、噴出角
度βgで吐出する燃料は、旋回羽根９ａ，９ｂに
よつて旋回する１次エアおよび２次エアと混合
し、バーナタイル１内で燃焼する。 In the radiation burner 2 having the above configuration, 350,000
kcal/Hr, β T = βg = 80 to 120°, the number of holes in the fuel nozzle 3 is half of the conventional one, and the fuel nozzle 3
The amount of protrusion l 2 from the burner throat part 10 is expressed as l 2 =
0.22×D 0 , while α 1 = 0~15° for the primary air.
While giving the secondary air a rotation of α=40 to 60°,
Air is constantly supplied from the center air nozzle 6 at 70 to 1.5 to 2.5% of the theoretical air amount at the rated capacity of the burner.
When the fuel is ejected at a flow rate of 85 m/s and operated, the fuel ejected at the ejection angle βg mixes with the primary air and secondary air swirled by the swirling vanes 9a and 9b, and is combusted within the burner tile 1.
また、このとき、燃焼直後の排ガスはバーナノ
ズル３に向つて逆流する。 Further, at this time, the exhaust gas immediately after combustion flows back toward the burner nozzle 3.
そして、燃料ガスは、エア噴出速度の1.2〜2.0
倍の速度で斜め外方に噴出するため、排ガス層お
よび１次、２次エアの旋回層を貫通し、その間、
排ガス、１次、２次エアと混合して燃焼し、つま
り、バーナタイル１内での高温燃焼が抑制され
NOxは大巾に低減する。 And the fuel gas has an air jet velocity of 1.2 to 2.0
Because it is ejected diagonally outward at twice the speed, it penetrates the exhaust gas layer and the swirling layers of primary and secondary air, and during that time,
It burns by mixing with exhaust gas, primary air, and secondary air, which means that high-temperature combustion inside burner tile 1 is suppressed.
NO x will be significantly reduced.
なお、バーナノズル３の孔３ａの数は、従来の
ものより少なくなつているため、第４図に示すよ
うに火炎は分割火炎となり、よりNOxが低減さ
れる。 Incidentally, since the number of holes 3a of the burner nozzle 3 is smaller than that of the conventional one, the flame becomes a divided flame as shown in FIG. 4, and NO x is further reduced.
バーナ２がターンダウンしても、センタエアノ
ズル６からセンタエアが半径方向に一定量噴出し
ているため、燃料ガスと燃焼ガスとの混合性能が
よく、10％負荷においても低空気比で火炎に方向
性を維持させるから完全燃焼が可能となつた。 Even when the burner 2 is turned down, a constant amount of center air is ejected in the radial direction from the center air nozzle 6, so the mixing performance of the fuel gas and combustion gas is good, and even at 10% load, the flame is directed at a low air ratio. Since it maintains its properties, complete combustion is possible.
また、前記のようにセンタエアノズル６は半径
方向に開口しているため、バーナ中央部からの排
ガス巻き込みを促進し、特に低負荷域でのNOx
の増大を完全に防止することができた。 In addition, as mentioned above, since the center air nozzle 6 is opened in the radial direction, it promotes the entrainment of exhaust gas from the center of the burner, especially in the low load range .
We were able to completely prevent the increase in
（発明の効果）
以上の説明から明らかなように、本発明によれ
ば、輻射バーナを、１次エア流路と、該１次エア
流路の外周部に設けた２次エア流路と、前記各流
路に設けた旋回羽根と、燃料をエア噴出速度の
1.2〜2.0倍で斜め方向に噴射させる複数の噴出孔
を有するとともに、バーナスロートから突出し、
かつ前記１次エア流路の中心部に配置された燃料
ノズルと、燃料噴射角度βgに等しいかそれより
小さい角度βTで開いたバーナタイルから構成した
ため、燃料ガスは１次、２次エアと混合するとと
もに、バーナ中心部に流入する排ガスと混合し
NOxの発生がすくない。しかも、燃料ノズルは
バーナスロートから突出しているため、つまり、
バーナタイルとの距離が大であることと、燃焼用
エアは旋回流となつてバーナタイル内面に沿つて
流れて冷却するため、バーナタイルは高温赤熱せ
ず、第３図のロ線で示すようにNOxの発生をそ
れだけ低減する。(Effects of the Invention) As is clear from the above description, according to the present invention, a radiant burner is provided in a primary air flow path, a secondary air flow path provided on the outer periphery of the primary air flow path, The swirl vanes provided in each flow path and the fuel flow rate are adjusted to
It has multiple nozzles that spray diagonally at 1.2 to 2.0 times, and protrudes from the burner throat.
In addition, since it is composed of a fuel nozzle placed in the center of the primary air flow path and a burner tile that opens at an angle β T that is equal to or smaller than the fuel injection angle βg, the fuel gas is mixed with the primary and secondary air. At the same time, it mixes with the exhaust gas flowing into the center of the burner.
There is less NO x generation. Moreover, since the fuel nozzle protrudes from the burner throat,
Because the distance from the burner tile is large, and the combustion air forms a swirling flow that flows along the inner surface of the burner tile and cools it, the burner tile does not become red hot, as shown by line B in Figure 3. The generation of NO x is reduced accordingly.
第１図は本発明にかかる輻射バーナの該略図、
第２図は燃料ノズル、センタエアノズルの拡大断
面図、第３図は本発明にかかる輻射バーナと従来
バーナとのバーナ負荷とNOxの発生量との関係
を示すグラフ、第４図および第５図は本発明にか
かる輻射バーナと従来バーナとの火炎の状態を示
す図、第６図は従来バーナの該略図で、第７図は
第６図の燃料ノズル、センタエアノズルの拡大断
面図である。
１〜バーナタイル、２〜バーナ、３〜燃料ノズ
ル、３ａ，５〜孔、６〜センタエアノズル、７〜
孔、８ａ，８ｂ〜１次、２次エア流路、９ａ，９
ｂ〜旋回羽根、１０〜バーナスロート。
FIG. 1 is a schematic diagram of a radiant burner according to the present invention;
Fig. 2 is an enlarged sectional view of the fuel nozzle and center air nozzle, Fig. 3 is a graph showing the relationship between the burner load and the amount of NO x generated between the radiant burner according to the present invention and the conventional burner, and Figs. 4 and 5. The figure is a diagram showing the flame state of the radiant burner according to the present invention and the conventional burner, FIG. 6 is a schematic diagram of the conventional burner, and FIG. 7 is an enlarged sectional view of the fuel nozzle and center air nozzle of FIG. 6. . 1-burner tile, 2-burner, 3-fuel nozzle, 3a, 5-hole, 6-center air nozzle, 7-
Holes, 8a, 8b to primary and secondary air flow paths, 9a, 9
b ~ swirl vane, 10 ~ burner throat.
Claims (1)
設けた２次エア流路と、前記各流路に設けた旋回
羽根と、燃料をエア噴出速度の1.2〜2.0倍で斜め
方向に噴射させる複数の噴出孔を有するととも
に、バーナスロートから突出し、かつ前記１次エ
ア流路の中心部に配置された燃料ノズルと、燃料
噴射角度βgに等しいかそれより小さい角度βT開
いたバーナタイルと、から構成したことを特徴と
する輻射バーナ。 ２ 前記２次エア流路の旋回羽根部とバーナスロ
ート部の内外径および旋回羽根取付角度αとの関
係が、 ２／３［１−（di／d0）3／１−（di／d0）2］・tanα
・D0［１−（Di／D0）2］／d0［１−（di／d0）2］＞0.
8 であることを特徴とする前記特許請求の範囲第１
項に記載の輻射バーナ。 ただし、D0：バーナスロート外径 Di：２次エア流路の内径 d0：２次エア流路の旋回羽根部外径 di：２次エア流路の旋回羽根部内径 ３ 前記燃料ノズルが、その先端から突出し、半
径方向にエアを噴出させる噴出孔を有するセンタ
エアノズルを備えていることを特徴とする前記特
許請求の範囲第１項または第２項に記載の輻射バ
ーナ。[Scope of Claims] 1. A primary air flow path, a secondary air flow path provided on the outer periphery of the primary air flow path, and a swirling vane provided in each of the flow paths to control fuel at an air jetting speed. A fuel nozzle that has a plurality of injection holes that inject diagonally at a rate of 1.2 to 2.0 times, protrudes from the burner throat, and is located at the center of the primary air flow path, and a fuel injection angle that is equal to or greater than βg. A radiant burner characterized by comprising a burner tile opened at a small angle βT . 2 The relationship between the inner and outer diameters of the swirling vane portion of the secondary air flow path and the burner throat portion, and the swirling vane mounting angle α is 2/3[1-(di/d 0 ) 3 /1-(di/d 0 ) 2 ]・tanα
・D 0 [1-(Di/D 0 ) 2 ]/d 0 [1-(di/d 0 ) 2 ]>0.
8.
Radiant burner as described in section. However, D 0 : Burner throat outer diameter Di : Inner diameter of secondary air flow path d 0 : Outer diameter of swirling blade part of secondary air flow path di : Inner diameter of swirling blade part of secondary air flow path 3 The fuel nozzle is The radiant burner according to claim 1 or 2, further comprising a center air nozzle that protrudes from its tip and has an ejection hole that ejects air in a radial direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60225710A JPS6287717A (en) | 1985-10-09 | 1985-10-09 | Radiation burner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60225710A JPS6287717A (en) | 1985-10-09 | 1985-10-09 | Radiation burner |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS6287717A JPS6287717A (en) | 1987-04-22 |
| JPH0217770B2 true JPH0217770B2 (en) | 1990-04-23 |
Family
ID=16833589
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP60225710A Granted JPS6287717A (en) | 1985-10-09 | 1985-10-09 | Radiation burner |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6287717A (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5209656A (en) * | 1991-08-29 | 1993-05-11 | Praxair Technology, Inc. | Combustion system for high velocity gas injection |
| AT408796B (en) * | 1999-04-29 | 2002-03-25 | Dumag Ohg | BURNER |
| KR102111644B1 (en) * | 2019-06-11 | 2020-05-15 | 두산중공업 주식회사 | Combustor and gas turbine with multiple swirlers formed in different shapes |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS577923U (en) * | 1980-06-17 | 1982-01-16 | ||
| JPS5844927A (en) * | 1981-09-11 | 1983-03-16 | Itsushin Kogyo:Kk | Manufacture of tube joint and clamping tool used for this method |
-
1985
- 1985-10-09 JP JP60225710A patent/JPS6287717A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPS6287717A (en) | 1987-04-22 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EXPY | Cancellation because of completion of term |