JP2001235119A - Burner device - Google Patents
Burner deviceInfo
- Publication number
- JP2001235119A JP2001235119A JP2000041170A JP2000041170A JP2001235119A JP 2001235119 A JP2001235119 A JP 2001235119A JP 2000041170 A JP2000041170 A JP 2000041170A JP 2000041170 A JP2000041170 A JP 2000041170A JP 2001235119 A JP2001235119 A JP 2001235119A
- Authority
- JP
- Japan
- Prior art keywords
- flow path
- pilot
- combustion
- inner cylinder
- main combustion
- 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
Landscapes
- Gas Burners (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、地域暖房などを行
うためのコージェネレーションシステムにおけるガスタ
ービンエンジンや焼却炉などのバーナ装置で、詳しく
は、パイロット領域を規定する内筒と、前記内筒を外囲
する中間流路を規定する外筒とを設け、前記中間流路に
おいて、混合気流れ方向で、燃料混入部と前記外筒に設
けられる流路拡大部である燃焼開始部との間に規定され
るメイン燃焼用混合流路を設けてあるものに関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a burner apparatus such as a gas turbine engine or an incinerator in a cogeneration system for performing district heating or the like. An outer cylinder that defines an intermediate flow path that surrounds the fuel cell, and in the intermediate flow path, in the mixture flow direction, between a fuel mixing part and a combustion start part that is a flow path expansion part that is provided in the outer cylinder. The present invention relates to an apparatus provided with a specified main combustion mixing channel.
【０００２】[0002]
【従来の技術】従来のこの種のバーナ装置では、前記内
筒内のうちメイン燃焼用混合流路の混合気流れ方向の開
始位置近傍に、前記パイロット領域の開始位置を設定し
ていた。2. Description of the Related Art In a conventional burner of this type, the start position of the pilot region is set near the start position of the main combustion mixing flow path in the mixture flow direction in the inner cylinder.
【発明が解決しようとする課題】しかし、上記従来の技
術によるときは、パイロット領域の開始位置がメイン燃
焼用混合流路の開始位置近傍に位置することで、パイロ
ット領域の開始位置と、メイン燃焼用混合流路の終端位
置との流れ方向での距離が大きくなりやすいから、パイ
ロット燃焼用の燃料ガスの供給流量を少なくしていく
と、パイロット燃焼炎のメイン燃焼混合流路の終端位置
までの到達性が不安定となって、燃焼振動が発生し、そ
の結果、パイロット燃焼炎のメイン燃焼用混合気への火
移り性能が低下することでメイン燃焼が不安定となっ
て、低ＮＯｘを目的とした希薄燃焼を妨げていた。However, according to the above-mentioned prior art, since the start position of the pilot region is located near the start position of the main combustion mixing flow path, the start position of the pilot region and the main combustion Since the distance in the flow direction from the end position of the mixing flow path for the pilot combustion tends to increase, the supply flow rate of the fuel gas for pilot combustion is reduced, so that the pilot combustion flame reaches the end position of the main combustion mixing flow path. Reachability becomes unstable and combustion oscillation occurs. As a result, the performance of the pilot combustion flame to be transferred to the main combustion air-fuel mixture is reduced, so that the main combustion becomes unstable and low NOx is intended. And prevented lean burn.
【０００３】本発明の目的は、燃焼振動を抑制してメイ
ン燃焼を安定化させる点にある。An object of the present invention is to stabilize main combustion by suppressing combustion oscillation.
【０００４】[0004]
【課題を解決するための手段】請求項１に係る本発明の
バーナ装置の特徴・作用・効果は次の通りである。The features, operations and effects of the burner device according to the present invention are as follows.
【０００５】〔特徴〕パイロット領域を規定する内筒
と、前記内筒を外囲する中間流路を規定する外筒とを設
け、前記中間流路において、混合気流れ方向で、燃料混
入部と前記外筒に設けられる流路拡大部である燃焼開始
部との間に規定されるメイン燃焼用混合流路を設けてあ
るバーナ装置であって、前記パイロット領域の開始位置
を、前記メイン燃焼用混合流路の混合気流れ方向の中央
よりもパイロット燃焼炎流れ方向（この方向はメイン燃
焼用混合流路の混合気流れ方向と一致している。）下流
側に設定してある点にある。[Features] An inner cylinder that defines a pilot region and an outer cylinder that defines an intermediate flow path surrounding the inner cylinder are provided. A burner device provided with a main combustion mixing flow path defined between the combustion start part which is a flow path expansion part provided in the outer cylinder, wherein the start position of the pilot region is set to the main combustion position. The point is that it is set on the downstream side of the pilot combustion flame flow direction (this direction coincides with the mixture flow direction of the main combustion mixing flow path) from the center of the mixture flow direction of the mixing flow path.
【０００６】〔作用〕メイン燃焼用混合流路の混合気流
れ方向の中央よりもパイロット燃焼炎流れ方向下流側に
パイロット領域の開始位置を設定してあるから、パイロ
ット燃焼開始位置からメイン燃焼用混合流路の終端まで
の距離を短くできて、パイロット燃焼炎のメイン燃焼用
混合流路終端までの到達を安定よく行わせることができ
て、燃焼振動を抑制することができる。 〔効果〕従って、パイロット燃焼炎からメイン燃焼用の
混合気への火移りを安定して確実に行って，低ＮＯｘ化
のための希薄燃焼であっても燃焼安定性を優れたものに
できるようになった。[Operation] Since the starting position of the pilot region is set at a position downstream of the center of the main combustion mixing flow direction in the flow direction of the air-fuel mixture, the mixing position for the main combustion is determined from the pilot combustion start position. The distance to the end of the flow path can be shortened, the pilot combustion flame can reach the end of the main combustion mixing flow path stably, and combustion oscillation can be suppressed. [Effect] Therefore, the transfer of fire from the pilot combustion flame to the air-fuel mixture for main combustion can be performed stably and reliably, so that excellent combustion stability can be achieved even in lean combustion for reducing NOx. Became.
【０００７】請求項２に係る本発明のバーナ装置の特徴
・作用・効果は次の通りである。[0007] The features, functions and effects of the burner device according to the second aspect of the present invention are as follows.
【０００８】〔特徴〕上記請求項１に係る本発明のバー
ナ装置において、前記内筒が円筒形のものであり、前記
内筒の内径Ｄと前記パイロット領域のパイロット燃焼炎
流れ方向の長さＬとの比Ｌ／Ｄが０．１以上で１．５以
下に設定されている点にある。In the burner device according to the first aspect of the present invention, the inner cylinder has a cylindrical shape, and the inner diameter D of the inner cylinder and the length L of the pilot region in the pilot combustion flame flow direction. Is set to be not less than 0.1 and not more than 1.5.
【０００９】〔作用〕本発明者らは、研究開発を続けた
結果、パイロット領域を規定する内筒の内径Ｄとパイロ
ット領域の長さＬとの比Ｌ／Ｄが０．１以上で１．５以
下であると、燃焼振動を起こさずにパイロット燃焼させ
ることができることを知見した。[Operation] As a result of continuing research and development, the present inventors have found that when the ratio L / D of the inner diameter D of the inner cylinder defining the pilot region to the length L of the pilot region is 0.1 or more, 1. It has been found that when it is 5 or less, pilot combustion can be performed without causing combustion oscillation.
【００１０】〔効果〕従って、パイロット燃焼炎からメ
イン燃焼用の混合気への火移りを安定して確実に行っ
て，低ＮＯｘ化のための希薄燃焼であっても燃焼安定性
を優れたものにできるようになった。[Effect] Therefore, the transfer from the pilot combustion flame to the air-fuel mixture for the main combustion is performed stably and reliably, and the combustion stability is excellent even in lean combustion for reducing NOx. Now you can do it.
【００１１】請求項３に係る本発明のバーナ装置の特徴
・作用・効果は次の通りである。The features, functions and effects of the burner device according to the third aspect of the present invention are as follows.
【００１２】〔特徴〕上記請求項１や２に係る本発明の
バーナ装置において、前記混合気流れ方向における前記
内筒の終端位置である前記パイロット領域の終端位置
を、前記外筒の流路拡大部の始端位置である前記メイン
燃焼用混合流路の終端よりも前記混合気流れ方向での上
流側に設定してある点にある。[Features] In the burner device of the present invention according to claim 1 or 2, the end position of the pilot region, which is the end position of the inner cylinder in the flow direction of the air-fuel mixture, is increased by increasing the flow path of the outer cylinder. The main combustion mixing flow path, which is the start position of the portion, is set upstream of the end of the main combustion mixing flow path in the mixture flow direction.
【００１３】〔作用〕パイロット領域の終端位置のメイ
ン燃焼用混合流路の終端から上流側への後退長さを適宜
設定することにより、パイロット燃焼炎からメイン燃焼
炎への火移りを良好に行わせることができることが本発
明者の研究開発の結果判った。具体的に言えば、メイン
燃焼用混合流路の長さをＡとすると、後退長さＬＢは、
０．０５Ａ≦ＬＢ≦０．３０Ａである。つまり、パイロ
ット燃料の供給流量を少なくした場合に、パイロット燃
焼炎とメイン燃焼炎との接触部分が小さくなって火移り
性が低下することを防止する上で、後退長さＬＢには下
限限界があり、他方、パイロット燃焼炎とメイン燃焼炎
との位置が離れすぎて火移り性が低下することを防止す
る上で、後退長さＬＢには上限限界がある。[Action] By appropriately setting the retreat length upstream from the end of the main combustion mixing flow path at the end position of the pilot region, a good fire transfer from the pilot combustion flame to the main combustion flame is performed. As a result of the inventor's research and development, it has been found that it can be performed. Specifically, assuming that the length of the main combustion mixing channel is A, the retreat length LB is
0.05A ≦ LB ≦ 0.30A. In other words, when the supply flow rate of the pilot fuel is reduced, in order to prevent the contact portion between the pilot combustion flame and the main combustion flame from becoming small and thereby reducing the fireability, the lower limit of the retreat length LB has a lower limit. On the other hand, there is an upper limit for the retreat length LB in order to prevent the pilot combustion flame and the main combustion flame from being too far apart from each other to reduce the fireability.
【００１４】〔効果〕従って、パイロット燃焼炎からメ
イン燃焼用の混合気への火移りを安定して確実に行っ
て，低ＮＯｘ化のための希薄燃焼であっても燃焼安定性
を優れたものにできるようになった。[Effect] Therefore, the transfer from the pilot combustion flame to the air-fuel mixture for the main combustion is performed stably and reliably, and the combustion stability is excellent even in the lean combustion for reducing NOx. Now you can do it.
【００１５】[0015]
【発明の実施の形態】ガスタービンエンジンや焼却炉な
どに用いられるバーナ装置は、図１、図２に示すよう
に、パイロット領域Ａ１を規定する円筒形の内筒１と、
この内筒１を外囲する中間流路を規定する外筒２と、前
記パイロット領域Ａ１及び中間流路に空気を供給するた
めの空気供給手段と、前記パイロット領域Ａ１に燃料ガ
スを供給するための第１ガス供給手段と、前記中間流路
に燃料ガスを供給するための第２ガス供給手段とを設け
て構成されている。DESCRIPTION OF THE PREFERRED EMBODIMENTS As shown in FIGS. 1 and 2, a burner device used in a gas turbine engine, an incinerator or the like has a cylindrical inner cylinder 1 defining a pilot area A1.
An outer cylinder 2 for defining an intermediate flow path surrounding the inner cylinder 1, air supply means for supplying air to the pilot area A1 and the intermediate flow path, and an air supply means for supplying fuel gas to the pilot area A1. And a second gas supply means for supplying a fuel gas to the intermediate flow path.
【００１６】前記内筒１と外筒２とは同心状に配置され
ており、内筒１は外筒２に周方向複数の第１スラット３
を介して支持されている。The inner cylinder 1 and the outer cylinder 2 are arranged concentrically, and the inner cylinder 1 is provided on the outer cylinder 2 with a plurality of first slats 3 in the circumferential direction.
Is supported through.
【００１７】前記空気供給手段は、図示しないコンプレ
ッサーなどにより、パイロット領域Ａ１及び中間流路に
一端開口から空気を押し込む手段である。The air supply means is means for pushing air into the pilot area A1 and the intermediate flow path from one end opening by a compressor (not shown) or the like.
【００１８】前記第１ガス供給手段は、互いに独立した
第１供給路４Ａと第２供給路４Ｂとを形成したノズル４
を前記内筒１内に配置し、前記第１供給路４Ａ内の燃料
ガスを内筒１内に噴出供給する複数の噴出口５を前記ノ
ズル４に周方向に適宜間隔を隔てて形成して構成されて
いる。前記ノズル４は周方向複数の第２スラット６を介
して内筒１に支持されている。また、前記第１供給路４
Ａには、図示しないガス供給源から図示しない導管を介
して燃料ガスが供給される。The first gas supply means includes a nozzle 4 having a first supply path 4A and a second supply path 4B which are independent of each other.
Are arranged in the inner cylinder 1, and a plurality of jet ports 5 for jetting and supplying the fuel gas in the first supply path 4 </ b> A into the inner cylinder 1 are formed in the nozzle 4 at appropriate intervals in the circumferential direction. It is configured. The nozzle 4 is supported by the inner cylinder 1 via a plurality of second slats 6 in the circumferential direction. Further, the first supply path 4
A is supplied with fuel gas from a gas supply source (not shown) via a conduit (not shown).
【００１９】前記第２ガス供給手段は、前記第２供給路
４Ｂにノズル４に形成の連通孔７を介して連通する連通
路８を前記第２スラット６内に形成し、長さ方向の一端
で前記連通路８に連通するノズル管９を前記外筒２の半
径方向に沿う姿勢で中間流路内に配置し、前記第２供給
路４Ｂから連通孔７及び連通路８を介して前記ノズル管
９に供給されてくる燃料ガスを中間流路に噴出するノズ
ル孔１０の複数をノズル管９の長さ方向に適宜間隔を隔
ててノズル管９に形成して構成されている。前記ノズル
孔１０からの燃料ガスの噴出方向は、図３に示すよう
に、接線方向である。また、前記第２供給路４Ｂには、
図示しないガス供給源から図示しない前記とは別の導管
を介して燃料ガスが供給される。The second gas supply means forms a communication passage 8 in the second slat 6, which communicates with the second supply passage 4B through a communication hole 7 formed in the nozzle 4, and has one end in the longitudinal direction. A nozzle pipe 9 communicating with the communication path 8 is disposed in the intermediate flow path in a position along the radial direction of the outer cylinder 2, and the nozzle pipe 9 is connected to the nozzle via the communication hole 7 and the communication path 8 from the second supply path 4 </ b> B. A plurality of nozzle holes 10 for ejecting fuel gas supplied to the pipe 9 into the intermediate flow path are formed in the nozzle pipe 9 at appropriate intervals in the length direction of the nozzle pipe 9. The direction in which the fuel gas is ejected from the nozzle hole 10 is tangential, as shown in FIG. Further, the second supply path 4B includes:
Fuel gas is supplied from a gas supply source (not shown) through another conduit (not shown).
【００２０】そして、前記中間流路のうち、前記ノズル
管９を備えた燃料混入部よりも空気流れ方向で上流側に
は、供給されてくる空気に外筒２周りの旋回力を付与す
る空気スワラー１１が配置され、また、前記外筒２の混
合気流れ方向の下流端には、燃焼開始部となる流路拡大
部１２が連設されている。つまり、中間流路のうち、前
記燃料混入部と流路拡大部１２の始端位置との間の部分
が、メイン燃焼用混合流路Ａ２となっている。In the intermediate flow path, upstream of the fuel mixing portion provided with the nozzle pipe 9 in the air flow direction, air for imparting a turning force around the outer cylinder 2 to the supplied air. A swirler 11 is arranged, and a flow passage expanding portion 12 serving as a combustion start portion is continuously provided at a downstream end of the outer cylinder 2 in the air-fuel mixture flow direction. That is, a portion of the intermediate flow path between the fuel mixing section and the start end position of the flow path expansion section 12 is the main combustion mixing flow path A2.
【００２１】また、前記内筒１内には、内筒１内の燃料
ガスと空気との混合気に内筒１周りの旋回力を付与する
混合気スワラー１３が配置されており、この混合気スワ
ラー１３が前記パイロット領域Ａ１の開始位置を規定す
るものである。なお、この実施の形態では、混合気スワ
ラー１３を設けることでパイロット領域Ａ１の開始位置
を規定するようにしたが、混合気スワラー１３に代えて
混合気噴出孔付きのバーナプレートを設けることにより
パイロット領域の開始位置を規定しても良い。要する
に、前記パイロット領域の開始位置を規定する手段は適
宜変更可能である。Further, a mixture swirler 13 for applying a swirling force around the inner cylinder 1 to the mixture of the fuel gas and the air in the inner cylinder 1 is disposed in the inner cylinder 1. The swirler 13 defines the start position of the pilot area A1. In this embodiment, the start position of the pilot area A1 is defined by providing the mixture swirler 13, but by providing a burner plate with a mixture ejection hole instead of the mixture swirler 13, The start position of the area may be defined. In short, the means for defining the start position of the pilot area can be changed as appropriate.
【００２２】なお、内筒１は、本体１Ａと、混合気流れ
方向の終端部分において、メイン燃焼用混合流路Ａ２を
流れてきた混合気の一部をパイロット領域Ａ１に混合さ
せるエアステージリング１Ｂとから構成されており、こ
のエアステージリング１Ｂの終端位置が前記パイロット
領域Ａ１の終端位置となっている。The inner cylinder 1 has an air stage ring 1B which mixes a part of the air-fuel mixture flowing through the main combustion mixing flow path A2 into the pilot region A1 at the end of the main body 1A in the air-fuel mixture flow direction. The end position of the air stage ring 1B is the end position of the pilot area A1.
【００２３】そして、前記パイロット領域Ａ１の開始位
置は、前記メイン燃焼用混合流路Ａ２の混合気流れ方向
の中央よりもパイロット燃焼炎流れ方向下流側に設定さ
れ、前記内筒１の内径Ｄと前記パイロット領域Ａ１のパ
イロット燃焼炎流れ方向の長さＬとの比Ｌ／Ｄは、０．
１以上で１．５以下に設定され、パイロット領域Ａ１の
終端位置のメイン燃焼用混合流路Ａ２の終端から上流側
への後退長さＬＢは、メイン燃焼用混合流路Ａ２の長さ
をＡとすると、０．０５Ａ≦ＬＢ≦０．３０Ａに設定さ
れている。The start position of the pilot region A1 is set on the downstream side in the pilot combustion flame flow direction from the center of the main combustion mixing flow path A2 in the air-fuel mixture flow direction. The ratio L / D of the pilot region A1 to the length L in the pilot combustion flame flow direction is 0.1.
The retreat length LB from the end of the main combustion mixing flow path A2 at the end position of the pilot area A1 to the upstream side is set to 1 or more and 1.5 or less, and the length of the main combustion mixing flow path A2 is set to A. Then, 0.05A ≦ LB ≦ 0.30A is set.
【００２４】上記構成のバーナ装置では、混合気スワラ
ー１３で旋回力を付与されたパイロット領域Ａ１内の混
合気に図示しない点火装置で点火することにより、この
混合気が着火燃焼して、パイロット燃焼が起こり、この
パイロット燃焼の炎が、メイン燃焼用混合流路Ａ２を流
れてきた混合気に火移りすることで混合気が着火燃焼し
て、メイン燃焼が起こる。In the burner apparatus having the above structure, the mixture in the pilot area A1 to which the swirling force is applied by the mixture swirler 13 is ignited by an igniter (not shown). Then, the flame of the pilot combustion is transferred to the air-fuel mixture flowing through the main combustion mixing flow path A2, so that the air-fuel mixture ignites and burns, and the main combustion occurs.
【００２５】[0025]
【実施例】因みに、本発明の効果を確認するために本発
明者が行った実験を次に示す。本発明のバーナ装置とし
て、上記実施の形態で示した構造でＬ／Ｄが１．２のバ
ーナ装置を用意し、比較対象バーナ装置として、上記従
来の技術で説明した構造でＬ／Ｄが２．５のバーナ装置
を用意した。そして、本発明のバーナ装置については、
定格（当量比Φ＝０．３５、メイン燃料流量１８．４ｍ
3 ／ｈ（標準状態）、パイロット燃料流量１．０ｍ3 ／
ｈ（標準状態），ＴＩＴ（燃焼器出口平均温度）＝１０
００℃）でＮＯｘ１０ｐｐｍ以下（酸素０％換算）、燃
焼効率９９％以上で大気開放燃焼試験を行った。また、
比較対象バーナ装置については、定格（当量比Φ＝０．
３５、メイン燃料流量１７．５ｍ3 ／ｈ（標準状態）、
パイロット燃料流量１．９ｍ3 ／ｈ（標準状態），ＴＩ
Ｔ（燃焼器出口平均温度）＝１０００℃）でＮＯｘ１３
ｐｐｍ以下（酸素０％換算）、燃焼効率９９％以上で大
気開放燃焼試験を行った。以上の実験で、本発明のバー
ナ装置では、当量比Φ０．３５のときの燃料量のうちパ
イロット燃料量が占める割合を５% に減らしても、燃焼
振動が発生しないことが判明し、比較対象バーナ装置で
は、１０% に減らすと、燃焼振動が発生することが判明
した。EXAMPLES Incidentally, experiments performed by the present inventors to confirm the effects of the present invention will be described below. As the burner device of the present invention, a burner device having an L / D of 1.2 in the structure shown in the above embodiment is prepared, and a burner device to be compared having an L / D of 2 in the structure described in the above prior art is used. .5 was prepared. And about the burner device of the present invention,
Rating (equivalent ratio Φ = 0.35, main fuel flow rate 18.4m
3 / h (standard condition), pilot fuel flow rate 1.0m 3 /
h (standard state), TIT (combustor outlet average temperature) = 10
(00 ° C.), NOx was 10 ppm or less (converted to 0% oxygen), and the combustion efficiency was 99% or more. Also,
For the burner device to be compared, the rating (equivalent ratio Φ = 0.
35, main fuel flow rate 17.5 m 3 / h (standard condition),
Pilot fuel flow rate 1.9m 3 / h (standard condition), TI
NOx13 at T (Average temperature of combustor outlet) = 1000 ° C
An open-air combustion test was performed at a ppm or less (converted to 0% oxygen) and a combustion efficiency of 99% or more. From the above experiments, it was found that in the burner device of the present invention, even if the ratio of the pilot fuel amount to the fuel amount at the equivalent ratio Φ0.35 was reduced to 5%, no combustion oscillation was generated. It was found that when the burner device was reduced to 10%, combustion oscillation occurred.
【図１】バーナ装置の縦断側面図FIG. 1 is a longitudinal side view of a burner device.
【図２】バーナ装置の横断正面図FIG. 2 is a cross-sectional front view of the burner device.
【図３】ノズル孔からの燃料ガス噴出方向を示す図面FIG. 3 is a view showing a direction in which fuel gas is ejected from a nozzle hole.
１ 内筒 ２ 外筒 １２ 流路拡大部 Ａ１ パイロット領域 Ａ２ メイン燃焼用混合流路 DESCRIPTION OF SYMBOLS 1 Inner cylinder 2 Outer cylinder 12 Channel expansion part A1 Pilot area A2 Mixing channel for main combustion
Claims (3)
内筒を外囲する中間流路を規定する外筒とを設け、前記
中間流路において、混合気流れ方向で、燃料混入部と前
記外筒に設けられる流路拡大部である燃焼開始部との間
に規定されるメイン燃焼用混合流路を設けてあるバーナ
装置であって、前記パイロット領域の開始位置を、前記
メイン燃焼用混合流路の混合気流れ方向の中央よりもパ
イロット燃焼炎流れ方向下流側に設定してあるバーナ装
置。An inner cylinder defining a pilot region and an outer cylinder defining an intermediate flow path surrounding the inner cylinder are provided. A burner device provided with a main combustion mixing flow path defined between a combustion start part that is a flow path expansion part provided in an outer cylinder, wherein the start position of the pilot region is determined by the main combustion mixing flow path. A burner device which is set on the downstream side in the flow direction of the pilot combustion flame from the center of the flow direction of the air-fuel mixture.
筒の内径Ｄと前記パイロット領域のパイロット燃焼炎流
れ方向の長さＬとの比Ｌ／Ｄが０．１以上で１．５以下
に設定されている請求項１記載のバーナ装置。2. The method according to claim 1, wherein the inner cylinder has a cylindrical shape, and the ratio L / D of the inner diameter D of the inner cylinder to the length L of the pilot region in the pilot combustion flame flow direction is 0.1 or more. The burner device according to claim 1, wherein the number is set to 5 or less.
終端位置である前記パイロット領域の終端位置を、前記
外筒の流路拡大部の始端位置である前記メイン燃焼用混
合流路の終端よりも前記混合気流れ方向での上流側に設
定してある請求項１又は２記載のバーナ装置。3. The end position of the pilot region, which is the end position of the inner cylinder in the flow direction of the air-fuel mixture, is shifted from the end of the main combustion mixing flow passage, which is the start end position of the enlarged flow path portion of the outer cylinder. The burner device according to claim 1, wherein the pressure is also set on the upstream side in the flow direction of the air-fuel mixture.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2000041170A JP4033596B2 (en) | 2000-02-18 | 2000-02-18 | Burner equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2000041170A JP4033596B2 (en) | 2000-02-18 | 2000-02-18 | Burner equipment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP2001235119A true JP2001235119A (en) | 2001-08-31 |
| JP4033596B2 JP4033596B2 (en) | 2008-01-16 |
Family
ID=18564442
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2000041170A Expired - Fee Related JP4033596B2 (en) | 2000-02-18 | 2000-02-18 | Burner equipment |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP4033596B2 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2002073091A1 (en) * | 2001-03-09 | 2002-09-19 | Osaka Gas Co., Ltd. | Burner and gas turbine engine |
| JP2010190540A (en) * | 2009-02-20 | 2010-09-02 | Mitsubishi Heavy Ind Ltd | Combustor and gas turbine |
| CN109724080A (en) * | 2019-02-13 | 2019-05-07 | 郑州立德机电设备有限公司 | A kind of burner noz(zle) for natural gas air Mixture |
-
2000
- 2000-02-18 JP JP2000041170A patent/JP4033596B2/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2002073091A1 (en) * | 2001-03-09 | 2002-09-19 | Osaka Gas Co., Ltd. | Burner and gas turbine engine |
| JP2010190540A (en) * | 2009-02-20 | 2010-09-02 | Mitsubishi Heavy Ind Ltd | Combustor and gas turbine |
| CN109724080A (en) * | 2019-02-13 | 2019-05-07 | 郑州立德机电设备有限公司 | A kind of burner noz(zle) for natural gas air Mixture |
| CN109724080B (en) * | 2019-02-13 | 2023-09-22 | 郑州立德机电设备有限公司 | Combustion nozzle for natural gas-air mixture |
Also Published As
| Publication number | Publication date |
|---|---|
| JP4033596B2 (en) | 2008-01-16 |
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