JP2003014233A - Fuel injection nozzle for gas turbine - Google Patents
Fuel injection nozzle for gas turbineInfo
- Publication number
- JP2003014233A JP2003014233A JP2002121074A JP2002121074A JP2003014233A JP 2003014233 A JP2003014233 A JP 2003014233A JP 2002121074 A JP2002121074 A JP 2002121074A JP 2002121074 A JP2002121074 A JP 2002121074A JP 2003014233 A JP2003014233 A JP 2003014233A
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- nozzle cylinder
- air
- air nozzle
- cylinder
- 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
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
Description
【0001】[0001]
【発明の属する技術分野】本発明はガスタービン用燃料
噴射ノズルに関し,特に,第1空気ノズル筒を中心部に
配置して,その外周に燃料ノズル筒,第2空気ノズル筒
及び第3空気ノズル筒を順次同心上に配置すると共に,
燃焼室に開口する第1空気ノズル筒,燃料ノズル筒,第
2空気ノズル筒及び第3空気ノズル筒の噴孔を,その順
で軸方向に沿って燃焼室側にオフセットし,燃料ノズル
筒の入口には燃料マニホールドを接続し,第1〜第3空
気ノズル筒の入口は圧縮空気室に開口し,各燃料及び空
気ノズル筒には,それを通る燃料又は空気に旋回流を付
与するスワーラ手段と,各噴孔の直前に位置するテーパ
状の絞り込み部とを設けたものに関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a fuel injection nozzle for a gas turbine, and more particularly, a first air nozzle cylinder is arranged at a central portion, and a fuel nozzle cylinder, a second air nozzle cylinder and a third air nozzle are provided on the outer periphery thereof. The cylinders are sequentially arranged concentrically, and
The nozzle holes of the first air nozzle cylinder, the fuel nozzle cylinder, the second air nozzle cylinder, and the third air nozzle cylinder that open to the combustion chamber are offset in that order along the axial direction toward the combustion chamber side, A fuel manifold is connected to the inlet, the inlets of the first to third air nozzle cylinders are opened to the compressed air chamber, and a swirler means for imparting a swirling flow to the fuel or air passing through each fuel and air nozzle cylinder And a tapered narrowed portion located immediately before each injection hole.
【0002】[0002]
【従来の技術】かゝるガスタービン用燃料噴射ノズル
は,例えば米国特許5,417,054号明細書に開示
されているように,既に知られている。BACKGROUND OF THE INVENTION Fuel injection nozzles for such gas turbines are already known, for example as disclosed in US Pat. No. 5,417,054.
【0003】[0003]
【発明が解決しようとする課題】ガスタービンにおい
て,燃料噴射ノズルから噴出する燃料を微粒化すること
は,着火性及び低燃費性を向上する上で極めて重要であ
る。また所望の燃焼方式や燃焼室形状に対して燃料の噴
霧パターンを最適な円錐形状に安定させることは,着火
性,保炎性及び低エミッション性を確保する上で重要で
ある。In the gas turbine, it is extremely important to atomize the fuel ejected from the fuel injection nozzle in order to improve the ignitability and the fuel economy. Further, stabilizing the fuel spray pattern in an optimum conical shape for a desired combustion method or combustion chamber shape is important for ensuring ignitability, flame holding property, and low emission property.
【0004】本発明は,かゝる点に鑑みて,燃料の微粒
化及び円錐状噴霧パタ−ンの安定化を図り,着火性,低
燃費性及び保炎性を向上させ得る,前記ガスタービン用
燃料噴射ノズルを提供することを目的とする。In view of the above points, the present invention aims to improve the ignitability, the fuel economy and the flame retention by atomizing the fuel and stabilizing the conical spray pattern. A fuel injection nozzle for a vehicle is provided.
【0005】[0005]
【課題を解決するための手段】上記目的を達成するため
に,本発明は,第1空気ノズル筒を中心部に配置して,
その外周に燃料ノズル筒,第2空気ノズル筒及び第3空
気ノズル筒を順次同心上に配置すると共に,燃焼室に開
口する第1空気ノズル筒,燃料ノズル筒,第2空気ノズ
ル筒及び第3空気ノズル筒の噴孔を,その順で軸方向に
沿って燃焼室側にオフセットし,燃料ノズル筒の入口に
は燃料マニホールドを接続し,第1〜第3空気ノズル筒
の入口は圧縮空気室に開口し,各燃料及び空気ノズル筒
には,それを通る燃料又は空気に旋回流を付与するスワ
ーラ手段と,各噴孔の直前に位置するテーパ状の絞り込
み部とを設けた,ガスタービン用燃料噴射ノズルにおい
て,燃料ノズル筒の噴孔の内面を,該噴孔から噴出する
燃料を円筒膜状に形成すべく円筒状整流面となし,第1
空気ノズル筒の噴孔を,該噴孔からの空気流が燃料ノズ
ル筒の噴孔から噴出した前記円筒膜状の燃料に衝突する
ように形成すると共に,燃料ノズル筒内のスワーラ手段
の捩じれ方向と,第1空気ノズル筒内のスワーラ手段の
捩じれ方向とを互いに反対に設定したことを第1の特徴
とする。In order to achieve the above-mentioned object, the present invention has a first air nozzle cylinder arranged at the center,
A fuel nozzle cylinder, a second air nozzle cylinder, and a third air nozzle cylinder are sequentially arranged concentrically on the outer periphery thereof, and a first air nozzle cylinder, a fuel nozzle cylinder, a second air nozzle cylinder, and a third air nozzle cylinder that open to the combustion chamber The injection holes of the air nozzle cylinder are offset in that order toward the combustion chamber along the axial direction, the fuel manifold is connected to the inlet of the fuel nozzle cylinder, and the inlets of the first to third air nozzle cylinders are compressed air chambers. For gas turbines, each of the fuel and air nozzle cylinders is provided with swirler means for imparting a swirl flow to the fuel or air passing therethrough and a tapered narrowing portion located immediately before each injection hole. In the fuel injection nozzle, the inner surface of the injection hole of the fuel nozzle cylinder is formed as a cylindrical straightening surface for forming the fuel ejected from the injection hole into a cylindrical film shape.
The nozzle hole of the air nozzle cylinder is formed so that the air flow from the nozzle hole collides with the cylindrical film-like fuel ejected from the nozzle hole of the fuel nozzle cylinder, and the twisting direction of the swirler means in the fuel nozzle cylinder is formed. The first feature is that the twisting direction of the swirler means in the first air nozzle cylinder is set to be opposite to each other.
【0006】この第1の特徴によれば,燃料ノズル筒
は,これを通過する燃料をスワーラ手段により旋回させ
つゝ,噴孔の整流面で円筒膜状の流れに整流される。一
方,第1空気ノズル筒は,圧縮空気室から流入する高圧
空気をスワーラ手段により旋回させつゝ噴孔の整流面で
整流させて,燃料ノズル筒の噴孔に向かわせ,その空気
の旋回方向は,燃料ノズル筒から噴出する円筒膜状の燃
料の旋回方向とが正反対であるので,燃料ノズル筒から
噴出する燃料と,第1空気ノズル筒の噴孔から噴出する
空気とが激しく衝突し合って,燃料の微粒化と,燃料及
び空気の混合とを効果的に行うことができる。また第2
空気ノズル筒からの噴出する空気によって,上記燃料の
微粒化を更に促進することができ,着火性及び低燃費性
の向上を図ることができる。According to the first feature, in the fuel nozzle cylinder, while the fuel passing therethrough is swirled by the swirler means, it is rectified into a cylindrical film-like flow by the rectification surface of the injection hole. On the other hand, the first air nozzle cylinder swirls the high-pressure air flowing from the compressed air chamber by the swirler means to straighten it by the straightening surface of the nozzle hole and directs it toward the nozzle hole of the fuel nozzle cylinder. Of the cylindrical film-like fuel ejected from the fuel nozzle cylinder is opposite to the swirling direction, the fuel ejected from the fuel nozzle cylinder and the air ejected from the injection hole of the first air nozzle cylinder violently collide with each other. Thus, atomization of fuel and mixing of fuel and air can be effectively performed. The second
The atomization of the fuel can be further promoted by the air ejected from the air nozzle cylinder, and the ignitability and the fuel economy can be improved.
【0007】また本発明は,第1の特徴に加えて,第2
空気ノズル筒内のスワーラ手段の捩じれ方向と,第3空
気ノズル筒のスワーラ手段の捩じれ方向とを同方向に設
定すると共に,第2空気ノズル筒のスワーラ手段の捩じ
れ角よりも第3空気ノズル筒の内のスワーラ手段の捩じ
れ角を大きく設定し,且つ第2空気ノズル筒の絞り込み
部のテーパ角よりも,第3空気ノズル筒の絞り込み部の
テーパ角を大きく設定したことを第2の特徴とする。In addition to the first feature, the present invention has a second feature.
The twisting direction of the swirler means in the air nozzle cylinder and the twisting direction of the swirler means of the third air nozzle cylinder are set to be the same direction, and the twisting angle of the swirler means of the second air nozzle cylinder is set to be larger than the twisting angle of the swirler means. The second characteristic is that the twist angle of the swirler means is set large and the taper angle of the narrowing portion of the third air nozzle cylinder is set to be larger than the taper angle of the narrowing portion of the second air nozzle cylinder. To do.
【0008】この第2の特徴によれば,主として第3空
気ノズル筒から噴出する空気により,混合気の噴霧パタ
ーンの外周部の混合を促進し,着火性及び保炎性の向上
を図ることができる。According to the second feature, it is possible to promote the mixing of the outer peripheral portion of the spray pattern of the air-fuel mixture mainly by the air ejected from the third air nozzle cylinder, and to improve the ignitability and the flame holding property. it can.
【0009】[0009]
【発明の実施の形態】本発明の実施の形態を,添付図面
に示す本発明の一実施例に基づいて以下に説明する。BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of the present invention will be described below based on an embodiment of the present invention shown in the accompanying drawings.
【0010】図1は本発明の燃料噴射ノズルを備えるガ
スタービンの要部縦断面図,図2は上記燃料噴射ノズル
の拡大縦断面図,図3は上記燃料噴射ノズルにおける第
1空気ノズル筒の側面図,図4は図3の3−3線断面図
である。FIG. 1 is a longitudinal sectional view of a main part of a gas turbine equipped with a fuel injection nozzle of the present invention, FIG. 2 is an enlarged vertical sectional view of the fuel injection nozzle, and FIG. 3 is a first air nozzle cylinder of the fuel injection nozzle. A side view and FIG. 4 are sectional views taken along line 3-3 of FIG.
【0011】先ず,図1において,ガスタービンのエン
ジンケース1に,図示しないコンプレッサの出口に連な
る圧縮空気室2が形成されており,この圧縮空気室2内
にアンニュラ型燃焼室3が配設される。この燃焼室3
は,円筒状のインナケーシング4と,このインナケーシ
ング4を囲繞する円筒状のアウタケーシング5とから構
成され,そのアウタケーシング5の一端には,インナケ
ーシング4の一端に連結される環状の端壁5aが一体に
連設されている。この端壁5aに,環状に配列される複
数の燃料噴射ノズルNがそれぞれノズル支持手段6を介
して取り付けられる。ノズル支持手段6は,前記端壁5
aに内端を固着される漏斗状の支持ベース7と,この支
持ベース7の外端に形成されたフランジ部7aに取り付
けられる保持環8とからなっており,その保持環が燃料
噴射ノズルNを外周側から保持するようになっている。First, in FIG. 1, a compressed air chamber 2 is formed in an engine case 1 of a gas turbine and communicates with an outlet of a compressor (not shown), and an annular combustion chamber 3 is arranged in the compressed air chamber 2. It This combustion chamber 3
Is composed of a cylindrical inner casing 4 and a cylindrical outer casing 5 surrounding the inner casing 4. One end of the outer casing 5 has an annular end wall connected to one end of the inner casing 4. 5a are integrally connected. A plurality of fuel injection nozzles N arranged in an annular shape are attached to the end wall 5a via nozzle supporting means 6, respectively. The nozzle supporting means 6 is provided with the end wall 5
The support base 7 has a funnel-shaped support base whose inner end is fixed to a, and a holding ring 8 attached to a flange portion 7a formed on the outer end of the support base 7. The holding ring 8 has a holding ring. Is held from the outer peripheral side.
【0012】図2に示すように,燃料噴射ノズルNは,
第1空気ノズル筒10と,この第1空気ノズル筒10の
外周に嵌合した燃料ノズル筒11と,この燃料ノズル筒
11を囲繞する第2空気ノズル筒12と,この第2空気
ノズル筒12を囲繞する第3空気ノズル筒13とを,そ
れぞれの噴孔10c〜13cを燃焼室3に向けながら同
心状に結合して構成され,それらの噴孔10c〜13c
は,第1空気ノズル筒10,燃料ノズル筒11,第2空
気ノズル筒12及び第3空気ノズル筒13の順で軸方向
に沿って燃焼室3側へオフセット配置される。As shown in FIG. 2, the fuel injection nozzle N is
A first air nozzle cylinder 10, a fuel nozzle cylinder 11 fitted on the outer periphery of the first air nozzle cylinder 10, a second air nozzle cylinder 12 surrounding the fuel nozzle cylinder 11, and a second air nozzle cylinder 12 And a third air nozzle cylinder 13 that surrounds each of the injection holes 10c to 13c concentrically with the injection holes 10c to 13c facing the combustion chamber 3.
Are arranged in the order of the first air nozzle cylinder 10, the fuel nozzle cylinder 11, the second air nozzle cylinder 12 and the third air nozzle cylinder 13 along the axial direction toward the combustion chamber 3 side.
【0013】図2〜図4に示すように,第1空気ノズル
筒10及び燃料ノズル筒11の上流端には,燃料・空気
分配ブロック15が嵌着される。第1空気ノズル筒10
の空気路16の上流側は,この燃料・空気分配ブロック
15まで延長しており,この空気路16に上流部に連な
る複数の空気入口孔17(スワーラ手段)が空気路16
の接線方向に沿って燃料・空気分配ブロック15に設け
られ,これら空気入口孔17を通して空気路16に圧縮
空気室2の高圧空気が供給されると,空気路16で空気
の旋回流を生じさせるようになっている。空気路16
は,その噴孔10cの手前にテーパ状の絞り込み部10
bを有しており,この絞り込み部10bの小径端に連な
る円筒状の整流面20で噴孔10cの内周面が形成され
る。As shown in FIGS. 2 to 4, a fuel / air distribution block 15 is fitted to the upstream ends of the first air nozzle cylinder 10 and the fuel nozzle cylinder 11. First air nozzle cylinder 10
The upstream side of the air passage 16 extends to the fuel / air distribution block 15, and a plurality of air inlet holes 17 (swirl means) connected to the upstream portion of the air passage 16 are provided in the air passage 16.
Is provided in the fuel / air distribution block 15 along the tangential direction of, and when the high pressure air of the compressed air chamber 2 is supplied to the air passage 16 through these air inlet holes 17, a swirling flow of air is generated in the air passage 16. It is like this. Airway 16
Is a tapered narrowing portion 10 in front of the injection hole 10c.
The inner peripheral surface of the injection hole 10c is formed by the cylindrical straightening surface 20 which is continuous with the small diameter end of the narrowed portion 10b.
【0014】また燃料・空気分配ブロック15には,燃
料室25と,この燃料室25から延出して燃料・空気分
配ブロック15の前端面に開口する複数本(図示例では
2本)の燃料通孔26とが設けられ,燃料室25には,
燃料ポンプ27から吐出される燃料を分配する燃料マニ
ホールド28の分岐管28aが接続される。The fuel / air distribution block 15 has a fuel chamber 25 and a plurality of (two in the illustrated example) fuel passages extending from the fuel chamber 25 and opening at the front end surface of the fuel / air distribution block 15. And a hole 26 is provided in the fuel chamber 25.
A branch pipe 28a of a fuel manifold 28 that distributes the fuel discharged from the fuel pump 27 is connected.
【0015】上記各燃料通孔26には,第1空気ノズル
筒10及び燃料ノズル筒11の対向周面,図示例では第
1空気ノズル筒10の外周面に形成されて前端を燃料ノ
ズル筒11内に開口する燃料溝29(図3参照)が設け
られる。この燃料溝29は,少なくとも下流側に,周方
向に傾斜したねじ溝部29a(スワーラ手段)を有して
おり,このねじ溝部29aを通過する燃料に旋回流を与
えるようになっている。その際,この燃料の旋回方向と
空気路16内での空気の旋回方向とが互いに反対となる
ように,ねじ溝部29a及び空気入口孔17は形成され
る。In each of the fuel through holes 26, the front end is formed on the outer peripheral surface of the first air nozzle cylinder 10 and the fuel nozzle cylinder 11 facing each other, that is, the outer peripheral surface of the first air nozzle cylinder 10 in the illustrated example. A fuel groove 29 (see FIG. 3) that opens inside is provided. The fuel groove 29 has a thread groove portion 29a (swirler means) inclined in the circumferential direction at least on the downstream side, and imparts a swirling flow to the fuel passing through the thread groove portion 29a. At this time, the thread groove portion 29a and the air inlet hole 17 are formed so that the swirling direction of the fuel and the swirling direction of the air in the air passage 16 are opposite to each other.
【0016】燃料ノズル筒11は,第1空気ノズル筒1
0の外周面に嵌合する円筒面11aと,この円筒面11
aの燃焼室3側端部に連なるテーパ状の絞り込み部11
bと,この絞り込み部11bの小径端部に連なる噴孔1
1cとを有し,そのテーパ部11cに向かって前記ねじ
溝部29aは開口する。噴孔11cの内周面は円筒状の
整流面21に形成され,その内径D2は,第1空気ノズ
ル筒10の噴孔10cの内径D1と同等もしくはそれよ
り僅かに大径に設定される。The fuel nozzle cylinder 11 is the first air nozzle cylinder 1
Cylindrical surface 11a fitted to the outer peripheral surface of 0, and the cylindrical surface 11a
tapered portion 11 connected to the end of the combustion chamber 3 side of a
b and the injection hole 1 connected to the small diameter end of the narrowed portion 11b
1c, and the thread groove portion 29a opens toward the taper portion 11c. The inner peripheral surface of the injection hole 11c is formed into a cylindrical straightening surface 21, and the inner diameter D2 thereof is set to be equal to or slightly larger than the inner diameter D1 of the injection hole 10c of the first air nozzle cylinder 10.
【0017】第2空気ノズル筒12の噴孔12cは,そ
の円筒状の入口部12aより小径に形成され,それらの
間はテーパ状の絞り込み部12bによって接続される。
入口部12aには,それを通る空気に,第1空気ノズル
筒10内での空気の旋回流と同方向の旋回流を与える複
数のスワーラ壁32(スワーラ手段)が設けられ,また
噴孔12cの内周面は円筒状の整流面22若しくはその
上流側に形成される。The injection hole 12c of the second air nozzle cylinder 12 is formed to have a diameter smaller than that of the cylindrical inlet portion 12a thereof, and they are connected by a tapered narrowed portion 12b.
The inlet portion 12a is provided with a plurality of swirler walls 32 (swirler means) for giving the air passing therethrough a swirling flow in the same direction as the swirling flow of the air in the first air nozzle cylinder 10, and the injection hole 12c. The inner peripheral surface of is formed on the rectifying surface 22 having a cylindrical shape or on the upstream side thereof.
【0018】また第3空気ノズル筒13の噴孔13c
は,その円筒状の入口部13aより小径に形成され,そ
れらの間はテーパ状の絞り込み部13bによって接続さ
れる。この絞り込み部13bのテーパ角度βは,第2空
気ノズル筒12の絞り込み部12bのテーパ角度αより
大きく設定される。この第3空気ノズル筒13の入口部
13aにも,それを通る空気に第1空気ノズル筒10内
での空気の旋回流と同方向の旋回流を与える複数のスワ
ーラ壁33(スワーラ手段)が設けられ,このスワーラ
壁33の捩じれ角は,第2空気ノズル筒12のスワーラ
壁32の捩じれ角より大きく設定される。またこの第3
空気ノズル筒13の噴孔13cの内周面も円筒状の整流
面23に形成される。Further, the injection hole 13c of the third air nozzle cylinder 13
Are formed to have a diameter smaller than that of the cylindrical inlet portion 13a, and they are connected by a tapered narrowed portion 13b. The taper angle β of the narrowed portion 13b is set to be larger than the taper angle α of the narrowed portion 12b of the second air nozzle cylinder 12. The inlet portion 13a of the third air nozzle cylinder 13 is also provided with a plurality of swirler walls 33 (swirler means) that imparts to the air passing therethrough a swirl flow in the same direction as the swirl flow of air in the first air nozzle cylinder 10. The twist angle of the swirler wall 33 is set to be larger than the twist angle of the swirler wall 32 of the second air nozzle cylinder 12. Also this third
The inner peripheral surface of the injection hole 13c of the air nozzle cylinder 13 is also formed on the cylindrical straightening surface 23.
【0019】次に,この実施例の作用について説明す
る。Next, the operation of this embodiment will be described.
【0020】ガスタービンの運転中,燃料マニホールド
28から第1空気ノズル筒10の燃料室25に分配され
た高圧の燃料は,燃料通孔26及び燃料溝29を順次経
て燃料ノズル筒11の噴孔11cに向かうが,燃料溝2
9のねじ溝部29aを通過するとき旋回を強制される。
こうして旋回するようになった燃料は,燃料ノズル筒1
1の絞り込み部11bを移動しながら流速を増した後,
その噴孔11cの整流面21で円筒膜状の流れに整流さ
れ,燃焼室3に向かって噴出する。During operation of the gas turbine, the high-pressure fuel distributed from the fuel manifold 28 to the fuel chamber 25 of the first air nozzle cylinder 10 sequentially passes through the fuel through hole 26 and the fuel groove 29, and then the injection hole of the fuel nozzle cylinder 11. 11c, but fuel groove 2
When passing through the screw groove portion 29a of 9, the turning is forced.
The fuel thus swirled is the fuel nozzle cylinder 1
After increasing the flow velocity while moving the narrowed portion 11b of 1,
The flow is rectified by the flow regulating surface 21 of the injection hole 11c into a cylindrical film-like flow, and jets toward the combustion chamber 3.
【0021】一方,図示しないコンプレッサから圧縮空
気室2に圧送された高圧空気は第1空気ノズル筒10の
空気入口孔17や,第2及び第3空気ノズル筒12,1
3の入口部12a,13aに流入する。On the other hand, the high-pressure air pressure-fed from the compressor (not shown) to the compressed air chamber 2 is used for the air inlet hole 17 of the first air nozzle cylinder 10 and the second and third air nozzle cylinders 12, 1.
3 into the inlet portions 12a and 13a.
【0022】而して,第1空気ノズル筒10の空気入口
孔17に流入した高圧空気は,前述のように旋回しなが
ら空気路16を進み,絞り込み部10bで流速を増し,
整流面20により整流された後,燃料ノズル筒11の噴
孔11cに向かって高速で噴出する。しかも,この噴出
空気の旋回方向は,燃料ノズル筒11から噴出する円筒
膜状の燃料流の旋回方向と正反対となっているから,第
1空気ノズル筒10から噴出した空気の旋回流が,燃料
ノズル筒11から噴出した円筒膜状の燃料流に激しく衝
突して,その燃料を効果的に微粒化しながら,それと混
合して,良好な混合気を生成することになる。Thus, the high-pressure air that has flowed into the air inlet hole 17 of the first air nozzle cylinder 10 travels in the air passage 16 while swirling as described above, and increases in flow velocity at the narrowing portion 10b,
After being rectified by the rectifying surface 20, it is jetted at high speed toward the injection hole 11c of the fuel nozzle cylinder 11. Moreover, since the swirling direction of the jet air is opposite to the swirling direction of the cylindrical film-like fuel flow jetting from the fuel nozzle cylinder 11, the swirling flow of the air jetted from the first air nozzle cylinder 10 is It violently collides with the cylindrical film-like fuel flow ejected from the nozzle cylinder 11, and while effectively atomizing the fuel, it mixes with it to produce a good air-fuel mixture.
【0023】また第2空気ノズル筒12に流入した高圧
空気は,スワーラ壁32を通過するとき旋回を付与さ
れ,絞り込み部12bで流速を増し,整流面22で整流
された後,燃焼室3に噴出し,この空気の旋回流は,前
記混合気に外周側から衝突しながら,旋回力を強化する
ので,混合気内の燃料を更に微粒化しながら,それと混
合する。その結果,燃焼室3内の混合気の空燃比の均一
化をもたらし,着火性及び低燃費性の向上に寄与するこ
とができる。The high-pressure air flowing into the second air nozzle cylinder 12 is swirled when passing through the swirler wall 32, the flow velocity is increased at the narrowing portion 12b, and the flow is rectified by the rectifying surface 22, and then is diverted into the combustion chamber 3. The swirling flow of the air jetting and strengthening the swirling force while colliding from the outer peripheral side of the air-fuel mixture, further mixes the fuel in the air-fuel mixture while further atomizing it. As a result, the air-fuel ratio of the air-fuel mixture in the combustion chamber 3 is made uniform, which can contribute to the improvement of ignitability and fuel economy.
【0024】ところで,第2空気ノズル筒12から噴出
した旋回速度の大きい空気は,遠心力の作用により広角
度に広がろうとし,それを放置すれば,混合気の噴霧パ
ターンが広角度になり過ぎて,燃焼に悪影響を及ぼすこ
とになるが,第3空気ノズル筒13から噴出する空気が
その混合気の噴霧パターンを所定の円錐形状に抑える。By the way, the air having a high swirling velocity ejected from the second air nozzle cylinder 12 tries to spread to a wide angle by the action of centrifugal force, and if left unattended, the mixture spray pattern becomes a wide angle. However, the air ejected from the third air nozzle cylinder 13 suppresses the spray pattern of the air-fuel mixture into a predetermined conical shape.
【0025】即ち,第3空気ノズル筒13に流入した高
圧空気は,入口部13aのスワーラ壁33を通過すると
き旋回を付与され,絞り込み部13bで流速を増し,整
流面23で整流された後,燃焼室3に噴出するが,その
スワーラ壁33の捩じれ角は第2空気ノズル筒12のス
ワーラ壁32の捩じれ角より大きく,絞り込み部13b
のテーパ角度βは第2空気ノズル筒12の絞り込み部1
2bのテーパ角度αより大きいので,主として第3空気
ノズル筒13から噴出する空気により,混合気の噴霧パ
ターンの外周部の混合を促進し,着火性及び保炎性の向
上を図ることができる。That is, the high-pressure air flowing into the third air nozzle cylinder 13 is swirled when passing through the swirler wall 33 of the inlet portion 13a, the flow velocity is increased at the narrowing portion 13b, and after being rectified at the rectifying surface 23. , Is jetted into the combustion chamber 3, but the twist angle of the swirler wall 33 is larger than the twist angle of the swirler wall 32 of the second air nozzle cylinder 12, and the narrowed portion 13b
The taper angle β of is the narrowed portion 1 of the second air nozzle cylinder 12.
Since it is larger than the taper angle α of 2b, it is possible to promote the mixing of the outer peripheral portion of the spray pattern of the air-fuel mixture mainly by the air ejected from the third air nozzle cylinder 13, and to improve the ignitability and flame holding property.
【0026】本発明は上記実施例に限定されるものでは
なく,その要旨を逸脱しない範囲で種々の設計変更が可
能である。例えば,燃焼室3をカン型又はカンニュラ型
に構成することもできる。The present invention is not limited to the above embodiments, and various design changes can be made without departing from the scope of the invention. For example, the combustion chamber 3 can be configured as a can type or a cannula type.
【0027】[0027]
【発明の効果】以上のように本発明の第1の特徴によれ
ば,第1空気ノズル筒を中心部に配置して,その外周に
燃料ノズル筒,第2空気ノズル筒及び第3空気ノズル筒
を順次同心上に配置すると共に,燃焼室に開口する第1
空気ノズル筒,燃料ノズル筒,第2空気ノズル筒及び第
3空気ノズル筒の噴孔を,その順で軸方向に沿って燃焼
室側にオフセットし,燃料ノズル筒の入口には燃料マニ
ホールドを接続し,第1〜第3空気ノズル筒の入口は圧
縮空気室に開口し,各燃料及び空気ノズル筒には,それ
を通る燃料又は空気に旋回流を付与するスワーラ手段
と,各噴孔の直前に位置するテーパ状の絞り込み部とを
設けた,ガスタービン用燃料噴射ノズルにおいて,燃料
ノズル筒の噴孔の内面を,該噴孔から噴出する燃料を円
筒膜状に形成すべく円筒状整流面となし,第1空気ノズ
ル筒の噴孔を,該噴孔からの空気流が燃料ノズル筒の噴
孔から噴出した前記円筒膜状の燃料に衝突するように形
成すると共に,燃料ノズル筒内のスワーラ手段の捩じれ
方向と,第1空気ノズル筒内のスワーラ手段の捩じれ方
向とを互いに反対に設定したので,燃料ノズル筒から噴
出する燃料と,第1空気ノズル筒の噴孔から噴出する空
気とを激しい衝突し合わせて,燃料の微粒化と,燃料及
び空気の混合を効果的に行うことができ,また第2空気
ノズル筒からの噴出する空気によって,上記燃料の微粒
化を更に促進することができ,着火性及び低燃費性の向
上に寄与し得る。As described above, according to the first feature of the present invention, the first air nozzle cylinder is arranged in the central portion, and the fuel nozzle cylinder, the second air nozzle cylinder and the third air nozzle are provided on the outer periphery thereof. The cylinders are sequentially arranged concentrically, and the first chamber opens in the combustion chamber.
The nozzle holes of the air nozzle cylinder, the fuel nozzle cylinder, the second air nozzle cylinder and the third air nozzle cylinder are offset in that order toward the combustion chamber along the axial direction, and the fuel manifold is connected to the inlet of the fuel nozzle cylinder. However, the inlets of the first to third air nozzle cylinders are open to the compressed air chamber, and the swirler means for imparting a swirl flow to the fuel or air passing through the fuel and air nozzle cylinders and immediately before each injection hole. In a fuel injection nozzle for a gas turbine, which is provided with a tapered narrowed portion, a cylindrical straightening surface is formed on the inner surface of the injection hole of the fuel nozzle cylinder so as to form the fuel ejected from the injection hole into a cylindrical film shape. That is, the injection hole of the first air nozzle cylinder is formed so that the air flow from the injection hole collides with the cylindrical film-like fuel ejected from the injection hole of the fuel nozzle cylinder, and The twist direction of the swirler means and the Since the twisting directions of the swirler means in the cylinder are set to be opposite to each other, the fuel ejected from the fuel nozzle cylinder and the air ejected from the injection hole of the first air nozzle cylinder violently collide with each other, and the fine particles of fuel are And the mixture of fuel and air can be effectively performed, and the atomization of the fuel can be further promoted by the air ejected from the second air nozzle cylinder, which can improve the ignitability and the fuel economy. Can contribute to improvement.
【0028】また本発明の第2の特徴によれば,第1の
特徴に加えて,第2空気ノズル筒内のスワーラ手段の捩
じれ方向と,第3空気ノズル筒のスワーラ手段の捩じれ
方向とを同方向に設定すると共に,第2空気ノズル筒の
スワーラ手段の捩じれ角よりも第3空気ノズル筒の内の
スワーラ手段の捩じれ角を大きく設定し,且つ第2空気
ノズル筒の絞り込み部のテーパ角よりも,第3空気ノズ
ル筒の絞り込み部のテーパ角を大きく設定したので,主
として第3空気ノズル筒13から噴出する空気により,
混合気の噴霧パターンの外周部の混合を促進し,着火性
及び保炎性の向上を図ることができる。According to the second feature of the present invention, in addition to the first feature, the twist direction of the swirler means in the second air nozzle cylinder and the twist direction of the swirler means in the third air nozzle cylinder are defined. In the same direction, the twist angle of the swirler means in the third air nozzle cylinder is set to be larger than the twist angle of the swirler means of the second air nozzle cylinder, and the taper angle of the narrowing portion of the second air nozzle cylinder is set. Since the taper angle of the narrowed portion of the third air nozzle cylinder is set to be larger than that of the third air nozzle cylinder,
It is possible to promote the mixing of the outer peripheral portion of the spray pattern of the air-fuel mixture and improve the ignitability and flame holding property.
【図1】本発明の燃料噴射ノズルを備えるガスタービン
の要部縦断面図。FIG. 1 is a longitudinal sectional view of a main part of a gas turbine including a fuel injection nozzle of the present invention.
【図2】上記燃料噴射ノズルの拡大縦断面図。FIG. 2 is an enlarged vertical sectional view of the fuel injection nozzle.
【図3】上記燃料噴射ノズルにおける第1空気ノズル筒
の側面図。FIG. 3 is a side view of a first air nozzle cylinder in the fuel injection nozzle.
【図4】図3の3−3線断面図。4 is a sectional view taken along line 3-3 of FIG.
2・・・・・圧縮空気室
3・・・・・燃焼室
10・・・・第1空気ノズル筒
10b・・・第1空気ノズル筒の絞り込み部
10c・・・第1空気ノズル筒の噴孔
11・・・・燃焼ノズル筒
11b・・・燃焼ノズル筒の絞り込み部
11c・・・燃焼ノズル筒の噴孔
12・・・・第2空気ノズル筒
12b・・・第2空気ノズル筒の絞り込み部
12c・・・第2空気ノズル筒の噴孔
13・・・・第3空気ノズル筒
13b・・・第3空気ノズル筒の絞り込み部
13c・・・第3空気ノズル筒の噴孔
17・・・・第1空気ノズル筒のスワーラ手段(空気入
口孔)
20・・・・第1空気ノズル筒の噴孔の整流面
21・・・・燃焼ノズル筒の噴孔の整流面
22・・・・第2空気ノズル筒の噴孔の整流面
23・・・・第3空気ノズル筒の噴孔の整流面
28・・・・燃料マニホールド
29a・・・燃料ノズル筒のスワーラ手段(ねじ溝部)2 ... Compressed air chamber 3 ... Combustion chamber 10 ... First air nozzle cylinder 10b ... First air nozzle cylinder narrowing portion 10c ... First air nozzle cylinder jet Hole 11 ... Combustion nozzle cylinder 11b ... Narrowing portion of combustion nozzle cylinder 11c ... Injection hole 12 of combustion nozzle cylinder ... Second air nozzle cylinder 12b ... Narrowing of second air nozzle cylinder Portion 12c ... Injection port 13 of second air nozzle cylinder ... Third air nozzle tube 13b ... Narrowing portion of third air nozzle tube 13c ... Injection hole 17 of third air nozzle tube ... ..Swirl means (air inlet hole) of the first air nozzle cylinder 20 ..... Straightening surface 21 of the injection hole of the first air nozzle cylinder ..... Straightening surface 22 of the injection hole of the combustion nozzle cylinder .. Nozzle straightening surface 23 of the second air nozzle cylinder ... Nozzle straightening surface 28 of the third air nozzle cylinder -Fuel manifold 29a: swirler means for the fuel nozzle cylinder (thread groove)
Claims (2)
置して,その外周に燃料ノズル筒(11),第2空気ノ
ズル筒(12)及び第3空気ノズル筒(13)を順次同
心上に配置すると共に,燃焼室(3)に開口する第1空
気ノズル筒(10),燃料ノズル筒(11),第2空気
ノズル筒(12)及び第3空気ノズル筒(13)の各噴
孔(10c〜13c)を,その順で軸方向に沿って燃焼
室(3)側にオフセットし,燃料ノズル筒(11)の入
口には燃料マニホールド(28)を接続し,第1〜第3
空気ノズル筒(10,12,13)の入口は圧縮空気室
(2)に開口し,各燃料及び空気ノズル筒(10〜1
3)には,それを通る燃料又は空気に旋回流を付与する
スワーラ手段(17,29a,32,33)と,各噴孔
(10c〜13c)の直前に位置するテーパ状の絞り込
み部(10b〜13b)とを設けた,ガスタービン用燃
料噴射ノズルにおいて,燃料ノズル筒(11)の噴孔
(11c)の内面を,該噴孔(11c)から噴出する燃
料を円筒膜状に形成すべく円筒状整流面(21)とな
し,第1空気ノズル筒(10)の噴孔(10c)を,該
噴孔(10c)からの空気流が燃料ノズル筒(11)の
噴孔(11c)から噴出した前記円筒膜状の燃料に衝突
するように形成すると共に,燃料ノズル筒(11)内の
スワーラ手段(29a)の捩じれ方向と,第1空気ノズ
ル筒(10)内のスワーラ手段(17)の捩じれ方向と
を互いに反対に設定したことを特徴とする,ガスタービ
ン用燃料噴射ノズル。1. A first air nozzle cylinder (10) is arranged in the central portion, and a fuel nozzle cylinder (11), a second air nozzle cylinder (12) and a third air nozzle cylinder (13) are sequentially arranged on the outer periphery thereof. Each of a first air nozzle cylinder (10), a fuel nozzle cylinder (11), a second air nozzle cylinder (12) and a third air nozzle cylinder (13) which are arranged concentrically and open to the combustion chamber (3) The injection holes (10c to 13c) are offset in that order along the axial direction toward the combustion chamber (3) side, and the fuel manifold (28) is connected to the inlet of the fuel nozzle cylinder (11). Three
The inlet of the air nozzle cylinder (10, 12, 13) is opened to the compressed air chamber (2), and each fuel and air nozzle cylinder (10-1)
3), a swirler means (17, 29a, 32, 33) for imparting a swirl flow to the fuel or air passing through it, and a tapered narrowing portion (10b) located immediately before each injection hole (10c to 13c). To 13b), a fuel injection nozzle for a gas turbine, in which the fuel injected from the injection hole (11c) is formed into a cylindrical film on the inner surface of the injection hole (11c) of the fuel nozzle cylinder (11) The air flow from the injection hole (10c) passes through the injection hole (11c) of the fuel nozzle cylinder (11) through the injection hole (10c) of the first air nozzle cylinder (10) without forming the cylindrical straightening surface (21). The twisting direction of the swirler means (29a) in the fuel nozzle cylinder (11) and the swirler means (17) in the first air nozzle cylinder (10) are formed so as to collide with the jetted cylindrical film-like fuel. Set the twist direction of Wherein the fuel injection nozzle for a gas turbine.
ノズルにおいて,第2空気ノズル筒(12)内のスワー
ラ手段(32)の捩じれ方向と,第3空気ノズル筒(1
3)のスワーラ手段(33)の捩じれ方向とを同方向に
設定すると共に,第2空気ノズル筒(12)のスワーラ
手段(32)の捩じれ角よりも第3空気ノズル筒(1
3)の内のスワーラ手段(33)の捩じれ角を大きく設
定し,且つ第2空気ノズル筒(12)の絞り込み部(1
2b)のテーパ角(α)よりも,第3空気ノズル筒(1
3)の絞り込み部(13b)のテーパ角(β)を大きく
設定したことを特徴とする,ガスタービン用燃料噴射ノ
ズル。2. The fuel injection nozzle for a gas turbine according to claim 1, wherein the twisting direction of the swirler means (32) in the second air nozzle cylinder (12) and the third air nozzle cylinder (1).
The twisting direction of the swirler means (33) of 3) is set to the same direction, and the twisting angle of the swirler means (32) of the second air nozzle tube (12) is larger than the twisting angle of the third air nozzle tube (1).
3), the twist angle of the swirler means (33) is set to be large, and the narrowing portion (1) of the second air nozzle cylinder (12) is set.
2b) taper angle (α), the third air nozzle tube (1
A fuel injection nozzle for a gas turbine, characterized in that the taper angle (β) of the narrowed portion (13b) of 3) is set to be large.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2002121074A JP3986874B2 (en) | 2001-04-23 | 2002-04-23 | Fuel injection nozzle for gas turbine |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2001124826 | 2001-04-23 | ||
JP2001-124826 | 2001-04-23 | ||
JP2002121074A JP3986874B2 (en) | 2001-04-23 | 2002-04-23 | Fuel injection nozzle for gas turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2003014233A true JP2003014233A (en) | 2003-01-15 |
JP3986874B2 JP3986874B2 (en) | 2007-10-03 |
Family
ID=26614032
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2002121074A Expired - Lifetime JP3986874B2 (en) | 2001-04-23 | 2002-04-23 | Fuel injection nozzle for gas turbine |
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2005326144A (en) * | 2004-05-11 | 2005-11-24 | United Technol Corp <Utc> | Fuel injection device and designing method of fuel injection device |
JP2013177990A (en) * | 2012-02-28 | 2013-09-09 | Hitachi Ltd | Gas turbine combustor |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH0783436A (en) * | 1993-09-10 | 1995-03-28 | Fuel Systems Textron Inc | Fuel injector for combustion equipment of gas turbine engine |
JPH09500439A (en) * | 1993-06-01 | 1997-01-14 | プラット アンド ホイットニー カナダ,インコーポレイテッド | Air injection type fuel injection valve mounted in radial direction |
-
2002
- 2002-04-23 JP JP2002121074A patent/JP3986874B2/en not_active Expired - Lifetime
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH09500439A (en) * | 1993-06-01 | 1997-01-14 | プラット アンド ホイットニー カナダ,インコーポレイテッド | Air injection type fuel injection valve mounted in radial direction |
JPH0783436A (en) * | 1993-09-10 | 1995-03-28 | Fuel Systems Textron Inc | Fuel injector for combustion equipment of gas turbine engine |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2005326144A (en) * | 2004-05-11 | 2005-11-24 | United Technol Corp <Utc> | Fuel injection device and designing method of fuel injection device |
JP2013177990A (en) * | 2012-02-28 | 2013-09-09 | Hitachi Ltd | Gas turbine combustor |
CN103292351A (en) * | 2012-02-28 | 2013-09-11 | 株式会社日立制作所 | Gas turbine combustor |
CN103292351B (en) * | 2012-02-28 | 2015-07-29 | 三菱日立电力***株式会社 | Gas turbine burner |
Also Published As
Publication number | Publication date |
---|---|
JP3986874B2 (en) | 2007-10-03 |
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