JP2000039148A - Gas turbine combustor nozzle - Google Patents
Gas turbine combustor nozzleInfo
- Publication number
- JP2000039148A JP2000039148A JP10205289A JP20528998A JP2000039148A JP 2000039148 A JP2000039148 A JP 2000039148A JP 10205289 A JP10205289 A JP 10205289A JP 20528998 A JP20528998 A JP 20528998A JP 2000039148 A JP2000039148 A JP 2000039148A
- Authority
- JP
- Japan
- Prior art keywords
- injection port
- oil fuel
- air
- nozzle
- injected
- 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
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明はガスタービンの燃焼
器ノズルに関し、特にパイロットノズル先端に適用さ
れ、油燃料の噴射に際し、油燃料の未燃分がカーボンと
して先端部へ堆積するのを防止する構造としたものであ
る。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a combustor nozzle for a gas turbine, and more particularly, to a combustor nozzle for a pilot nozzle. It is a structure.
【０００２】[0002]
【従来の技術】ガスタービンのパイロットノズルでは、
中心部に油燃料噴射口を有し、周囲には拡散用の空気噴
射口があり、油燃料を燃焼させると両者の間に燃料の滞
溜域が生じ、そこに燃料油が炭化して付着し、未燃分の
カーボンとなってたまってしまい、ノズル周囲の水噴射
口を塞いだり、拡散空気の流れを妨げたりする不具合が
生じていた。2. Description of the Related Art In a gas turbine pilot nozzle,
There is an oil fuel injection port in the center, and there is an air injection port for diffusion in the periphery, and when burning oil fuel, a fuel accumulation area is created between the two, where the fuel oil carbonizes and adheres However, the unburned carbon is accumulated and causes a problem that the water injection port around the nozzle is blocked or the flow of diffused air is obstructed.
【０００３】図３はガスタービンのパイロットノズルを
示す図であり、図において１はノズル本体を示し、２は
周囲の空気通路で空気１１が吸い込まれる。３は油燃料
供給管で、本体の中心部に設けられ、油燃料１０が導か
れる。４はガス燃料通路であり、ガス燃料を使用する場
合にはガス燃料１２が導かれる。５は油燃料噴射口、６
は空気噴射口、７はガス燃料噴射口である。このような
構成のノズルで油燃料１０とガス燃料１２の両方が使用
可能であり、先端より燃料を噴射し、拡散用の空気１１
と水を図示省略の水噴射口から噴射し、燃焼する構成で
ある。FIG. 3 is a view showing a pilot nozzle of a gas turbine. In FIG. 3, reference numeral 1 denotes a nozzle body, and reference numeral 2 denotes a surrounding air passage into which air 11 is sucked. Reference numeral 3 denotes an oil fuel supply pipe, which is provided at the center of the main body and through which the oil fuel 10 is guided. Reference numeral 4 denotes a gas fuel passage through which a gas fuel 12 is introduced when gas fuel is used. 5 is an oil fuel injection port, 6
Denotes an air injection port, and 7 denotes a gas fuel injection port. Both the oil fuel 10 and the gas fuel 12 can be used with the nozzle having such a configuration.
And water are injected from a water injection port (not shown) and burned.
【０００４】図４は上記に説明したパイロットノズルの
先端部の詳細を部分的に示した断面図であり、図におい
て、油燃料を使用する場合には油燃料供給管３から油燃
料１０が供給され、中心部の油燃料噴射口５より燃焼室
に噴射し燃焼に供される。一方、空気１１は空気通路２
より本体１の周囲を流れて空気噴射口６より噴出した燃
料を拡散させる。又、水９が油燃料噴射口５の周囲の水
噴射口８より噴出し、油燃料噴射口５の周囲を冷却して
いる。FIG. 4 is a cross-sectional view partially showing the details of the tip of the pilot nozzle described above. In the figure, when oil fuel is used, oil fuel 10 is supplied from an oil fuel supply pipe 3. Then, the fuel is injected into the combustion chamber from the oil fuel injection port 5 at the center and is provided for combustion. On the other hand, the air 11 is
The fuel which flows around the body 1 and is ejected from the air injection port 6 is diffused. Water 9 is jetted from the water injection port 8 around the oil fuel injection port 5 to cool the area around the oil fuel injection port 5.
【０００５】上記のノズルにおいて油燃料噴射口５より
噴射した油燃料は図示のように周囲に向かって拡大して
噴射するが、一方空気１１もこれと交差するような角度
で空気噴射口６より噴出しており、両者の間には空気や
燃料の届かない滞溜領域２０が存在する。この滞溜領域
２０に油燃料１０の一部がミスト２１となって飛散して
流入し、これが先端に付着して未燃分カーボン２２とな
って堆積してしまう。この未燃分カーボン２２が徐々に
増加し、水噴射口８を塞ぎ、又空気噴射口６の空気の流
れを妨げるようになり、油燃料噴射口５周囲の冷却性能
を劣化させたり、燃焼性能に影響を与えるようになる。[0005] The oil fuel injected from the oil fuel injection port 5 in the above nozzle is expanded and injected toward the periphery as shown in the figure, while the air 11 is also injected from the air injection port 6 at an angle that intersects the fuel. There is a stagnation area 20 between the two, which does not reach air or fuel. A part of the oil fuel 10 scatters and flows into the stagnation region 20 as a mist 21, which adheres to the tip and deposits as unburned carbon 22. The unburned carbon 22 gradually increases, closes the water injection port 8 and hinders the flow of air from the air injection port 6, deteriorating the cooling performance around the oil fuel injection port 5, and deteriorating the combustion performance. Will affect you.
【０００６】[0006]
【発明が解決しようとする課題】前述のように従来のガ
スタービンのパイロットノズルで油燃料を使用する場合
には、油燃料噴射口５と拡散用の空気噴射口６との間に
滞溜領域２０が生じ、この滞溜領域２０に油燃料のミス
ト２１が飛散して付着し、炭化して未燃分カーボン２２
となって堆積する。そのために水噴射口８が塞がれ、水
が噴射できなくなって油燃料噴射口５周囲の冷却を劣化
させたり、空気の噴射経路を妨げたりしてノズルの性能
に悪影響を及ぼす。As described above, when oil fuel is used in the pilot nozzle of the conventional gas turbine, a stagnation area is provided between the oil fuel injection port 5 and the air injection port 6 for diffusion. The mist 21 of the oil fuel scatters and adheres to the stagnation area 20, carbonizes and unburned carbon 22.
And accumulate. As a result, the water injection port 8 is blocked, and water cannot be injected, thereby deteriorating the cooling around the oil fuel injection port 5 or obstructing the air injection path, adversely affecting the performance of the nozzle.
【０００７】そこで本発明は拡散用の空気の流れ方向を
変えて飛散してくる油燃料のミストが滞溜し、付着しな
いようなノズル先端部の構造として未燃分カーボンの堆
積が生じないようにし、ノズルの信頼性を向上させるよ
うなガスタービン燃焼器ノズルを提供することを課題と
してなされたものである。[0007] Therefore, the present invention is to prevent the accumulation of unburned carbon due to the structure of the nozzle tip that prevents the mist of the scattered oil fuel from accumulating and changing by changing the flow direction of the air for diffusion. SUMMARY OF THE INVENTION It is an object of the present invention to provide a gas turbine combustor nozzle that improves the reliability of the nozzle.
【０００８】[0008]
【課題を解決するための手段】本発明は前述の課題を解
決するために次の手段を提供する。The present invention provides the following means for solving the above-mentioned problems.
【０００９】中心部に油燃料供給管を有し、先端の油燃
料噴射口より油燃料を噴射すると共に、同油燃料供給管
の周囲に設けられた空気通路を通って空気を先端部に導
き同先端部の前記油燃料噴射口の周囲に設けられた空気
噴射口より噴射するガスタービンの燃焼器ノズルにおい
て、前記空気噴射口の出口部を先端部外側から覆い、中
央部が開口するカバーリングを先端部に設けたことを特
徴とするガスタービン燃焼器ノズル。An oil fuel supply pipe is provided at the center, oil fuel is injected from an oil fuel injection port at the tip, and air is guided to the tip through an air passage provided around the oil fuel supply pipe. In a combustor nozzle of a gas turbine injecting from an air injection port provided around the oil fuel injection port at the front end portion, a cover ring covering an outlet portion of the air injection port from outside the front end portion and opening a central portion. A gas turbine combustor nozzle characterized in that a gas turbine combustor nozzle is provided at the tip.
【００１０】本発明のガスタービン燃焼器ノズルは、先
端部にカバーリングが設けられており、このカバーリン
グは先端部周囲の空気噴射口の空気出口部を外側からリ
ング状に覆い、中央部は油燃料噴射口から油燃料が噴射
できるように充分に開口している。従って噴射した空気
はカバーリングによってその流れがノズル中心方向を向
いて流れ、油燃料のミストが飛散して付着しようとする
と、このミストを吹き飛ばし、ミストの付着を防止す
る。従来は空気噴射口と油燃料噴射口との間に滞溜領域
が生じ飛散してきた油燃料のミストが先端部に付着し、
これが炭化して未燃分カーボンとして堆積し、油燃料噴
射口周囲の水噴射口を塞ぐ、等の不具合が生じたが、本
発明ではこのようなミストの付着を防止するので未燃分
カーボンの堆積が発生しない。[0010] The gas turbine combustor nozzle of the present invention is provided with a cover ring at the tip, which covers the air outlet of the air injection port around the tip in a ring shape from the outside, and has a central portion. The opening is sufficiently open so that oil fuel can be injected from the oil fuel injection port. Therefore, the injected air flows toward the center of the nozzle by the covering, and when the mist of the oil fuel scatters and tries to adhere, the mist is blown off to prevent the mist from adhering. Conventionally, a stagnant area is created between the air injection port and the oil fuel injection port, and the mist of the scattered oil fuel adheres to the tip,
This was carbonized and deposited as unburned carbon, which caused problems such as blocking the water injection port around the oil fuel injection port. However, in the present invention, since such mist is prevented from adhering, the unburned carbon No deposition occurs.
【００１１】[0011]
【発明の実施の形態】以下、本発明の実施の形態につい
て図面に基づいて具体的に説明する。図１は本発明の実
施の一形態に係るガスタービンの燃焼器ノズルの先端部
断面図である。図において、符号１乃至１２は図４に示
す従来の構造と同じであるので、詳しい説明は省略し、
そのまま引用して説明するが、本発明の特徴部分は符号
１３で示すカバーリングを設けたものであり、以下に詳
しく説明する。Embodiments of the present invention will be specifically described below with reference to the drawings. FIG. 1 is a sectional view of a tip end portion of a combustor nozzle of a gas turbine according to one embodiment of the present invention. In the figure, reference numerals 1 to 12 have the same structure as the conventional structure shown in FIG.
As will be described as it is, a characteristic part of the present invention is provided with a cover ring indicated by reference numeral 13 and will be described in detail below.
【００１２】図１において先端部には空気噴射口６出口
部近辺を外側から全周にわたって覆うように環状のカバ
ーリング１３が設けられる。リング状のカバーリング１
３の中央部は開口し、中心部の油燃料１０の噴射及び空
気１１の噴射に支障がないようにし、周囲のリングは中
心軸と直交となる方向へ伸び、その長さＬは水噴射口８
を覆うことのない程度に延長して伸びた長さとする。In FIG. 1, an annular cover ring 13 is provided at the front end so as to cover the vicinity of the outlet of the air injection port 6 from the outside over the entire circumference. Ring-shaped cover ring 1
The center of 3 is open so that the injection of oil fuel 10 and the injection of air 11 at the center does not interfere, the surrounding ring extends in a direction perpendicular to the central axis, and its length L is the water injection port. 8
Is extended to such an extent that it does not cover it.
【００１３】上記の構成において、油燃料１０は従来と
同じように油燃料噴射口５から噴射されるが、拡散用の
空気１１は周囲の空気通路２を通り、先端部の空気噴射
口６より噴射され、噴射された空気は、カバーリング１
３が噴射口５出口外側を覆っているので、その流れ方向
は直進せずにノズル中心軸と直交方向に向きを変えて１
１ａのように流れ、油燃料１０と合流して油燃料と共に
流れ、燃焼に供される。In the above configuration, the oil fuel 10 is injected from the oil fuel injection port 5 as in the prior art, but the air 11 for diffusion passes through the surrounding air passage 2 and from the air injection port 6 at the tip. The injected air is injected into the covering 1
Since 3 covers the outside of the outlet of the injection port 5, its flow direction does not go straight but changes its direction in the direction orthogonal to the nozzle center axis.
It flows like 1a, merges with the oil fuel 10, flows with the oil fuel, and is provided for combustion.
【００１４】空気１１は上記のようにノズル中心軸と直
角方向に流れることにより、従来生じていた滞溜領域２
０に飛散してくる油燃料のミスト２１は、この空気流れ
１１ａによりその飛散が妨げられてノズル先端部には付
着せずに燃焼領域に飛ばされて未燃分カーボンとして先
端部に堆積することがなくなる。The air 11 flows in the direction perpendicular to the central axis of the nozzle as described above, and thus the stagnation area 2 which has been generated conventionally.
The mist 21 of the oil fuel scattered to zero is prevented from being scattered by the air flow 11a, and is not attached to the tip of the nozzle, but is skipped to the combustion region and deposited at the tip as unburned carbon. Disappears.
【００１５】図２は図１におけるＡ−Ａ矢視図であり、
カバーリング全体１３を示している。図示のようにカバ
ーリング１３正面部は中央部には円形状に開口部３０を
有し、油燃料噴射口５からの燃料噴射を妨げず、周囲は
リング状にノズルの先端部周囲を覆う構造であり、この
ようなリング状のカバーリング１３により従来生じてい
た滞溜領域の周囲を覆うと共に、噴出する空気により、
この領域を飛散してくる油燃料のミストの侵入を防止す
るものである。FIG. 2 is a view taken in the direction of arrows AA in FIG.
The entire covering 13 is shown. As shown in the drawing, the front surface of the cover ring 13 has a circular opening 30 in the center, does not hinder the fuel injection from the oil fuel injection port 5, and covers the periphery of the tip of the nozzle in a ring shape. With the ring-shaped cover ring 13, the surrounding area of the accumulation region, which has been conventionally generated, is covered.
This prevents the mist of the oil fuel scattered in this region from entering.
【００１６】以上説明のように、本実施の形態によれ
ば、ノズル本体１の先端部周囲に空気噴射口６を覆うよ
うにカバーリング１３を設けたので、先端部に飛散して
くる油燃料のミストを空気により吹き飛ばして先端部に
付着することを防止し、水噴射口８を塞ぐようなことが
なくなり、ノズルの信頼性が向上するものである。As described above, according to the present embodiment, since the cover ring 13 is provided around the tip of the nozzle body 1 so as to cover the air injection port 6, the oil fuel scattered at the tip is provided. The mist is prevented from being blown off by air and adhered to the tip portion, so that the water injection port 8 is not blocked, and the reliability of the nozzle is improved.
【００１７】[0017]
【発明の効果】本発明のガスタービン燃焼器ノズルは、
中心部に油燃料供給管を有し、先端の油燃料噴射口より
油燃料を噴射すると共に、同油燃料供給管の周囲に設け
られた空気通路を通って空気を先端部に導き同先端部の
前記油燃料噴射口の周囲に設けられた空気噴射口より噴
射するガスタービンの燃焼器ノズルにおいて、前記空気
噴射口の出口部を先端部外側から覆い、中央部が開口す
るカバーリングを先端部に設けたことを特徴としてい
る。このような構成により、噴射した空気はカバーリン
グの覆いによってその流れがノズル中心方向に向いて流
れ、飛散してきた油燃料のミストを吹き飛ばし、先端部
に付着するのを防止する。これにより先端部に未燃分カ
ーボンが堆積することがなくノズルの信頼性が著しく向
上するものである。According to the gas turbine combustor nozzle of the present invention,
It has an oil fuel supply pipe in the center, injects oil fuel from the oil fuel injection port at the tip, and guides air to the tip through an air passage provided around the oil fuel supply pipe. In a gas turbine combustor nozzle that injects air from an air injection port provided around the oil fuel injection port, a cover ring that covers the outlet of the air injection port from the outside of the front end and opens at the center is provided at the front end. It is characterized by being provided in. With such a configuration, the injected air flows toward the center of the nozzle by the covering of the covering, thereby blowing off the mist of the scattered oil fuel and preventing it from adhering to the tip. As a result, unburned carbon is not deposited on the tip portion, and the reliability of the nozzle is significantly improved.
【図１】本発明の実施の一形態に係るガスタービンの燃
焼器ノズルの先端部断面図である。FIG. 1 is a sectional view of a distal end portion of a combustor nozzle of a gas turbine according to an embodiment of the present invention.
【図２】図１におけるＡ−Ａ矢視図である。FIG. 2 is a view taken in the direction of arrows AA in FIG.
【図３】従来のガスタービンのパイロットノズルの断面
図である。FIG. 3 is a sectional view of a pilot nozzle of a conventional gas turbine.
【図４】従来のガスタービンのパイロットノズル先端部
の断面図である。FIG. 4 is a sectional view of a pilot nozzle tip of a conventional gas turbine.
１ ノズル本体 ２ 空気通路 ３ 油燃料供給管 ４ ガス燃料通路 ５ 油燃料噴射口 ６ 空気噴射口 ７ ガス燃料噴射口 ８ 水噴射口 １０ 油燃料 １１，１１ａ 空気 １２ ガス燃料 １３ カバーリング ２０ 滞溜領域 ２１ ミスト ３０ 開口部 DESCRIPTION OF SYMBOLS 1 Nozzle main body 2 Air passage 3 Oil fuel supply pipe 4 Gas fuel passage 5 Oil fuel injection port 6 Air injection port 7 Gas fuel injection port 8 Water injection port 10 Oil fuel 11, 11a Air 12 Gas fuel 13 Covering 20 Reservation area 21 mist 30 opening
Claims (1)
燃料噴射口より油燃料を噴射すると共に、同油燃料供給
管の周囲に設けられた空気通路を通って空気を先端部に
導き同先端部の前記油燃料噴射口の周囲に設けられた空
気噴射口より噴射するガスタービンの燃焼器ノズルにお
いて、前記空気噴射口の出口部を先端部外側から覆い、
中央部が開口するカバーリングを先端部に設けたことを
特徴とするガスタービン燃焼器ノズル。An oil fuel supply pipe is provided at a central portion, and oil fuel is injected from an oil fuel injection port at a tip, and air is passed through an air passage provided around the oil fuel supply pipe. In a gas turbine combustor nozzle that injects from an air injection port provided around the oil fuel injection port at the front end portion, the outlet of the air injection port is covered from the outside of the front end portion,
A gas turbine combustor nozzle, wherein a cover ring having an opening at a central portion is provided at a tip portion.
Priority Applications (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10205289A JP2000039148A (en) | 1998-07-21 | 1998-07-21 | Gas turbine combustor nozzle |
| EP99106822A EP0952392B1 (en) | 1998-04-15 | 1999-04-06 | Combustor |
| DE69910106T DE69910106T2 (en) | 1998-04-15 | 1999-04-06 | combustion chamber |
| US09/289,606 US6267583B1 (en) | 1998-04-15 | 1999-04-12 | Combustor |
| CA002268730A CA2268730C (en) | 1998-04-15 | 1999-04-14 | Combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10205289A JP2000039148A (en) | 1998-07-21 | 1998-07-21 | Gas turbine combustor nozzle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JP2000039148A true JP2000039148A (en) | 2000-02-08 |
Family
ID=16504516
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP10205289A Pending JP2000039148A (en) | 1998-04-15 | 1998-07-21 | Gas turbine combustor nozzle |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2000039148A (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1632721A2 (en) | 2004-09-02 | 2006-03-08 | Hitachi, Ltd. | Combustor, gas turbine combustor, and air supply method for the same |
| JP2006071275A (en) * | 2004-09-01 | 2006-03-16 | General Electric Co <Ge> | Method and device for reducing exhaust emission of gas turbine engine |
| JP2008122065A (en) * | 2006-11-10 | 2008-05-29 | General Electric Co <Ge> | High expansion fuel injection slot jet and method for enhancing mixing in premixing devices |
| JP2009168397A (en) * | 2008-01-18 | 2009-07-30 | Mitsubishi Heavy Ind Ltd | Pilot nozzle, gas turbine combustor, and gas turbine |
| JP2009250240A (en) * | 2008-04-09 | 2009-10-29 | General Electric Co <Ge> | Surface treatment for preventing hydrocarbon thermal degradation deposit on article |
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