JPS62247134A - Air-assistance-type fuel injection valve for gas turbine - Google Patents
Air-assistance-type fuel injection valve for gas turbineInfo
- Publication number
- JPS62247134A JPS62247134A JP9096186A JP9096186A JPS62247134A JP S62247134 A JPS62247134 A JP S62247134A JP 9096186 A JP9096186 A JP 9096186A JP 9096186 A JP9096186 A JP 9096186A JP S62247134 A JPS62247134 A JP S62247134A
- Authority
- JP
- Japan
- Prior art keywords
- air
- tip
- fuel injection
- sprayer tip
- gas turbine
- 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
- 239000000446 fuel Substances 0.000 title claims abstract description 47
- 238000002347 injection Methods 0.000 title claims abstract description 30
- 239000007924 injection Substances 0.000 title claims abstract description 30
- 239000007788 liquid Substances 0.000 claims description 6
- 238000007664 blowing Methods 0.000 claims description 2
- 238000002485 combustion reaction Methods 0.000 abstract description 16
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 abstract description 6
- 229910052799 carbon Inorganic materials 0.000 abstract description 6
- 238000000034 method Methods 0.000 description 13
- 238000000889 atomisation Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 3
- 238000004891 communication Methods 0.000 description 2
- 239000006185 dispersion Substances 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 238000005422 blasting Methods 0.000 description 1
- 238000003763 carbonization Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 239000010419 fine particle Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000003758 nuclear fuel Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、ガスタービンのエアアシスト形燃料噴射弁に
関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an air-assisted fuel injection valve for a gas turbine.
周知のように、ガスタービンの燃焼室には液体燃料が導
入され、高速化された空気流れと混合して燃焼する。そ
して、ガスタービン燃焼室内の燃焼は、一旦点火をすれ
ば連続的に安定した燃焼ができなければならない、その
ため、液体燃料は燃料噴射弁により微細な粒子にして連
続状に噴出させ、燃料の蒸発を促進して燃焼速度を上げ
るとともに、燃焼室内へ燃料での適正な分散と分布をδ
する必要がある。As is well known, liquid fuel is introduced into the combustion chamber of a gas turbine and is mixed with a high-velocity air stream and combusted. Once ignited, the combustion inside the gas turbine combustion chamber must be continuous and stable. Therefore, the liquid fuel is made into fine particles by the fuel injection valve and continuously injected, resulting in evaporation of the fuel. In addition to increasing the combustion rate, it also increases the proper dispersion and distribution of fuel within the combustion chamber.
There is a need to.
そこで、液体燃料を微粒化する方法には、】）燃料自身
による微粒化、２）補助手段を用いる微粒化とに大別で
きるが、後者に属するものの一つとして、燃料流れを空
気または蒸気によって吹切る方法が知られている。かか
る方法に属するものとして、更に、ブラストエア法とア
シストエア法とが知られている。Therefore, methods for atomizing liquid fuel can be roughly divided into 1) atomization using the fuel itself, and 2) atomization using auxiliary means. As one of the methods belonging to the latter, there is a method of atomizing the fuel flow by air or steam. A method of blowing it off is known. Blast air methods and assisted air methods are also known as such methods.
ところで、本発明に係るアシストエア法は、高圧のエア
を用いるブラスト法とは違い、低圧エアを用いることに
より、燃料の微粒化を補助する方法で、これは例えば、
ガスタービンの着火時は、０．５／ｄ程度の燃料油圧を
ライナーに定常的に供給しながら、同程度のエア圧のア
シストエアを吹込み、また、定格運転時には、アシスト
エアのエア圧はそのままで、燃料油圧は３５ｋｇ／−程
度増圧して定常的にライナーへ供給し、該アシストエア
により微粒化の補助を行う方法である。Incidentally, unlike the blasting method that uses high-pressure air, the assist air method according to the present invention is a method that uses low-pressure air to assist in atomizing the fuel.
When igniting a gas turbine, while constantly supplying fuel oil pressure of about 0.5/d to the liner, assist air of the same air pressure is blown into the liner, and during rated operation, the air pressure of the assist air is In this method, the fuel oil pressure is increased by about 35 kg/- and is constantly supplied to the liner, and the assist air is used to assist in atomization.
かかるアシストエア法を用いる燃料噴射弁は、メイン孔
およびプライマリ孔を並設した渦巻き式の燃料噴射弁に
比べ、構造簡単であり、広い範囲の液体燃料が使用でき
、しかも、スワラ−流の制御が容易であるという長所が
あるものの、環状に形成されたアシストエア噴孔と、そ
の中心に位置する１個の燃料噴孔との間のスプレィチッ
プ先端面にカーボンが堆積し、それが徐々に成長してエ
アアシストスワラ−からのアシストエアの流れを乱し、
殊にライナーに装着されている点火栓への燃料分散を悪
くし、着火ミスが発生しやすくなる、という問題がある
。A fuel injection valve using this assist air method has a simpler structure than a spiral fuel injection valve in which a main hole and a primary hole are arranged side by side, can use a wide range of liquid fuels, and can control the swirler flow. However, carbon accumulates on the tip of the spray tip between the annularly formed assist air nozzle and one fuel nozzle located in the center, and it gradually It grows and disturbs the flow of assist air from the air assist swirler.
In particular, there is a problem in that fuel dispersion to the ignition plug attached to the liner becomes poor, making ignition errors more likely to occur.
かかるカーボン堆積の原因は、エアアシスト形燃料噴射
弁では、ガスタービン定格運転時に燃料自体の噴出とア
シストエアの助勢とで液体燃料は微粒化が進みすぎ、炭
化しやすくなる傾向があるため、カーボンの付着が生成
しやすい、ということに起因するが、本来、燃料噴射弁
の適否が燃焼効率、燃焼状態に重大な影響を及ぼすので
、設計変更して容易にその対策を構じることができない
。The cause of such carbon deposits is that in air-assisted fuel injection valves, during rated operation of the gas turbine, the liquid fuel tends to become too atomized due to the jetting of the fuel itself and the assistance of assist air, making it easy to carbonize. However, since the suitability of the fuel injector has a significant impact on combustion efficiency and combustion conditions, it is not possible to easily take measures against this problem by changing the design. .
したがって、現在、エアアシスト形燃料噴射弁を備えた
ガスタービンでは、そのメンテナンス時に分解して、Ｉ
ＩＩＩ ｉｌされたカーボンを手作業で落す、という方
策がとられている。Therefore, currently, gas turbines equipped with air-assisted fuel injection valves are disassembled during maintenance, and the I.
III. A method is being used to manually remove the filtrated carbon.
かかる状態では、エアアシスト形燃料噴射弁を備えたガ
スタービンを、非常用発電機の原動機に通用した場合は
、非常用発電機の着火信頼性を欠くこととなって致命的
な欠陥を有することになる。Under such conditions, if a gas turbine equipped with an air-assisted fuel injection valve is used as the prime mover of the emergency generator, the emergency generator will lack ignition reliability and have a fatal defect. become.
そこで本発明は、かかる問題を解消することに着目して
創作されたもので、殊に、エアアシスト形燃料噴射弁に
よる燃焼効率、燃焼状態を良好に維持しながら、かかる
問題を解消しようとするガスタービンの燃料噴射弁を提
供することにある。Therefore, the present invention was created with a focus on solving such problems, and in particular, attempts to solve these problems while maintaining good combustion efficiency and combustion conditions by the air-assisted fuel injection valve. An object of the present invention is to provide a fuel injection valve for a gas turbine.
以下、本発明の構成を添付図面に示す実施例により詳細
に説明する。DESCRIPTION OF THE PREFERRED EMBODIMENTS The structure of the present invention will be explained in detail below with reference to embodiments shown in the accompanying drawings.
第１図は本発明の第１の実施例を示す断面図で、本実施
例は産業用小型ガスタービン、特に、非常用発電機の原
動機に最適なもので、ライナーｌが横向きに構成されて
いるタイプである。２は燃境゛外筒でその端部にエアア
シスト形燃料噴射弁３が装着されている。FIG. 1 is a sectional view showing the first embodiment of the present invention. This embodiment is most suitable for a small industrial gas turbine, especially a prime mover for an emergency generator, and the liner l is configured horizontally. This is the type that exists. Reference numeral 2 denotes a combustion chamber outer cylinder, and an air-assisted fuel injection valve 3 is attached to the end thereof.
核燃１１噴射弁３は、スプレイヤチップ４を先端に螺着
した燃料送油管５と、該燃料送油管５に、環状エア通路
６を介して、嵌挿されたアシストエア送気管７とからな
り、該スプレイヤチップ４の軸心にＨＩＭの噴孔８が穿
設されており、該スプレイヤチップ４の先端は円錐部９
を形成し、その基部を前記燃料送油管５に螺着している
。該円錐部９の基部と前記アシストエア送気管７の先端
の絞り部１０とで、リング状のアシストエアスワラ−１
１を挟持している。該アシストエアスワラ−１１には前
記環状エア道路６と連通ずる多数の連通孔１２を穿設し
、該連通孔１２を、該アシストエアスワラ−１１の内面
と前記円錐部９とで形成されたエア噴孔１３に連通して
いる。なお、１４は燃ｍ器スワラ−で、前記アシストエ
ア送気管７と前記ライナー１とで挟持され、図示しない
コンブレフすによって形成された圧縮空気をライナーｌ
内へスワラ−状に拡散して導入するようにしている。The nuclear fuel 11 injection valve 3 consists of a fuel feed pipe 5 with a sprayer tip 4 screwed onto its tip, and an assist air feed pipe 7 fitted into the fuel feed pipe 5 via an annular air passage 6. A HIM nozzle hole 8 is bored in the axis of the sprayer tip 4, and the tip of the sprayer tip 4 has a conical portion 9.
The base portion thereof is screwed onto the fuel oil pipe 5. A ring-shaped assist air swirler 1 is formed by the base of the conical portion 9 and the constricted portion 10 at the tip of the assist air supply pipe 7.
1 is held in between. The assist air swirler 11 is provided with a large number of communication holes 12 communicating with the annular air road 6, and the communication holes 12 are formed by the inner surface of the assist air swirler 11 and the conical portion 9. It communicates with the air injection hole 13. A combustion swirler 14 is sandwiched between the assist air supply pipe 7 and the liner 1, and transfers compressed air formed by a combination leaf (not shown) to the liner l.
It is introduced by spreading it inward in a swirler shape.
１５はエア送気管用継手を示し、コンプレッサに接続さ
れるようにな、ている。Reference numeral 15 indicates a joint for an air supply pipe, which is connected to a compressor.
ここにおいて、本実施例では、前記スプレイヤチップ４
の約１０ｍ５径の先端面１６を、アシストエアスワラ−
１１のエア噴孔１３の先端開口部よリ０．５鰭程度突出
させている。かかる４Ｒ造にすると、アシストエアの一
部がその先端面１６に沿って流れようとするから、ｌｌ
ｌｔａ粒化されて、すでに炭化された燃料流がスプレイ
ヤチップ４の先端に迄回流することを阻止でき、該先端
面１６にカーボンの堆積が防止できる。勿論、かかる構
造に変更しても、（ムの構造は変更しないことから、エ
アアシスト形燃料噴射弁３による燃焼効率、燃焼状態に
は影響を与えない。Here, in this embodiment, the sprayer tip 4
An assist air swirler
About 0.5 fin protrudes from the tip opening of the air injection hole 13 of No. 11. With such a 4R structure, a part of the assist air tends to flow along the tip surface 16, so
It is possible to prevent the already carbonized fuel flow from flowing to the tip of the sprayer tip 4, and to prevent the accumulation of carbon on the tip surface 16. Of course, even if such a structure is changed, the combustion efficiency and combustion state of the air-assisted fuel injection valve 3 will not be affected because the structure of the air-assisted fuel injection valve 3 is not changed.
第２図は本発明の第２の実施例を示し、第１図と同一部
分は同一符号で示しているので、その説明を省略するが
、スプレイヤチップ４の円錐部９の先端角部にＲを形成
（Ｒ＝２ｍｓ）Ｌ、アシストエアをスプレイヤチップ４
の先端面１６に沿って流すようにして、第１の実施例と
同様、細微粒化されて炭化されやすい燃料の回流を阻止
している。FIG. 2 shows a second embodiment of the present invention, and the same parts as in FIG. (R=2ms) L, assist air to sprayer tip 4
As in the first embodiment, this prevents the fuel, which is atomized and easily carbonized, from circulating around.
以上要するに本発明は、特許請求の範囲に記載された構
成を採択したので、以下の効果を奏する。In summary, since the present invention adopts the configuration described in the claims, the following effects are achieved.
（１ン 微粒化による炭化が促進されやすいエアアシ
スト形燃料噴射弁のスプレイヤチップの先端面をアシス
トエアの一部が覆うよう構成したので、該スプレイヤチ
ップの先端面を微粒化、ないし炭化された燃料流を阻止
し、先端面にカーボンの付着を防止する。(1) Since the configuration is such that a part of the assist air covers the tip surface of the sprayer tip of the air-assisted fuel injection valve, where carbonization due to atomization is likely to be promoted, the tip surface of the sprayer tip is not atomized or carbonized. Blocks fuel flow and prevents carbon from adhering to the tip surface.
（２） アシストエアで先端面を覆うだけであるので
、安価な改良となり、燃料噴射弁に対しては燃焼効率や
燃焼状態について何ら悪影響を与えず、しかも、アシス
トエアや燃料の供給圧力を変更することもない。(2) Since the tip surface is simply covered with assist air, it is an inexpensive improvement, has no negative effect on the combustion efficiency or combustion condition of the fuel injector, and also changes the supply pressure of assist air and fuel. There's nothing to do.
第１図は本発明の第１の実施例の断面図、第２図は他の
実施例の断面図を示す。
１・・・ライナー、３・・・エアアシスト形燃料噴射弁
、４・・・スプレイヤチップ、８・・・噴孔、９・・・
円錐部、１１・・・アシストエアスワラ−５１３・・・
エア噴孔、１６・・・先端面。FIG. 1 shows a sectional view of a first embodiment of the invention, and FIG. 2 shows a sectional view of another embodiment. DESCRIPTION OF SYMBOLS 1... Liner, 3... Air assist type fuel injection valve, 4... Sprayer tip, 8... Nozzle hole, 9...
Conical part, 11...Assist air swirler-513...
Air nozzle hole, 16...tip surface.
Claims (3)
円錐状に形成されたスプレイヤチップと、該スプレイヤ
チップの円錐部に、該燃料用噴孔の囲りに環状のエア噴
孔を形成して嵌挿されたリング状のアシストエアスワラ
ーとからなり、該環状のエア噴孔から低圧のアシストエ
アを、ライナー内に吹込むことにより、液体燃料を微粒
化するための補助をするガスタービンのエアアシスト形
燃料噴射弁において、 該環状のエア噴孔から吹込むアシストエアの一部を、該
スプレイヤチップの先端面を覆うようにしたことを特徴
とするガスタービンのエアアシスト形燃料噴射弁。(1) Has a fuel injection hole opened in the liner, and
It consists of a sprayer tip formed in a conical shape, and a ring-shaped assist air swirler fitted into the conical part of the sprayer tip with an annular air nozzle formed around the fuel nozzle hole, In an air-assisted fuel injection valve for a gas turbine that assists in atomizing liquid fuel by blowing low-pressure assist air into the liner from the annular air injection hole, from the annular air injection hole. 1. An air-assisted fuel injection valve for a gas turbine, characterized in that a part of the assist air blown in covers the front end surface of the sprayer tip.
ラーのライナー側における端面より若干突出させた特許
請求の範囲第（１）項に記載のガスタービンのエアアシ
スト形燃料噴射弁。(2) The air-assisted fuel injection valve for a gas turbine according to claim (1), wherein the tip end surface of the sprayer tip slightly protrudes from the end surface on the liner side of the assist air swirler.
にＲを付設した特許請求の範囲第（１）項に記載のガス
タービンのエアアシスト形燃料噴射弁。(3) The air-assisted fuel injection valve for a gas turbine according to claim (1), wherein a radius is added to a tip corner on the liner side of the sprayer tip.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9096186A JPS62247134A (en) | 1986-04-19 | 1986-04-19 | Air-assistance-type fuel injection valve for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9096186A JPS62247134A (en) | 1986-04-19 | 1986-04-19 | Air-assistance-type fuel injection valve for gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS62247134A true JPS62247134A (en) | 1987-10-28 |
Family
ID=14013090
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP9096186A Pending JPS62247134A (en) | 1986-04-19 | 1986-04-19 | Air-assistance-type fuel injection valve for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS62247134A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6311473B1 (en) * | 1999-03-25 | 2001-11-06 | Parker-Hannifin Corporation | Stable pre-mixer for lean burn composition |
-
1986
- 1986-04-19 JP JP9096186A patent/JPS62247134A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6311473B1 (en) * | 1999-03-25 | 2001-11-06 | Parker-Hannifin Corporation | Stable pre-mixer for lean burn composition |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA1147974A (en) | Gas turbine engine fuel burners | |
| US6695234B2 (en) | Liquid fuel injection nozzles | |
| US4600151A (en) | Fuel injector assembly with water or auxiliary fuel capability | |
| JP3029196B2 (en) | Atomized dual fuel nozzle for gas turbine | |
| AU612038B2 (en) | Improvements relating to nozzles for in-cylinder fuel injection systems | |
| JPH04227410A (en) | Rear-section charging type fuel nozzle | |
| US5685492A (en) | Fuel injector nozzles | |
| CN109237515B (en) | Low-emission combustion chamber head with oil way automatic regulating valve structure | |
| JPH01130015A (en) | Fuel nozzle assembly for gas turbine engine | |
| US20230097301A1 (en) | Passive secondary air assist nozzles | |
| WO1995016881A1 (en) | Method and apparatus for atomizing liquid fuel | |
| JPS593643B2 (en) | Ekitainen Ryoutenka Souchi | |
| JPS62247134A (en) | Air-assistance-type fuel injection valve for gas turbine | |
| JPH08145363A (en) | Gas turbine combustor for liquid fuel | |
| CA1283551C (en) | Fuel nozzle assembly for a gas turbine engine | |
| KR200274405Y1 (en) | Nozzle structure for burner | |
| JP2929409B2 (en) | Supply structure of scavenging air in gas turbine combustor | |
| JP2768740B2 (en) | Fuel injection nozzle | |
| JPS63143423A (en) | Gas turbine combustor | |
| KR200321854Y1 (en) | Spray nozzle for semi - dry absorber or reactor | |
| RU1778351C (en) | Internal combustion engine injector nozzle | |
| JPS6249522B2 (en) | ||
| GB191401439A (en) | Improvements in or relating to Liquid Fuel Furnaces. | |
| JP2001141210A (en) | Oil burner | |
| JPS5838687B2 (en) | Low NOX liquid fuel injection valve |