JP3316429B2 - Oil and gas fired gas turbine combustor - Google Patents
Oil and gas fired gas turbine combustorInfo
- Publication number
- JP3316429B2 JP3316429B2 JP25847797A JP25847797A JP3316429B2 JP 3316429 B2 JP3316429 B2 JP 3316429B2 JP 25847797 A JP25847797 A JP 25847797A JP 25847797 A JP25847797 A JP 25847797A JP 3316429 B2 JP3316429 B2 JP 3316429B2
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- gas
- oil
- combustor
- nozzle
- 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
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、油燃料とガス燃料
とを燃焼させる油・ガス焚きガスタービン用燃焼器に関
する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a combustor for an oil / gas fired gas turbine which burns oil fuel and gas fuel.
【０００２】[0002]
【従来の技術】従来の油・ガス焚き低ＮＯｘ燃焼器の例
を図２に示してある。図２において、０１は燃焼器、０
２はパイロット燃料ノズル、０３はマルチメインノズル
を示している。０４はケーシングであり、ケーシング０
４にはケーシング水噴射ノズル０５が設けられている。2. Description of the Related Art An example of a conventional oil / gas fired low NOx combustor is shown in FIG. In FIG. 2, 01 is a combustor, 0
2 denotes a pilot fuel nozzle, and 03 denotes a multi-main nozzle. Reference numeral 04 denotes a casing.
4 is provided with a casing water injection nozzle 05.
【０００３】パイロット燃料ノズル０２は火炎を確保す
るためのもので、燃焼器０１の中央部に設けられてい
る。また、マルチメインノズル０３は予混合ノズルであ
り、パイロット燃料ノズル０２の外周に配置されてい
て、これらのノズル０２，０３をケーシング０４が組み
込んでいる。[0003] The pilot fuel nozzle 02 is for securing a flame, and is provided at the center of the combustor 01. The multi-main nozzle 03 is a premix nozzle, which is arranged on the outer periphery of the pilot fuel nozzle 02, and these nozzles 02 and 03 are incorporated in the casing 04.
【０００４】この燃焼器は、油燃料０７とガス燃料０６
を燃焼させる、いわゆるデュアル焚きガスタービン燃焼
器であり、油燃料０７とガス燃料０６のための２系統の
燃料通路を燃焼器の内部に形成させる必要があり、しか
も油燃料０７の供給通路及びガス燃料０６の供給通路の
各通路を完全に分離してシールする必要がある。This combustor comprises an oil fuel 07 and a gas fuel 06
Is a so-called dual-fired gas turbine combustor, in which two fuel passages for the oil fuel 07 and the gas fuel 06 need to be formed inside the combustor, and the supply passage for the oil fuel 07 and the gas It is necessary to completely separate and seal each passage of the supply passage of the fuel 06.
【０００５】その上、油燃料０７を燃やすマルチメイン
ノズル０３には、低ＮＯｘ化のために水等を噴射して火
炎温度を低下させる必要があることから図示したケーシ
ング水噴射ノズル０５のような水供給ノズルを設ける必
要があった。一方パイロット燃料ノズル０２へは、内設
されている図示しない水噴射ノズルへ、それぞれ配管を
介して水１０が供給されていた。In addition, the multi-main nozzle 03 that burns the oil fuel 07 needs to inject water or the like to lower the flame temperature in order to reduce NOx. It was necessary to provide a water supply nozzle. On the other hand, water 10 was supplied to the pilot fuel nozzle 02 via a pipe to a water injection nozzle (not shown) provided therein.
【０００６】従来の油・ガス焚きガスタービン用燃焼器
は、前記した理由によって燃焼器は極めて複雑な構造と
なっていて製作が困難であった。[0006] The conventional combustor for an oil / gas fired gas turbine has an extremely complicated structure due to the above-mentioned reasons and is difficult to manufacture.
【０００７】[0007]
【発明が解決しようとする課題】本発明は、燃焼器の中
央部にパイロット燃料ノズルを有し、同パイロット燃料
ノズルの外周に複数の予混合ノズルを配置した油燃料と
ガス燃料を燃焼させる従来の油・ガス焚きガスタービン
用燃焼器における前記した問題点に鑑み、燃料の供給系
統の構造を簡素化し、製作容易な油・ガス焚きガスター
ビン用燃焼器を提供することを課題としている。SUMMARY OF THE INVENTION The present invention relates to a combustor,
It has a pilot fuel nozzle in the center,
In view of the above-mentioned problems in the conventional oil / gas-fired gas turbine combustor for burning oil fuel and gas fuel in which a plurality of premix nozzles are arranged on the outer periphery of the nozzle, the structure of the fuel supply system is simplified and manufactured. It is an object to provide an easy oil / gas fired gas turbine combustor.
【０００８】[0008]
【課題を解決するための手段】前記課題を解決するた
め、本発明は、パイロット燃料ノズル及び前記予混合ノ
ズルにガス燃料を導くガス燃料供給ラインおよび、油燃
料に対しては水蒸気を添加し同油燃料をガス化させる混
合器を具え、同混合器でガス化後の前記油燃料を弁を介
して前記ガス燃料供給ラインに送り込むように構成し
た、油・ガス焚きガスタービン用燃焼器を提供する。SUMMARY OF THE INVENTION In order to solve the above problems, the present invention provides a gas fuel supply line for guiding gas fuel to a pilot fuel nozzle and the premix nozzle, and an oil fuel supply line. A mixture that adds steam and gasifies the oil fuel.
An oil / gas-fired gas turbine combustor comprising a mixer and configured to feed the oil fuel after gasification by the mixer to the gas fuel supply line via a valve. .
【０００９】本発明による燃焼器では、油燃料を燃焼さ
せるときは、混合器によって油燃料中に水蒸気を添加し
て水蒸気の温度により油燃料を蒸発させてガス化するの
で、燃料の容積流量が増加し燃焼器のガス燃料供給ライ
ンを使って油燃料を燃焼することができる。In the combustor according to the present invention, when the oil fuel is burned, steam is added to the oil fuel by the mixer, and the oil fuel is evaporated and gasified by the temperature of the steam. Oil fuel can be burned using the increased combustor gas fuel supply line.
【００１０】このように、本発明による油・ガス焚きガ
スタービン用燃焼器ではガス燃料供給ラインを形成させ
るだけでガス燃料はもとより、油燃料の燃焼及びガス燃
料と油燃料の混焼も可能となる。本発明による油・ガス
焚きガスタービン燃焼器ではガス燃料供給ラインを設け
るだけでよいので、その構造が簡単となり、製作も容易
となる。As described above, in the combustor for an oil / gas fired gas turbine according to the present invention, not only gas fuel but also combustion of oil fuel and co-firing of gas fuel and oil fuel can be achieved only by forming a gas fuel supply line. . In the oil / gas fired gas turbine combustor according to the present invention, only the gas fuel supply line needs to be provided, so that the structure is simplified and the manufacture is facilitated.
【００１１】[0011]
【発明の実施の形態】以下、本発明による油・ガス焚き
ガスタービン用燃焼器について図１に示した実施の形態
に基づいて具体的に説明する。なお、以下の実施の形態
において、図２に示した従来の燃焼器と同じ構成の部分
には説明を簡単にするため同じ符号を付してある。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, a combustor for an oil / gas fired gas turbine according to the present invention will be specifically described based on the embodiment shown in FIG. In the following embodiments, the same components as those of the conventional combustor shown in FIG. 2 are denoted by the same reference numerals for simplification of description.
【００１２】図１において、０９は混合器を示し、この
混合器０９では油燃料０７に対し水蒸気０８が供給され
る。燃焼器の基本構成は従来とおなじであるが、燃料ノ
ズルは従来のガス燃料供給ラインのみとし、油燃料ライ
ンはない。In FIG. 1, reference numeral 09 denotes a mixer. In the mixer 09, steam 08 is supplied to the oil fuel 07. Although the basic configuration of the combustor is the same as the conventional one, the fuel nozzle has only a conventional gas fuel supply line and no oil fuel line.
【００１３】また、油燃料０７の供給系には、前記した
ように混合器０９を有する水蒸気添加系統を設け、油燃
料０７中に水蒸気０８を添加することにより油燃料０７
をガス化し、ガス燃料０６のためのガス燃料供給ライン
から供給して燃焼させるようにしている。The oil fuel 07 supply system is provided with a steam addition system having the mixer 09 as described above, and by adding steam 08 to the oil fuel 07, the oil fuel 07 is supplied.
Is gasified, supplied from a gas fuel supply line for gas fuel 06, and burned.
【００１４】このように、図１の油・ガス焚きガスター
ビン用燃焼器においては、油燃料０７使用時には、混合
器０９において油燃料０７中に水蒸気０８を添加するこ
とにより油燃料０７を蒸発させ、油燃料０７のガス化を
行うとともに容積を増加させることにより、ガス燃料供
給ラインを使用することが可能となる。一方、ガス燃料
０６を燃焼させる時には、従来同様のガス燃料供給ライ
ンを使用することになる。従って、油・ガス各燃料のデ
ュアル焚きであっても燃料ラインはガス燃料供給ライン
一系統でよいこととなる。As described above, in the combustor for an oil / gas fired gas turbine shown in FIG. 1, when the oil fuel 07 is used, the oil fuel 07 is evaporated by adding the water vapor 08 to the oil fuel 07 in the mixer 09. By gasifying the oil fuel 07 and increasing the volume, the gas fuel supply line can be used. On the other hand, when burning the gas fuel 06, a gas fuel supply line similar to the conventional one is used. Therefore, the fuel line may be a single gas fuel supply line even in the case of dual firing of oil and gas fuels.
【００１５】[0015]
【発明の効果】以上説明したように、本発明による油・
ガス焚きガスタービン用燃焼器は、パイロット燃料ノズ
ル及び前記予混合ノズルにガス燃料を導くガス燃料供給
ラインおよび、油燃料に対しては水蒸気を添加し同油燃
料をガス化させる混合器を具え、同混合器でガス化後の
前記油燃料を弁を介して前記ガス燃料供給ラインに送り
込むように構成したものである。As described above, the oil according to the present invention
The gas-fired gas turbine combustor is a pilot fuel nozzle.
Le and the premixing nozzles to the gas fuel supply line leads to a gas fuel and for the oil fuel comprises a mixer for gasifying Doabura fuel and steam was added, after gasification in the mixer
The oil fuel and through the valve is obtained by adapted fed to the gas fuel supply line.
【００１６】本発明による燃焼器においては、油燃料を
燃焼させるときは、混合器によって油燃料中に水蒸気を
添加して水蒸気の温度により油燃料を蒸発させてガス化
するので、燃焼器のガス燃料供給ラインを使うことがで
きる。In the combustor according to the present invention, when the oil fuel is burned, steam is added to the oil fuel by the mixer and the oil fuel is evaporated and gasified by the temperature of the steam. A fuel supply line can be used.
【００１７】このように、本発明による油・ガス焚きガ
スタービン用燃焼器ではガス燃料供給ラインを形成させ
るだけでガス燃料はもとより、油燃料の燃焼及びガス燃
料と油燃料の混焼も可能となる。従って、本発明による
油・ガス焚きガスタービン燃焼器にはガス燃料供給ライ
ンを設けるだけでよく、その構造が簡単となり、製作が
容易となる。As described above, in the combustor for an oil / gas fired gas turbine according to the present invention, not only gas fuel but also combustion of oil fuel and co-firing of gas fuel and oil fuel can be achieved only by forming a gas fuel supply line. . Therefore, the oil / gas-fired gas turbine combustor according to the present invention only needs to be provided with a gas fuel supply line, and its structure is simplified and its manufacture is facilitated.
【図１】本発明の実施の一形態による油・ガス焚きガス
タービン用燃焼器の構成を示す説明図。FIG. 1 is an explanatory diagram showing a configuration of a combustor for an oil / gas fired gas turbine according to an embodiment of the present invention.
【図２】従来の油・ガス焚きガスタービン用燃焼器の構
成を示す説明図。FIG. 2 is an explanatory diagram showing a configuration of a conventional combustor for an oil / gas fired gas turbine.
０１ 燃焼器 ０２ パイロット燃料ノズル ０３ マルチメインノズル ０４ ケーシング ０５ ケーシング水噴射ノズル ０６ ガス燃料 ０７ 油燃料 ０８ 水蒸気 ０９ 混合器 01 Combustor 02 Pilot fuel nozzle 03 Multi main nozzle 04 Casing 05 Casing water injection nozzle 06 Gas fuel 07 Oil fuel 08 Steam 09 Mixer
───────────────────────────────────────────────────── フロントページの続き (72)発明者 春田 秀樹 兵庫県高砂市荒井町新浜２丁目１番１号 三菱重工業株式会社高砂製作所内 (56)参考文献 特開 平５−332166（ＪＰ，Ａ) 実開 昭55−114818（ＪＰ，Ｕ) (58)調査した分野(Int.Cl.7，ＤＢ名) F23R 3/36 F02C 7/22 F23R 3/28 F02C 9/40 ──────────────────────────────────────────────────続 き Continuation of front page (72) Inventor Hideki Haruta 2-1-1 Shinhama, Arai-machi, Takasago City, Hyogo Prefecture Inside the Takasago Works, Mitsubishi Heavy Industries, Ltd. (56) References 55-114818 (JP, U) (58) Fields investigated (Int. Cl. 7 , DB name) F23R 3/36 F02C 7/22 F23R 3/28 F02C 9/40
Claims (1)
を有し、同パイロット燃料ノズルの外周に複数の予混合
ノズルを配置した油燃料とガス燃料を燃焼させる油・ガ
ス焚きガスタービン用燃焼器において、前記パイロット
燃料ノズル及び前記予混合ノズルにガス燃料を導くガス
燃料供給ラインおよび、油燃料に対して水蒸気を添加し
同油燃料をガス化させる混合器を具え、同混合器でガス
化後の前記油燃料を弁を介して前記ガス燃料供給ライン
に送り込むように構成したことを特徴とする油・ガス焚
きガスタービン用燃焼器。1. A pilot fuel nozzle is provided at the center of a combustor.
With multiple premixes around the pilot fuel nozzle
In an oil / gas fired gas turbine combustor for burning oil fuel and gas fuel in which nozzles are arranged , the pilot
Gas fuel supply line leads to the fuel nozzle and the gas fuel into the premixing nozzles and the added Doabura fuel vapor comprising a mixer for gasifying the oil fuel, gas in the mixer
Combustor oil and gas fired gas turbine which is characterized by being configured to pump the gas fuel supply line the oil fuel and through the valve after reduction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP25847797A JP3316429B2 (en) | 1997-09-24 | 1997-09-24 | Oil and gas fired gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP25847797A JP3316429B2 (en) | 1997-09-24 | 1997-09-24 | Oil and gas fired gas turbine combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH1194255A JPH1194255A (en) | 1999-04-09 |
| JP3316429B2 true JP3316429B2 (en) | 2002-08-19 |
Family
ID=17320769
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP25847797A Expired - Lifetime JP3316429B2 (en) | 1997-09-24 | 1997-09-24 | Oil and gas fired gas turbine combustor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3316429B2 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7143583B2 (en) | 2002-08-22 | 2006-12-05 | Hitachi, Ltd. | Gas turbine combustor, combustion method of the gas turbine combustor, and method of remodeling a gas turbine combustor |
| CN106194437B (en) * | 2016-08-26 | 2017-12-12 | 天津成立航空技术有限公司 | A kind of Aero-Space engine fuel injection system component and its fuel injection method |
-
1997
- 1997-09-24 JP JP25847797A patent/JP3316429B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPH1194255A (en) | 1999-04-09 |
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