JP3174645B2 - Gas turbine low NOx combustor - Google Patents
Gas turbine low NOx combustorInfo
- Publication number
- JP3174645B2 JP3174645B2 JP30444292A JP30444292A JP3174645B2 JP 3174645 B2 JP3174645 B2 JP 3174645B2 JP 30444292 A JP30444292 A JP 30444292A JP 30444292 A JP30444292 A JP 30444292A JP 3174645 B2 JP3174645 B2 JP 3174645B2
- Authority
- JP
- Japan
- Prior art keywords
- combustor
- gas turbine
- pilot
- combustion
- low nox
- 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]
【産業上の利用分野】本発明はガスタービンの低ＮＯx
燃焼器に関するものである。BACKGROUND OF THE INVENTION The present invention relates to a low NOx gas turbine.
It relates to a combustor.
【０００２】[0002]
【従来の技術】最近複合サイクル発電プラントの高効率
化のために、ガスタービンの入口温度は高温化されてお
り、この結果排出するＮＯx 量も増大する傾向にある。
このため排ガス中のＮＯx 低減に対する要求は大きく、
種々のＮＯx 低減策の検討がなされている。ＮＯx の生
成に影響を与える要因の一つに燃焼温度があり、この燃
焼温度が低いとＮＯx の発生が少ないことが知られてい
る。このため現在では、燃焼温度の上昇を抑制し、ＮＯ
x の生成をおさえるために拡散・予混合を組合せた２段
階燃焼を行なっている。この２段階燃焼器方式では、１
段目の燃焼で着火と保炎を有利にするために拡散燃焼を
行なわせ、２段目の燃焼でＮＯx の低減効果の大きい予
混合燃焼を行なわせている。図２は従来の燃焼器の１段
目の断面図を示し、燃焼器１の内筒２の燃焼領域に向け
て中心部にパイロットノズル３が設置されており、その
周囲に複数本のメインノズル４が設置されている。な
お、符号６はそれぞれのノズルの燃焼管である。2. Description of the Related Art In recent years, in order to increase the efficiency of a combined cycle power plant, the inlet temperature of a gas turbine has been increased, and as a result, the amount of NOx emitted tends to increase.
Therefore, the demand for NOx reduction in exhaust gas is great,
Various NOx reduction measures have been studied. One of the factors affecting the generation of NOx is the combustion temperature, and it is known that when the combustion temperature is low, the generation of NOx is small. For this reason, at present, an increase in combustion temperature is suppressed and NO
Two-stage combustion combining diffusion and premixing is performed to suppress the generation of x. In this two-stage combustor system, 1
Diffusion combustion is performed in order to favor ignition and flame holding in the first stage combustion, and premixed combustion having a large NOx reduction effect is performed in the second stage combustion. FIG. 2 is a cross-sectional view of a first stage of a conventional combustor, in which a pilot nozzle 3 is provided at a central portion toward a combustion region of an inner cylinder 2 of the combustor 1, and a plurality of main nozzles are provided therearound. 4 are installed. Reference numeral 6 denotes a combustion tube of each nozzle.
【０００３】[0003]
【発明が解決しようとする課題】ところで図２に示す従
来の燃焼器においては、低ＮＯx 燃焼のために燃焼領域
へのパイロット燃料量を極力減少させる方法を採用して
いる。しかしパイロット燃料量を減少させてＮＯx を低
減させる方法では、燃焼が不安定になって着火・保炎な
どに支障を生ずる。従ってＮＯx 低減のためのパイロッ
ト燃料量の減少策には自と限界があり、そのことがＮＯ
x 低減の限界となっていた。本発明はパイロット火炎の
メイン火炎への火移り特性を向上させることにより、前
記従来の問題を解消しようとするものである。The conventional combustor shown in FIG. 2 employs a method for reducing the amount of pilot fuel to the combustion region for low NOx combustion as much as possible. However, in the method of reducing NOx by reducing the pilot fuel amount, combustion becomes unstable, and ignition, flame holding and the like are hindered. Therefore, there is a limit in reducing the amount of pilot fuel for reducing NOx, which is
x The limit of reduction was reached. SUMMARY OF THE INVENTION The present invention is intended to solve the above-mentioned conventional problems by improving the characteristics of the pilot flame transferring to the main flame.
【０００４】[0004]
【課題を解決するための手段】このため本発明は、ガス
タービンの燃焼器中心部に配置したパイロットノズル
と、その周辺に配置した複数個のメインノズルからな
り、拡散および予混合を組み合わせた２段階燃焼を行な
う低ＮＯx燃焼器において、同パイロットノズルの出口
部近傍にラッパ形状のコーンを突出して取付けてなるも
ので、これを課題解決のための手段とするものである。Accordingly, the present invention comprises a pilot nozzle disposed at the center of a combustor of a gas turbine and a plurality of main nozzles disposed around the pilot nozzle.
And perform two-stage combustion combining diffusion and premixing.
In the low NOx combustor, a trumpet-shaped cone is protruded and mounted near the outlet of the pilot nozzle, and this is used as means for solving the problem.
【０００５】[0005]
【作用】燃焼器のパイロットノズルの出口部に、ラッパ
形状のコーンを突出して取付けたことにより、パイロッ
トノズルからの燃料の循環流の領域は拡大され、パイロ
ット火炎のメイン火炎への火移り特性が向上する。この
結果、パイロット噴射量が少ない状態のもとでも安定し
た燃焼が可能となり、パイロットによる発生ＮＯx が低
減される。[Function] By projecting a trumpet-shaped cone at the outlet of the pilot nozzle of the combustor, the area of the circulating flow of fuel from the pilot nozzle is expanded, and the characteristic of the transfer of the pilot flame to the main flame is improved. improves. As a result, stable combustion is possible even in a state where the pilot injection amount is small, and NOx generated by the pilot is reduced.
【０００６】[0006]
【実施例】以下本発明の実施例を図面について説明する
と、図１は燃焼器１段目の断面図である。図において、
燃焼器１の内筒２の燃焼領域に向けて中心部にパイロッ
トノズル３が設置されており、その周囲に複数本のメイ
ンノズル４が設置されている。BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a sectional view of a first stage of a combustor. In the figure,
A pilot nozzle 3 is installed at the center toward the combustion area of the inner cylinder 2 of the combustor 1, and a plurality of main nozzles 4 are installed around the pilot nozzle 3.
【０００７】またパイロットノズル３の出口部には、ラ
ッパ形状のコーン５が突出して取付けられており、パイ
ロットノズル４からの噴射燃料の循環流領域を拡大する
ようになっている。このためパイロット燃料量の少ない
状態でも安定した燃焼が可能となり、パイロットによる
発生ＮＯx が低減される。なお、符号６はメインノズル
４の燃料管である。At the outlet of the pilot nozzle 3, a trumpet-shaped cone 5 is mounted so as to protrude therefrom, so as to enlarge the circulating flow region of the fuel injected from the pilot nozzle 4. Therefore, stable combustion is possible even in a state where the pilot fuel amount is small, and NOx generated by the pilot is reduced. Reference numeral 6 denotes a fuel pipe of the main nozzle 4.
【０００８】[0008]
【発明の効果】以上詳細に説明した如く、本発明の燃焼
器によれば、パイロットノズルからの燃料の循環流の領
域が拡大されることにより、パイロット火炎のメイン火
炎への火移り特性が向上し、燃焼・保炎が安定化してパ
イロットによる発生ＮＯx が低減される。従って環境規
制に寄与する効果は極めて大きい。As described above in detail, according to the combustor of the present invention, the area of the circulating flow of the fuel from the pilot nozzle is expanded, so that the characteristics of the transfer of the pilot flame to the main flame are improved. However, combustion and flame holding are stabilized, and NOx generated by the pilot is reduced. Therefore, the effect of contributing to environmental regulations is extremely large.
【図１】本発明の第１実施例に係る燃焼器の側断面図で
ある。FIG. 1 is a side sectional view of a combustor according to a first embodiment of the present invention.
【図２】従来の燃焼器の側断面図である。FIG. 2 is a side sectional view of a conventional combustor.
１ 燃焼器 ３ パイロットノズル ４ メインノズル ５ コーン 1 Combustor 3 Pilot nozzle 4 Main nozzle 5 Cone
───────────────────────────────────────────────────── フロントページの続き (72)発明者 佐藤 亘男 兵庫県高砂市荒井町新浜二丁目１番１号 三菱重工業株式会社 高砂研究所内 (72)発明者 西田 啓之 兵庫県高砂市荒井町新浜二丁目１番１号 三菱重工業株式会社 高砂研究所内 (72)発明者 田中 克則 兵庫県高砂市荒井町新浜二丁目１番１号 三菱重工業株式会社 高砂製作所内 審査官 田澤 英昭 (56)参考文献 特開 昭59−101551（ＪＰ，Ａ) 特開 平１−137117（ＪＰ，Ａ) 特開 平４−227414（ＪＰ，Ａ) 米国特許3349826（ＵＳ，Ａ) (58)調査した分野(Int.Cl.7，ＤＢ名) F23R 3/28 F23R 3/16 F23R 3/30 F23R 3/34 ──────────────────────────────────────────────────続 き Continuing from the front page (72) Inventor, Tatsuo Sato 2-1-1, Shinhama, Arai-machi, Takasago City, Hyogo Prefecture Inside the Mitsubishi Heavy Industries, Ltd. Takasago Research Laboratory (72) Inventor Hiroyuki Nishida 2-1-1, Shin-ama, Arai-machi, Takasago City, Hyogo Prefecture No. 1 Inside the Takasago Research Laboratory, Mitsubishi Heavy Industries, Ltd. (JP, A) JP-A-1-137117 (JP, A) JP-A-4-227414 (JP, A) US Patent 3,498,826 (US, A) (58) Fields investigated (Int. Cl. 7 , DB name ) F23R 3/28 F23R 3/16 F23R 3/30 F23R 3/34
Claims (1)
パイロットノズルと、その周辺に配置した複数個のメイ
ンノズルからなり、拡散および予混合を組み合わせた２
段階燃焼を行なう低ＮＯx 燃焼器において、同パイロッ
トノズルの出口部近傍にラッパ形状のコーンを突出して
取付けたことを特徴とするガスタービンの低ＮＯx 燃焼
器。1. A pilot nozzle disposed in the combustor center of the gas turbine, Ri Do a plurality of main nozzles arranged around the, combined diffusion and premix 2
A low NOx combustor for a gas turbine, wherein a trumpet-shaped cone is protruded and mounted near an outlet of the pilot nozzle in a low NOx combustor performing stepwise combustion .
Priority Applications (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP30444292A JP3174645B2 (en) | 1992-10-19 | 1992-10-19 | Gas turbine low NOx combustor |
| US08/137,343 US5410884A (en) | 1992-10-19 | 1993-10-18 | Combustor for gas turbines with diverging pilot nozzle cone |
| EP93116880A EP0594127B1 (en) | 1992-10-19 | 1993-10-19 | Combustor for gas turbines |
| DE69312208T DE69312208T2 (en) | 1992-10-19 | 1993-10-19 | Gas turbine combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP30444292A JP3174645B2 (en) | 1992-10-19 | 1992-10-19 | Gas turbine low NOx combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH06129640A JPH06129640A (en) | 1994-05-13 |
| JP3174645B2 true JP3174645B2 (en) | 2001-06-11 |
Family
ID=17933062
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP30444292A Expired - Lifetime JP3174645B2 (en) | 1992-10-19 | 1992-10-19 | Gas turbine low NOx combustor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3174645B2 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001254946A (en) | 2000-03-14 | 2001-09-21 | Mitsubishi Heavy Ind Ltd | Gas turbine combustor |
| JP2005221135A (en) * | 2004-02-05 | 2005-08-18 | Ishin Giken:Kk | Burning furnace |
| JP6318443B2 (en) | 2013-01-22 | 2018-05-09 | 三菱日立パワーシステムズ株式会社 | Combustor and rotating machine |
-
1992
- 1992-10-19 JP JP30444292A patent/JP3174645B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPH06129640A (en) | 1994-05-13 |
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