JPS59113662U - Combustor for gas turbine - Google Patents
Combustor for gas turbineInfo
- Publication number
- JPS59113662U JPS59113662U JP273583U JP273583U JPS59113662U JP S59113662 U JPS59113662 U JP S59113662U JP 273583 U JP273583 U JP 273583U JP 273583 U JP273583 U JP 273583U JP S59113662 U JPS59113662 U JP S59113662U
- Authority
- JP
- Japan
- Prior art keywords
- gas turbine
- combustor
- fuel nozzle
- vessel wall
- introduction part
- 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
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
第１図は従来のガスタービン用燃焼器の断面図、第２図
は燃焼器の一次燃焼領域の空気過剰率とＮＯｘおよびＣ
Ｏ生成率との関係を示す特性曲線図、及び第３図は本考
案によるガスタービン用燃焼器の断面図である。
１０１・・・燃料ノズル、１０２・・・−次空気導入部
、１０３・・・二次空気孔、１０４・・・壁面冷却空気
導入部、１０５・・・希釈空気孔、１１０・・・器壁、
３０１・・・燃料ノズル、３０２・・・−次空気導入部
、３０３・・・二次空気孔、３０４・・・壁面冷却空気
導入部、３０５・・・絞り部、３０６・・・触媒層、３
１０・・・器壁。Figure 1 is a cross-sectional view of a conventional gas turbine combustor, and Figure 2 shows the excess air ratio in the primary combustion region of the combustor and NOx and C.
A characteristic curve diagram showing the relationship with the O production rate and FIG. 3 are a cross-sectional view of a gas turbine combustor according to the present invention. 101...Fuel nozzle, 102...Secondary air introduction part, 103...Secondary air hole, 104...Wall surface cooling air introduction part, 105...Dilution air hole, 110...Instrument wall ,
301...Fuel nozzle, 302...Secondary air introduction part, 303...Secondary air hole, 304...Wall surface cooling air introduction part, 305...Aperture part, 306...Catalyst layer, 3
10... vessel wall.
Claims (1)
と、器壁に設けられた二次空気孔とを有するガスタービ
ン用燃焼器において、器壁の尾部に未燃成分を燃焼させ
る触媒層を設けたことを特徴とするガスタービン用燃焼
器。In a gas turbine combustor that has a fuel nozzle, a primary air introduction part surrounding the fuel nozzle, and a secondary air hole provided in the vessel wall, a catalyst layer for burning unburned components is provided in the tail part of the vessel wall. A combustor for a gas turbine, characterized in that:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP273583U JPS59113662U (en) | 1983-01-14 | 1983-01-14 | Combustor for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP273583U JPS59113662U (en) | 1983-01-14 | 1983-01-14 | Combustor for gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS59113662U true JPS59113662U (en) | 1984-08-01 |
Family
ID=30134388
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP273583U Pending JPS59113662U (en) | 1983-01-14 | 1983-01-14 | Combustor for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS59113662U (en) |
-
1983
- 1983-01-14 JP JP273583U patent/JPS59113662U/en active Pending
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