JPH0228964U

JPH0228964U -

Info

Publication number: JPH0228964U
Application number: JP10348688U
Authority: JP
Priority date: 1988-08-04
Filing date: 1988-08-04
Publication date: 1990-02-23
Anticipated expiration: 2003-08-04
Also published as: JP2516822Y2

Description

[Brief explanation of drawings]

第１図は本考案のガスタービン用燃焼器の一実
施例を示す縦断面説明図、第２図は第１図におけ
る予混合部および燃焼領域の詳細および流体の流
れを示す拡大説明図、第３図は本考案の燃焼器に
おける、空気・燃料比と燃焼ガス中のＣＯ，ＮＯ
ｘ、全圧損失係数との関係を示す線図、第４図は
本考案の燃焼器および従来の燃焼器における、空
気・燃料比と燃焼ガス中のＣＯ，ＮＯｘ、可変機
構開度との関係を示す線図、第５図は従来の燃焼
器の一例を示す説明図である。１…旋回羽根、２…予混合部、３…燃焼領域、
４…一次燃料噴射ノズル、５…ノズルステータ、
６…外筒、７…内筒、８…加圧空気通路、１０…
空気取入口、１１…主燃料噴射ノズル、１２…仕
切板、１３…空気通路、１４…シールエア取入管
、１５…シールエア取入口、１６…ライナヘツド
、１７…空気室、１８…小孔、２０…希釈領域、
２１…開口、２２…可変機構、２３…可変ポート
、２４…希釈孔、２５…点火プラグ。 FIG. 1 is an explanatory longitudinal cross-sectional view showing one embodiment of a gas turbine combustor of the present invention, FIG. 2 is an enlarged explanatory view showing details of the premixing section and combustion region in FIG. Figure 3 shows the air/fuel ratio and CO and NO in the combustion gas in the combustor of the present invention.
x, a diagram showing the relationship with the total pressure loss coefficient, and Figure 4 shows the relationship between the air/fuel ratio, CO and NOx in the combustion gas, and the opening degree of the variable mechanism in the combustor of the present invention and the conventional combustor. FIG. 5 is an explanatory diagram showing an example of a conventional combustor. 1... Swirling vane, 2... Premixing section, 3... Combustion region,
4...Primary fuel injection nozzle, 5...Nozzle stator,
6... Outer cylinder, 7... Inner cylinder, 8... Pressurized air passage, 10...
Air intake, 11... Main fuel injection nozzle, 12... Partition plate, 13... Air passage, 14... Seal air intake pipe, 15... Seal air intake, 16... Liner head, 17... Air chamber, 18... Small hole, 20... Dilution region,
21... Opening, 22... Variable mechanism, 23... Variable port, 24... Dilution hole, 25... Spark plug.

Claims

[Claims for Utility Model Registration] 1. An inner cylinder 7 is provided within the outer cylinder 6 to form a pressurized air passage 8 between the outer cylinder and the inner cylinder, and a primary fuel injection nozzle is provided at the center of the end of the inner cylinder. 4, an air intake 10 is provided around the end of the inner cylinder to take in pressurized air, and a large number of swirling vanes 1 are mounted inside this air intake, and a main In a gas turbine combustor in which a fuel injection nozzle 11 is inserted and a premixing section 2 that communicates with an air intake port 10 is formed around the outside of the primary fuel injection nozzle 4, a partition plate 12 is provided in the premixing section 2. A combustor for a gas turbine, characterized in that a premixing section is divided, and an air passage 13 for flowing seal air between a nozzle stator 5 outside a primary fuel injection nozzle 4 and the premixing section 2 is formed. 2. The combustor for a gas turbine according to claim 1, wherein the flat air chamber 17 is formed so as to cover the surface of the liner head 16 adjacent to the downstream side of the primary fuel injection nozzle 4. 3. The pressurized air passage 8 in the dilution region 20 on the downstream side of the combustion region 3 is provided with an opening 21 that allows air to flow into the inner cylinder 7, and the amount of air flowing into the inner cylinder is adjusted by opening and closing this opening. The gas turbine combustor according to claim 1 or 2, further comprising a variable mechanism (22) provided in the pressurized air passage.