JPS6139275U

JPS6139275U - combustor

Info

Publication number: JPS6139275U
Application number: JP12362884U
Authority: JP
Inventors: 昌彦森; 重実万代; 治也日浦; 一郎福江
Original assignee: 三菱重工業株式会社
Priority date: 1984-08-14
Filing date: 1984-08-14
Publication date: 1986-03-12

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

[Brief explanation of the drawing]

第１ａ図は、本考案に係る燃焼器の一実施例を示す概略
図、第１ｂ図は、第１ａ図の矢視一部平面図、第２ａ図
は、燃焼器の空気孔の位置を示す図、第２ｂ図は、空気
孔の位置と温度との関係を示す特性図、第３図は、一般
的なガスタービンの系統図、第４図は、ガスタービンに
使用される従来の燃焼器の概略図である。１・・・・・・負荷、２・・・・・・圧縮機、３・・・
・・・ガスタービ・ン、４・・・・・・軸、５・・・・
・・燃焼器、６・・・・・・空気取入口、７・・・・・
・燃焼ガス排出口：１０・・・・・・燃焼器本体、１
１・・・・・・内筒、１２・・・・・・尾筒、１３・・
・・・・燃焼ノズル、１４・・・・・・空気流入孔、１
５・・・・・・タービン部、１６・・・・・・ケーシン
グ、１７・・・・・・空気取入口、１２１・・・・・・
尾筒背側、１２２・・・・・・第１空気孔、１．２３・
・・・・・第２空気孔、１２４・・・・・・圧縮空気、
１２５・・・・・・コーナー部。Fig. 1a is a schematic diagram showing an embodiment of the combustor according to the present invention, Fig. 1b is a partial plan view taken in the direction of the arrow in Fig. 1a, and Fig. 2a shows the position of the air holes of the combustor. Figure 2b is a characteristic diagram showing the relationship between air hole position and temperature, Figure 3 is a system diagram of a typical gas turbine, and Figure 4 is a conventional combustor used in a gas turbine. FIG. 1...Load, 2...Compressor, 3...
...Gas turbine, 4...shaft, 5...
...Combustor, 6...Air intake, 7...
・Combustion gas exhaust port: 10... Combustor main body, 1
1... Inner tube, 12... Tail tube, 13...
... Combustion nozzle, 14 ... Air inflow hole, 1
5... Turbine part, 16... Casing, 17... Air intake, 121...
Tail tube dorsal side, 122... 1st air hole, 1.23.
...Second air hole, 124...Compressed air,
125... Corner section.

Claims

[Scope of utility model registration request]

A combustor with an integrated inner cylinder and tail cylinder inside the casing.
i are arranged around the turbine shaft, and fuel and compressed air are mixed and combusted in the inner cylinder. In the combustor, the combustion gas is supplied to the gas turbine through the transition piece. Cooling holes divided into two stages at optimal intervals are provided on the back side of the transition piece, so that the compressed air introduced into the casing is cooled. A combustor that suppresses a rise in transition pipe wall temperature by allowing an optimum amount to flow through the cooling hole.