JPH01159139U

JPH01159139U -

Info

Publication number: JPH01159139U
Application number: JP5464088U
Authority: JP
Priority date: 1988-04-25
Filing date: 1988-04-25
Publication date: 1989-11-02

Description

[Brief explanation of drawings]

第１図は本考案の尾筒冷却構造の一実施例の縦
断面図、第２図は従来の尾筒冷却構造のガスター
ビン燃焼器の縦断面図、第３図は尾筒内部の流路
断面積変化を示す図、第４図は尾筒の内側熱伝達
率分布図、第５図は本考案と従来の尾筒冷却構造
のインピンジメントカバーの内外の圧力分布図、
第６図は本考案の尾筒冷却構造のガスタービン燃
焼器の縦断面図、第７図と第９図は本考案の変形
例の尾筒出口部の縦断面図、第８図は第１図の
―矢視断面図である。１……ライナ、２……尾筒、３……燃料ノズル
、４……外筒、５……ケーシング、６……インピ
ンジメントカバー、７……フロースリーブ、８…
…小孔、９……流路、１１……リブ、１２……通
路、１３……尾筒外壁、１４……尾筒内壁、１５
……隙間、２１……空気、２２……燃焼ガス、１
０１……タービンノズル、１０２……デイフユー
ザ。 Figure 1 is a vertical cross-sectional view of an embodiment of the transition piece cooling structure of the present invention, Figure 2 is a vertical cross-sectional view of a gas turbine combustor with a conventional transition piece cooling structure, and Figure 3 is a flow path inside the transition piece. Figure 4 is a diagram showing the change in cross-sectional area, Figure 4 is a diagram showing the internal heat transfer coefficient distribution of the transition piece, Figure 5 is a diagram showing the pressure distribution inside and outside the impingement cover of the present invention and the conventional transition piece cooling structure.
FIG. 6 is a longitudinal sectional view of a gas turbine combustor with a transition pipe cooling structure according to the present invention, FIGS. FIG. DESCRIPTION OF SYMBOLS 1... Liner, 2... Transition piece, 3... Fuel nozzle, 4... Outer cylinder, 5... Casing, 6... Impingement cover, 7... Flow sleeve, 8...
... Small hole, 9 ... Channel, 11 ... Rib, 12 ... Passage, 13 ... Transition tube outer wall, 14 ... Transition tube inner wall, 15
...Gap, 21...Air, 22...Combustion gas, 1
01...Turbine nozzle, 102...Diff user.

Claims

[Scope of utility model registration request]

a combustor liner, a transition piece connecting the combustor liner and the turbine section, a turbine casing surrounding the combustor liner and the transition piece and communicating with a compressed air source; a fuel supply means, an impingement cover provided near the combustor liner side of the transition piece and surrounding the transition piece at a certain distance from an outer peripheral wall of the transition piece, and an impingement provided on the impingement cover. A group of small holes for cooling and a gap between the impingement cover and the transition piece in a wall of the transition piece near the turbine section that is not surrounded by the impingement cover communicate with the outside of the transition piece. A gas turbine combustor characterized in that a gas turbine combustor is provided with a passage.