JPS6180304U

JPS6180304U -

Info

Publication number: JPS6180304U
Application number: JP11958685U
Authority: JP
Priority date: 1985-08-02
Filing date: 1985-08-02
Publication date: 1986-05-28

Description

[Brief explanation of the drawing]

添付図面は本考案の一実施例を示し、第１図は
ガスタービンノズルを備えるラジアル型ガスター
ビンノズルの中心部縦断側面図、第２図はガスタ
ービンノズルの一部切欠正面図、第３図は分割ノ
ズル１５と分割リング１８′の斜視図、第４図は
スクロールへの取付けを第２図Ａ−Ａ線で切断し
て示した拡大側面図、第５図はケーシング１への
直接取付けを示した拡大切断側面図である。１→ハウジング、２→タービン軸、３→ロータ
、４→タービン羽根、５→ロータ、６→エヤー圧
縮羽根、７→スクロール、８→ガス排出口体、９
→ガス噴出通路、１０→ガスタービンノズル、１
１→単翼、１２→フランジ、１２′，１２″→フ
ランジ、１５→分割ノズル、１７′，１７″→位
置決め突起、１８→連結リング、１８′→分割リ
ング、１９′，１９″→位置決め透孔。 The accompanying drawings show an embodiment of the present invention, in which Fig. 1 is a vertical cross-sectional side view of the center of a radial type gas turbine nozzle equipped with a gas turbine nozzle, Fig. 2 is a partially cutaway front view of the gas turbine nozzle, and Fig. 3 is a partially cutaway front view of the gas turbine nozzle. is a perspective view of the split nozzle 15 and the split ring 18', FIG. 4 is an enlarged side view taken along line A-A in FIG. FIG. 1 → Housing, 2 → Turbine shaft, 3 → Rotor, 4 → Turbine blade, 5 → Rotor, 6 → Air compression vane, 7 → Scroll, 8 → Gas exhaust port body, 9
→ Gas ejection passage, 10 → Gas turbine nozzle, 1
1 → Single blade, 12 → Flange, 12′, 12″ → Flange, 15 → Split nozzle, 17′, 17″ → Positioning protrusion, 18 → Connecting ring, 18′ → Split ring, 19′, 19″ → Positioning hole Hole.

Claims

[Scope of utility model registration request]

In a gas turbine nozzle, in which a large number of gas induction single blades are provided at regular intervals in a circular direction within a gas flow jetting slit arranged in a ring corresponding to the turbine blades of a rotor, the nozzle is formed on both sides of the slit. It is formed by a pair of annular flanges and a large number of single blades as described above between the flanges, and the nozzle is constructed by a combination of a large number of split nozzles obtained by cutting the annular flange roughly in the radial direction between the single blades. The split flange and single blade of each split nozzle are integrally formed of ceramic, and the ceramic split ring, which is combined into an annular body by connecting the split ends, is connected to the two of the split flanges of the split nozzle. The connecting edges of the respective split ends are staggered on both sides of the same split flange so that they do not overlap, and the positioning between the split nozzles is controlled by this arrangement. A gas turbine nozzle made with