JPS6432434U - - Google Patents
Info
- Publication number
- JPS6432434U JPS6432434U JP12613087U JP12613087U JPS6432434U JP S6432434 U JPS6432434 U JP S6432434U JP 12613087 U JP12613087 U JP 12613087U JP 12613087 U JP12613087 U JP 12613087U JP S6432434 U JPS6432434 U JP S6432434U
- Authority
- JP
- Japan
- Prior art keywords
- inner disk
- scroll
- disk portion
- blade
- rotor blade
- 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
- 238000001816 cooling Methods 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims 1
- 238000009413 insulation Methods 0.000 description 2
- 230000007704 transition Effects 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Description
第１図は本考案のガスタービン機関の軸受部の
側面断面図、第２図は同じくロータ動翼１の内側
デイスク部２の部分の冷却装置、第３図は同じく
静翼３の内側デイスク部４と、ロータ動翼１の内
側デイスク部２の部分への冷却風の流れを示す拡
大断面図、第４図はロータ動翼の軸受部分におけ
る潤滑油のシール機構を示す拡大断面図、第５図
はロータ動翼１の冷却構造の他の実施例を示す断
面図である。
Ａ……スクロールと断熱壁の間の間隙、１……
ロータ動翼、２……ロータ動翼の内側デイスク部
、３……静翼、４……静翼の内側デイスク部、４
ａ……ノズル孔、５……トランジシヨンダクト支
持壁、６……断熱壁、７……スクロール、７ａ…
…ガス出口、８……コンプレツサ軸、８ａ……コ
ンプレツサ羽根。
FIG. 1 is a side sectional view of the bearing section of the gas turbine engine of the present invention, FIG. 2 is a cooling device for the inner disk section 2 of the rotor blade 1, and FIG. 3 is the inner disk section of the stationary blade 3. FIG. 4 is an enlarged sectional view showing the flow of cooling air to the inner disk portion 2 of the rotor blade 1; FIG. The figure is a sectional view showing another embodiment of the cooling structure for the rotor blade 1. A... Gap between the scroll and the insulation wall, 1...
Rotor moving blade, 2... Inner disk portion of rotor moving blade, 3... Stator blade, 4... Inner disk portion of stator blade, 4
a... Nozzle hole, 5... Transition duct support wall, 6... Heat insulation wall, 7... Scroll, 7a...
...Gas outlet, 8...Compressor shaft, 8a...Compressor blade.
Claims (1)
された静翼の内側デイスク部に、スクロール外周
とコンプレツサ吐出口６の間の間隙と連通し、か
つロータ動翼の内側デイスク部に対抗する向きに
貫通するノズル孔を設けたことを特徴とするガス
タービン機関の冷却構造。 The inner disk portion of the stationary blade interposed between the gas outlet of the scroll and the rotor blade is connected to the gap between the outer periphery of the scroll and the compressor discharge port 6, and is oriented opposite to the inner disk portion of the rotor blade. A cooling structure for a gas turbine engine, characterized by having a nozzle hole penetrating through the.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP12613087U JPS6432434U (en) | 1987-08-18 | 1987-08-18 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP12613087U JPS6432434U (en) | 1987-08-18 | 1987-08-18 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS6432434U true JPS6432434U (en) | 1989-03-01 |
Family
ID=31377364
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP12613087U Pending JPS6432434U (en) | 1987-08-18 | 1987-08-18 |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6432434U (en) |
-
1987
- 1987-08-18 JP JP12613087U patent/JPS6432434U/ja active Pending