JPS6375502U - - Google Patents
Info
- Publication number
- JPS6375502U JPS6375502U JP16907886U JP16907886U JPS6375502U JP S6375502 U JPS6375502 U JP S6375502U JP 16907886 U JP16907886 U JP 16907886U JP 16907886 U JP16907886 U JP 16907886U JP S6375502 U JPS6375502 U JP S6375502U
- Authority
- JP
- Japan
- Prior art keywords
- blade
- flow path
- cooling
- protrusions
- grooves
- 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 5
- 238000010586 diagram Methods 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
Description
第１図は本考案の一実施例の翼冷却構造の縦断
面図、第２図は第１図のＡ―Ａ線断面図、第３図
は本考案の他の実施例の縦断面図、第４図は本考
案の更に他の実施例の翼の前縁付近の断面の見取
り図、第５図は従来構造のリターンフロー翼であ
る。
１……冷却系統、２……冷却系統、３……隔壁
、４……溝、５……溝、６……タービンユレンス
プロモータ、７……流路、８……排出孔、９……
流路、１０……ピンフイン、１２……板、１３…
…部屋、１４……小孔、１５……流路、１６……
切欠き。
FIG. 1 is a longitudinal cross-sectional view of a blade cooling structure according to an embodiment of the present invention, FIG. 2 is a cross-sectional view taken along line AA in FIG. 1, and FIG. 3 is a longitudinal cross-sectional view of another embodiment of the present invention. FIG. 4 is a schematic diagram of a cross section near the leading edge of a blade according to another embodiment of the present invention, and FIG. 5 is a return flow blade of a conventional structure. DESCRIPTION OF SYMBOLS 1... Cooling system, 2... Cooling system, 3... Partition wall, 4... Groove, 5... Groove, 6... Turbine spring promoter, 7... Channel, 8... Discharge hole, 9...
Channel, 10... pin fin, 12... plate, 13...
...Room, 14...Small hole, 15...Flow path, 16...
Notch.
Claims (1)
有する翼の内壁の一部又は全域に溝、段差又は突
起を設け、これにより翼本体とは独立した平板又
は曲板を翼内部に支持して流路又は部屋を形成す
ることを特徴とするガスタービン翼冷却構造。 For cooling blades of high-temperature gas turbines, grooves, steps, or protrusions are provided in a part or the entire area of the inner wall of the blade having a space, thereby supporting a flat plate or curved plate independent of the blade body inside the blade to create a flow path. Or a gas turbine blade cooling structure characterized by forming a chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP16907886U JPS6375502U (en) | 1986-11-05 | 1986-11-05 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP16907886U JPS6375502U (en) | 1986-11-05 | 1986-11-05 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS6375502U true JPS6375502U (en) | 1988-05-19 |
Family
ID=31102556
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP16907886U Pending JPS6375502U (en) | 1986-11-05 | 1986-11-05 |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6375502U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018008813A1 (en) * | 2016-07-04 | 2018-01-11 | 두산중공업 주식회사 | Gas turbine blade |
-
1986
- 1986-11-05 JP JP16907886U patent/JPS6375502U/ja active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018008813A1 (en) * | 2016-07-04 | 2018-01-11 | 두산중공업 주식회사 | Gas turbine blade |
| US10837289B2 (en) | 2016-07-04 | 2020-11-17 | Doosan Heavy Industries Construction Co., Ltd. | Gas turbine blade |