JPS55114806A - Gas turbine blade - Google Patents
Gas turbine bladeInfo
- Publication number
- JPS55114806A JPS55114806A JP2388079A JP2388079A JPS55114806A JP S55114806 A JPS55114806 A JP S55114806A JP 2388079 A JP2388079 A JP 2388079A JP 2388079 A JP2388079 A JP 2388079A JP S55114806 A JPS55114806 A JP S55114806A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- air
- round hole
- slit
- flow
- 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
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
PURPOSE: To obtain a construction of the blade with an excellent thermally shielding effect further with an excellent material strength and workability, by constructing a film stream of the effective air of low temperature fully on surfaces of the blade, that is, by forming a front half on the blowing flow line into a round hole train pattern and a rear half of that into a slit pattern.
CONSTITUTION: In the gas turbine blade of a construction to blow out a cooling air along an external surface of the blade from the interior of the blade, after processing to form a round hole train in a base material 1 of the blade from its external surface to internal surface, a processing work into a slit pattern is performed from the outside to construct a blowing hole in such a manner as to finish an inner side section 2 into the round hole train portion and an outer side section 3 into the slit portion. In this way, the strength of the blade can be ensured by partitions between the round holes in the front half portion while the flow of an air, that causes a big non-uniformity of the air speed in a direction of the blade span due to the flow lines of round hole train pattern in the front half portion, can be smoothed ed by the slit patterned flow lines in the rear half portion, thus maintaining a film stream of the cooling air to the downstream of the air flow and improving the thermally shielding effect.
COPYRIGHT: (C)1980,JPO&Japio
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2388079A JPS55114806A (en) | 1979-02-27 | 1979-02-27 | Gas turbine blade |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2388079A JPS55114806A (en) | 1979-02-27 | 1979-02-27 | Gas turbine blade |
Publications (1)
Publication Number | Publication Date |
---|---|
JPS55114806A true JPS55114806A (en) | 1980-09-04 |
Family
ID=12122756
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2388079A Pending JPS55114806A (en) | 1979-02-27 | 1979-02-27 | Gas turbine blade |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPS55114806A (en) |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS59136502A (en) * | 1982-09-16 | 1984-08-06 | ロ−ルス−ロイス、パブリック、リミテッド、カンパニ− | Cooling gas turbine engine aerofoil |
US4653983A (en) * | 1985-12-23 | 1987-03-31 | United Technologies Corporation | Cross-flow film cooling passages |
US4664597A (en) * | 1985-12-23 | 1987-05-12 | United Technologies Corporation | Coolant passages with full coverage film cooling slot |
US4669957A (en) * | 1985-12-23 | 1987-06-02 | United Technologies Corporation | Film coolant passage with swirl diffuser |
US4676719A (en) * | 1985-12-23 | 1987-06-30 | United Technologies Corporation | Film coolant passages for cast hollow airfoils |
US4684323A (en) * | 1985-12-23 | 1987-08-04 | United Technologies Corporation | Film cooling passages with curved corners |
US4738588A (en) * | 1985-12-23 | 1988-04-19 | Field Robert E | Film cooling passages with step diffuser |
US4859147A (en) * | 1988-01-25 | 1989-08-22 | United Technologies Corporation | Cooled gas turbine blade |
US6241468B1 (en) | 1998-10-06 | 2001-06-05 | Rolls-Royce Plc | Coolant passages for gas turbine components |
US20130045106A1 (en) * | 2011-08-15 | 2013-02-21 | General Electric Company | Angled trench diffuser |
US9273561B2 (en) | 2012-08-03 | 2016-03-01 | General Electric Company | Cooling structures for turbine rotor blade tips |
CN108999646A (en) * | 2017-06-07 | 2018-12-14 | 安萨尔多能源瑞士股份公司 | Blade for gas turbine and the electric power generating device including the blade |
-
1979
- 1979-02-27 JP JP2388079A patent/JPS55114806A/en active Pending
Cited By (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS59136502A (en) * | 1982-09-16 | 1984-08-06 | ロ−ルス−ロイス、パブリック、リミテッド、カンパニ− | Cooling gas turbine engine aerofoil |
US4684323A (en) * | 1985-12-23 | 1987-08-04 | United Technologies Corporation | Film cooling passages with curved corners |
JPS62165504A (en) * | 1985-12-23 | 1987-07-22 | ユナイテツド・テクノロジ−ズ・コ−ポレイシヨン | Wall cooled in aerofoil |
US4669957A (en) * | 1985-12-23 | 1987-06-02 | United Technologies Corporation | Film coolant passage with swirl diffuser |
US4676719A (en) * | 1985-12-23 | 1987-06-30 | United Technologies Corporation | Film coolant passages for cast hollow airfoils |
US4738588A (en) * | 1985-12-23 | 1988-04-19 | Field Robert E | Film cooling passages with step diffuser |
EP0227577A2 (en) * | 1985-12-23 | 1987-07-01 | United Technologies Corporation | Coolant passages with full coverage film cooling slot |
US4664597A (en) * | 1985-12-23 | 1987-05-12 | United Technologies Corporation | Coolant passages with full coverage film cooling slot |
US4653983A (en) * | 1985-12-23 | 1987-03-31 | United Technologies Corporation | Cross-flow film cooling passages |
EP0227579A2 (en) * | 1985-12-23 | 1987-07-01 | United Technologies Corporation | Film coolant passage with swirl diffuser |
EP0227579B1 (en) * | 1985-12-23 | 1992-01-29 | United Technologies Corporation | Film coolant passage with swirl diffuser |
EP0227577B1 (en) * | 1985-12-23 | 1992-01-29 | United Technologies Corporation | Coolant passages with full coverage film cooling slot |
US4859147A (en) * | 1988-01-25 | 1989-08-22 | United Technologies Corporation | Cooled gas turbine blade |
US6241468B1 (en) | 1998-10-06 | 2001-06-05 | Rolls-Royce Plc | Coolant passages for gas turbine components |
US20130045106A1 (en) * | 2011-08-15 | 2013-02-21 | General Electric Company | Angled trench diffuser |
US9273561B2 (en) | 2012-08-03 | 2016-03-01 | General Electric Company | Cooling structures for turbine rotor blade tips |
CN108999646A (en) * | 2017-06-07 | 2018-12-14 | 安萨尔多能源瑞士股份公司 | Blade for gas turbine and the electric power generating device including the blade |
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