JPS5713201A - Air cooled gas turbine blade - Google Patents
Air cooled gas turbine bladeInfo
- Publication number
- JPS5713201A JPS5713201A JP8788680A JP8788680A JPS5713201A JP S5713201 A JPS5713201 A JP S5713201A JP 8788680 A JP8788680 A JP 8788680A JP 8788680 A JP8788680 A JP 8788680A JP S5713201 A JPS5713201 A JP S5713201A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- air
- blow
- cooling air
- air intake
- 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 effectively utilize cooling air for a moving blade to improve the reliability and life of the turbine blade by forming in the moving blade two cooling air passages which are connected to cooling air intake ports provided on opposite front and rear edges of a root portion of the blade with air taken in on the blade rear edge side having a lower pressure than that of air taken in on the blade front edge side.
CONSTITUTION: A moving blade 10 has formed along front and rear edges thereof respective cooling air passages 13, 14 which are connected to front and rear edge side air intake ports 11, 12 formed in the front and rear edges of a blade root portion 100. Cooling air introduced from the air intake port 11 passes an air passage 13 to a blade end portion and partially blows off from an air blow-off hole 23 opened to a blade end recessed portion 24 while the remainder is turned away by a partition wall 15 to be jetted into an air header 16 and then further controlled at blow-off holes 21 at the blade front edge. Meanwhile, cooling air of a lower pressure than that at the air intake port 11 is introduced from the other air intake port 12. It then passes an air passage 14 and partially blows off from an air blow-off hole 23a at an end of the blade while the remainder passes an air header 16a and then blows off from blow-off holes/22 at the blade rear end. Thus, cooling efficiency can be improved by such a construction.
COPYRIGHT: (C)1982,JPO&Japio
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP8788680A JPS5713201A (en) | 1980-06-30 | 1980-06-30 | Air cooled gas turbine blade |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP8788680A JPS5713201A (en) | 1980-06-30 | 1980-06-30 | Air cooled gas turbine blade |
Publications (1)
Publication Number | Publication Date |
---|---|
JPS5713201A true JPS5713201A (en) | 1982-01-23 |
Family
ID=13927348
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP8788680A Pending JPS5713201A (en) | 1980-06-30 | 1980-06-30 | Air cooled gas turbine blade |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPS5713201A (en) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS58170801A (en) * | 1982-03-31 | 1983-10-07 | Toshiba Corp | Blade for turbine |
JPS5918203A (en) * | 1982-07-21 | 1984-01-30 | Agency Of Ind Science & Technol | Blade of gas turbine |
US4940388A (en) * | 1988-12-07 | 1990-07-10 | Rolls-Royce Plc | Cooling of turbine blades |
EP0924383A2 (en) * | 1997-12-17 | 1999-06-23 | United Technologies Corporation | Turbine blade with trailing edge root section cooling |
JP2007154887A (en) * | 2005-11-30 | 2007-06-21 | General Electric Co <Ge> | Method for reducing axial compressor blade tipflow and turbine machine |
US20110058933A1 (en) * | 2008-02-28 | 2011-03-10 | Mtu Aero Engines Gmbh | Device and method for redirecting a leakage current |
JP2014043798A (en) * | 2012-08-27 | 2014-03-13 | Hitachi Ltd | Gas turbine, gas turbine blade, and manufacturing method of gas turbine blade |
US9664051B2 (en) | 2011-06-16 | 2017-05-30 | Siemens Aktiengesellschaft | Rotor blade root section with cooling passage and method for supplying cooling fluid to a rotor blade |
US10718213B2 (en) | 2017-04-10 | 2020-07-21 | United Technologies Corporation | Dual cooling airflow to blades |
CN112459849A (en) * | 2020-10-27 | 2021-03-09 | 哈尔滨广瀚燃气轮机有限公司 | Cooling structure for turbine blade of gas turbine |
-
1980
- 1980-06-30 JP JP8788680A patent/JPS5713201A/en active Pending
Cited By (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS58170801A (en) * | 1982-03-31 | 1983-10-07 | Toshiba Corp | Blade for turbine |
JPH0451641B2 (en) * | 1982-03-31 | 1992-08-19 | Tokyo Shibaura Electric Co | |
JPS5918203A (en) * | 1982-07-21 | 1984-01-30 | Agency Of Ind Science & Technol | Blade of gas turbine |
US4940388A (en) * | 1988-12-07 | 1990-07-10 | Rolls-Royce Plc | Cooling of turbine blades |
EP0924383A3 (en) * | 1997-12-17 | 2000-01-12 | United Technologies Corporation | Turbine blade with trailing edge root section cooling |
US5975851A (en) * | 1997-12-17 | 1999-11-02 | United Technologies Corporation | Turbine blade with trailing edge root section cooling |
EP0924383A2 (en) * | 1997-12-17 | 1999-06-23 | United Technologies Corporation | Turbine blade with trailing edge root section cooling |
JP2007154887A (en) * | 2005-11-30 | 2007-06-21 | General Electric Co <Ge> | Method for reducing axial compressor blade tipflow and turbine machine |
US20110058933A1 (en) * | 2008-02-28 | 2011-03-10 | Mtu Aero Engines Gmbh | Device and method for redirecting a leakage current |
US8753070B2 (en) * | 2008-02-28 | 2014-06-17 | Mtu Aero Engines Gmbh | Device and method for redirecting a leakage current |
US9664051B2 (en) | 2011-06-16 | 2017-05-30 | Siemens Aktiengesellschaft | Rotor blade root section with cooling passage and method for supplying cooling fluid to a rotor blade |
JP2014043798A (en) * | 2012-08-27 | 2014-03-13 | Hitachi Ltd | Gas turbine, gas turbine blade, and manufacturing method of gas turbine blade |
US10718213B2 (en) | 2017-04-10 | 2020-07-21 | United Technologies Corporation | Dual cooling airflow to blades |
US10934845B2 (en) | 2017-04-10 | 2021-03-02 | Raytheon Technologies Corporation | Dual cooling airflow to blades |
CN112459849A (en) * | 2020-10-27 | 2021-03-09 | 哈尔滨广瀚燃气轮机有限公司 | Cooling structure for turbine blade of gas turbine |
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