JPS5713201A - Air cooled gas turbine blade - Google Patents

Air cooled gas turbine blade

Info

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
Application number
JP8788680A
Other languages
Japanese (ja)
Inventor
Shigeyoshi Kobayashi
Manabu Matsumoto
Mitsutaka Shizutani
Shigeyuki Akatsu
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hitachi Ltd
Original Assignee
Hitachi Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Hitachi Ltd filed Critical Hitachi Ltd
Priority to JP8788680A priority Critical patent/JPS5713201A/en
Publication of JPS5713201A publication Critical patent/JPS5713201A/en
Pending legal-status Critical Current

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
JP8788680A 1980-06-30 1980-06-30 Air cooled gas turbine blade Pending JPS5713201A (en)

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)

* Cited by examiner, † Cited by third party
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

Cited By (15)

* Cited by examiner, † Cited by third party
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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