JPS55114806A - Gas turbine blade - Google Patents

Gas turbine blade

Info

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
Application number
JP2388079A
Other languages
Japanese (ja)
Inventor
Mitsutaka Shizutani
Takeshi Sakamoto
Shigeyoshi Kobayashi
Manabu Matsumoto
Shunichi Anzai
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 JP2388079A priority Critical patent/JPS55114806A/en
Publication of JPS55114806A publication Critical patent/JPS55114806A/en
Pending legal-status Critical Current

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
JP2388079A 1979-02-27 1979-02-27 Gas turbine blade Pending JPS55114806A (en)

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)

* Cited by examiner, † Cited by third party
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

Cited By (17)

* Cited by examiner, † Cited by third party
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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