JPS5688902A - Turbine blade - Google Patents

Turbine blade

Info

Publication number
JPS5688902A
JPS5688902A JP16538779A JP16538779A JPS5688902A JP S5688902 A JPS5688902 A JP S5688902A JP 16538779 A JP16538779 A JP 16538779A JP 16538779 A JP16538779 A JP 16538779A JP S5688902 A JPS5688902 A JP S5688902A
Authority
JP
Japan
Prior art keywords
pressure side
negative pressure
blade
area
turbine blade
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.)
Granted
Application number
JP16538779A
Other languages
Japanese (ja)
Other versions
JPS6139482B2 (en
Inventor
Yasuo Okamoto
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.)
Toshiba Corp
Original Assignee
Toshiba Corp
Tokyo Shibaura Electric Co 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 Toshiba Corp, Tokyo Shibaura Electric Co Ltd filed Critical Toshiba Corp
Priority to JP16538779A priority Critical patent/JPS5688902A/en
Publication of JPS5688902A publication Critical patent/JPS5688902A/en
Publication of JPS6139482B2 publication Critical patent/JPS6139482B2/ja
Granted legal-status Critical Current

Links

Landscapes

  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE: In a turbine blade having specific area wherein a fluid running along the surface on a negative pressure side is decelerated, to pevent a damage of the turbine blade during transonic operation by permitting the fluid to pass through it from the negative pressure surface in the decelerating area.
CONSTITUTION: A blade P having a negative pressure side C and a pressure side D is moved in the direction R. Several hiles E are made through up to a decelerating area W on the negative pressure side C. As a fluid flows through the holes E, a pressure difference may be reduced between the pressure and negative prssure surfaces created when a shock wave runs against the decelerating area on the negative pressure side. Additionally, the shock wave is prevented from making severe vibration on this area, resulting in an application of a seriously fluctuating pressure on the blade P, and thus, a damage of the blade P can be prevented.
COPYRIGHT: (C)1981,JPO&Japio
JP16538779A 1979-12-19 1979-12-19 Turbine blade Granted JPS5688902A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP16538779A JPS5688902A (en) 1979-12-19 1979-12-19 Turbine blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP16538779A JPS5688902A (en) 1979-12-19 1979-12-19 Turbine blade

Publications (2)

Publication Number Publication Date
JPS5688902A true JPS5688902A (en) 1981-07-18
JPS6139482B2 JPS6139482B2 (en) 1986-09-04

Family

ID=15811416

Family Applications (1)

Application Number Title Priority Date Filing Date
JP16538779A Granted JPS5688902A (en) 1979-12-19 1979-12-19 Turbine blade

Country Status (1)

Country Link
JP (1) JPS5688902A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS616603U (en) * 1984-06-19 1986-01-16 トヨタ自動車株式会社 Shaft structure of turbine wheel for turbocharger
US4714408A (en) * 1985-06-06 1987-12-22 Nissan Motor Co., Ltd. Radiator fan
FR2695163A1 (en) * 1992-09-02 1994-03-04 Snecma Hollow vane for gas turbine rotor - has one-piece body with apertures closed by plug sections
WO2001055559A1 (en) * 2000-01-27 2001-08-02 Siemens Aktiengesellschaft Porous turbine blades and turbine equipped with blades of this type
FR2906563A1 (en) * 2006-09-28 2008-04-04 Snecma Sa Acoustic treatment method for front fan and dual-flow jet engine of e.g. transport plane, involves arranging cavities on wall near leading edge of blades to reduce amplitude and fluctuations of unsteady pressure in surface of blades
JP2008215233A (en) * 2007-03-06 2008-09-18 Ihi Corp Cooling turbine blade
JP2020133602A (en) * 2019-02-26 2020-08-31 三菱重工業株式会社 Blade and machine with the same

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS616603U (en) * 1984-06-19 1986-01-16 トヨタ自動車株式会社 Shaft structure of turbine wheel for turbocharger
JPH0415921Y2 (en) * 1984-06-19 1992-04-09
US4714408A (en) * 1985-06-06 1987-12-22 Nissan Motor Co., Ltd. Radiator fan
FR2695163A1 (en) * 1992-09-02 1994-03-04 Snecma Hollow vane for gas turbine rotor - has one-piece body with apertures closed by plug sections
WO2001055559A1 (en) * 2000-01-27 2001-08-02 Siemens Aktiengesellschaft Porous turbine blades and turbine equipped with blades of this type
FR2906563A1 (en) * 2006-09-28 2008-04-04 Snecma Sa Acoustic treatment method for front fan and dual-flow jet engine of e.g. transport plane, involves arranging cavities on wall near leading edge of blades to reduce amplitude and fluctuations of unsteady pressure in surface of blades
JP2008215233A (en) * 2007-03-06 2008-09-18 Ihi Corp Cooling turbine blade
JP2020133602A (en) * 2019-02-26 2020-08-31 三菱重工業株式会社 Blade and machine with the same

Also Published As

Publication number Publication date
JPS6139482B2 (en) 1986-09-04

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