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JPS5669405A - Stationary blade of turbine - Google Patents

Stationary blade of turbine

Info

Publication number
JPS5669405A
JPS5669405A JP14446579A JP14446579A JPS5669405A JP S5669405 A JPS5669405 A JP S5669405A JP 14446579 A JP14446579 A JP 14446579A JP 14446579 A JP14446579 A JP 14446579A JP S5669405 A JPS5669405 A JP S5669405A
Authority
JP
Japan
Prior art keywords
blade
rear edge
turbine
stationary
stationary 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
JP14446579A
Other languages
Japanese (ja)
Other versions
JPS5925091B2 (en
Inventor
Tetsuo Sasada
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 JP54144465A priority Critical patent/JPS5925091B2/en
Publication of JPS5669405A publication Critical patent/JPS5669405A/en
Publication of JPS5925091B2 publication Critical patent/JPS5925091B2/en
Expired legal-status Critical Current

Links

Landscapes

  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE: To improve the strength of stationary blades, which constitute the output section of an axial-flow turbine, and to enhance the efficiency of the turbine, by protruding the rear edge of each stationary blade in the direction from the longitudinally central part of the blade toward an inner and an outer diaphragm rings.
CONSTITUTION: A plurality of stationary blades 11 are secured between an inner diaphragm ring 2 and an outer diaphragm ring 3. Each stationary blade 11 is curved as a bow so that the rear edge 11b of the blade 11 is gradually protruded in the direction from the longitudinally central part of the blade 11 toward the downstream side according as the distance from the inner and the outer diaphragm rings 2, 3 to the rear edge 11b decreases. Since the thickness te.C of the blade 11 at a point C where the maximum moment arm extends is much larger than that (te) of the rear edge 11b, the stress at the point C is low. This results in improving the strength of the stationary blade 11 and the turbine efficiency.
COPYRIGHT: (C)1981,JPO&Japio
JP54144465A 1979-11-09 1979-11-09 turbine stator blade Expired JPS5925091B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP54144465A JPS5925091B2 (en) 1979-11-09 1979-11-09 turbine stator blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP54144465A JPS5925091B2 (en) 1979-11-09 1979-11-09 turbine stator blade

Publications (2)

Publication Number Publication Date
JPS5669405A true JPS5669405A (en) 1981-06-10
JPS5925091B2 JPS5925091B2 (en) 1984-06-14

Family

ID=15362897

Family Applications (1)

Application Number Title Priority Date Filing Date
JP54144465A Expired JPS5925091B2 (en) 1979-11-09 1979-11-09 turbine stator blade

Country Status (1)

Country Link
JP (1) JPS5925091B2 (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0569301U (en) * 1992-02-27 1993-09-21 石川島播磨重工業株式会社 Turbine nozzle
US6079948A (en) * 1996-09-30 2000-06-27 Kabushiki Kaisha Toshiba Blade for axial fluid machine having projecting portion at the tip and root of the blade
JP2001132696A (en) * 1999-11-05 2001-05-18 General Electric Co <Ge> Stationary blade having narrow waist part
WO2007042522A1 (en) * 2005-10-11 2007-04-19 Alstom Technology Ltd Turbo-machine blade
EP1657401A3 (en) * 2004-11-12 2009-01-21 Rolls-Royce Deutschland Ltd & Co KG Turbo machine blade with an extended profile chord length in its tip and root regions
JP2014521874A (en) * 2011-08-04 2014-08-28 ジエ・アヴィオ・エッセ・エッレ・エッレ Gas turbine engine for aircraft engine
EP2492440A3 (en) * 2011-02-22 2014-09-03 Mitsubishi Hitachi Power Systems, Ltd. Turbine nozzle blade and steam turbine equipment using same

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0569301U (en) * 1992-02-27 1993-09-21 石川島播磨重工業株式会社 Turbine nozzle
US6079948A (en) * 1996-09-30 2000-06-27 Kabushiki Kaisha Toshiba Blade for axial fluid machine having projecting portion at the tip and root of the blade
JP2001132696A (en) * 1999-11-05 2001-05-18 General Electric Co <Ge> Stationary blade having narrow waist part
EP1657401A3 (en) * 2004-11-12 2009-01-21 Rolls-Royce Deutschland Ltd & Co KG Turbo machine blade with an extended profile chord length in its tip and root regions
US8382438B2 (en) 2004-11-12 2013-02-26 Rolls-Royce Deutschland Ltd & Co Kg Blade of a turbomachine with enlarged peripheral profile depth
WO2007042522A1 (en) * 2005-10-11 2007-04-19 Alstom Technology Ltd Turbo-machine blade
JP2009511811A (en) * 2005-10-11 2009-03-19 アルストム テクノロジー リミテッド Turbomachinery wing
US8221065B2 (en) 2005-10-11 2012-07-17 Alstom Technology Ltd Turbomachine blade with variable chord length
JP2012207668A (en) * 2005-10-11 2012-10-25 Alstom Technology Ltd Turbo machine blade
EP2492440A3 (en) * 2011-02-22 2014-09-03 Mitsubishi Hitachi Power Systems, Ltd. Turbine nozzle blade and steam turbine equipment using same
JP2014521874A (en) * 2011-08-04 2014-08-28 ジエ・アヴィオ・エッセ・エッレ・エッレ Gas turbine engine for aircraft engine
US9810082B2 (en) 2011-08-04 2017-11-07 Ge Avio S.R.L. Gas turbine engine for aircraft engine

Also Published As

Publication number Publication date
JPS5925091B2 (en) 1984-06-14

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