JPS5453710A - Turbine blade and its manufacturing method - Google Patents

Turbine blade and its manufacturing method

Info

Publication number
JPS5453710A
JPS5453710A JP11991977A JP11991977A JPS5453710A JP S5453710 A JPS5453710 A JP S5453710A JP 11991977 A JP11991977 A JP 11991977A JP 11991977 A JP11991977 A JP 11991977A JP S5453710 A JPS5453710 A JP S5453710A
Authority
JP
Japan
Prior art keywords
cavity
blade
turbine blade
manufacturing
gas turbine
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
JP11991977A
Other languages
Japanese (ja)
Other versions
JPS6045284B2 (en
Inventor
Hiroshi Fukui
Tetsuo Kashimura
Fumio Hataya
Nobuyuki Iizuka
Takashi Ito
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 JP11991977A priority Critical patent/JPS6045284B2/en
Publication of JPS5453710A publication Critical patent/JPS5453710A/en
Publication of JPS6045284B2 publication Critical patent/JPS6045284B2/en
Expired legal-status Critical Current

Links

Landscapes

  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE: To prevent a gas turbine blade from being destroyed due to its fragility by making a padding weld in rear of a cavity for reducting concentrated stress.
CONSTITUTION: A blade 3 of a gas turbine rotates in the direction 6 and constitutes a front leading part 8 and a rear trailing part 5. A cavity 4 is made in the end 3k of the blade, which is to reduce stress concentrated by centrifugal force of the self- weight. A padding weld 9 is made on the trailing part 5 in rear of the cavity 4 and prevents destroy caused by heat stress
COPYRIGHT: (C)1979,JPO&Japio
JP11991977A 1977-10-07 1977-10-07 Turbine blades and manufacturing method Expired JPS6045284B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP11991977A JPS6045284B2 (en) 1977-10-07 1977-10-07 Turbine blades and manufacturing method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP11991977A JPS6045284B2 (en) 1977-10-07 1977-10-07 Turbine blades and manufacturing method

Publications (2)

Publication Number Publication Date
JPS5453710A true JPS5453710A (en) 1979-04-27
JPS6045284B2 JPS6045284B2 (en) 1985-10-08

Family

ID=14773415

Family Applications (1)

Application Number Title Priority Date Filing Date
JP11991977A Expired JPS6045284B2 (en) 1977-10-07 1977-10-07 Turbine blades and manufacturing method

Country Status (1)

Country Link
JP (1) JPS6045284B2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2394751A (en) * 2002-11-02 2004-05-05 Rolls Royce Plc Anti creep turbine blade with internal cavity

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS61204886U (en) * 1985-06-14 1986-12-24
JPS6286292U (en) * 1985-11-20 1987-06-02

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2394751A (en) * 2002-11-02 2004-05-05 Rolls Royce Plc Anti creep turbine blade with internal cavity

Also Published As

Publication number Publication date
JPS6045284B2 (en) 1985-10-08

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