JPS57168006A - Method of manufacturing turbine blades - Google Patents

Method of manufacturing turbine blades

Info

Publication number
JPS57168006A
JPS57168006A JP5173981A JP5173981A JPS57168006A JP S57168006 A JPS57168006 A JP S57168006A JP 5173981 A JP5173981 A JP 5173981A JP 5173981 A JP5173981 A JP 5173981A JP S57168006 A JPS57168006 A JP S57168006A
Authority
JP
Japan
Prior art keywords
blade
root
residual stress
compressive residual
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.)
Pending
Application number
JP5173981A
Other languages
Japanese (ja)
Inventor
Hironori Kii
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.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries 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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to JP5173981A priority Critical patent/JPS57168006A/en
Publication of JPS57168006A publication Critical patent/JPS57168006A/en
Pending legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE:To improve the corrosion-fatigue resistance of a turbine blade, by forming a compressive residual stress layer in the blade root notched part. CONSTITUTION:After an excessive tension load is imposed on the root part 11 of an unused turbine blade 1, it is released to zero, then the compressive residual stress sigmaD is generated at the bottom of a notch 13 at the root part of the blade 1. The excessive pre-tension load should be larger than the maximum centrifugal force induced in the blade during the trial test or service time of the turbine and it produces plastic deformation at the bottom of the notched part 13 of the blade root, provided that no crack occurs. With these contrivances, a thick compressive residual stress layer 15 is formed at the notched part 13 of the blade root, which prevents the turbine blade 1 from lowering its fatigue resistance in the corrosive atmosphere.
JP5173981A 1981-04-08 1981-04-08 Method of manufacturing turbine blades Pending JPS57168006A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP5173981A JPS57168006A (en) 1981-04-08 1981-04-08 Method of manufacturing turbine blades

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP5173981A JPS57168006A (en) 1981-04-08 1981-04-08 Method of manufacturing turbine blades

Publications (1)

Publication Number Publication Date
JPS57168006A true JPS57168006A (en) 1982-10-16

Family

ID=12895267

Family Applications (1)

Application Number Title Priority Date Filing Date
JP5173981A Pending JPS57168006A (en) 1981-04-08 1981-04-08 Method of manufacturing turbine blades

Country Status (1)

Country Link
JP (1) JPS57168006A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006087292A1 (en) 2005-02-15 2006-08-24 Alstom Technology Ltd Method for prolonging the fatigue life of a blade footing of a turobmachine blade
CN104972281A (en) * 2015-07-15 2015-10-14 江西洪都航空工业集团有限责任公司 Machining technology of open structure part

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006087292A1 (en) 2005-02-15 2006-08-24 Alstom Technology Ltd Method for prolonging the fatigue life of a blade footing of a turobmachine blade
US7761993B2 (en) 2005-02-15 2010-07-27 Alstom Technology Ltd Method for increasing the fatigue life of a blade root of a turbomachine blade
CN104972281A (en) * 2015-07-15 2015-10-14 江西洪都航空工业集团有限责任公司 Machining technology of open structure part

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