JPS5550991A - Corrosion preventive piece joining method of turbine blade - Google Patents

Corrosion preventive piece joining method of turbine blade

Info

Publication number
JPS5550991A
JPS5550991A JP12252778A JP12252778A JPS5550991A JP S5550991 A JPS5550991 A JP S5550991A JP 12252778 A JP12252778 A JP 12252778A JP 12252778 A JP12252778 A JP 12252778A JP S5550991 A JPS5550991 A JP S5550991A
Authority
JP
Japan
Prior art keywords
piece
metal
anticorrosive
stress
buffer part
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
JP12252778A
Other languages
Japanese (ja)
Inventor
Munenobu Suzuki
Tomohiko Shida
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 JP12252778A priority Critical patent/JPS5550991A/en
Publication of JPS5550991A publication Critical patent/JPS5550991A/en
Pending legal-status Critical Current

Links

Landscapes

  • Turbine Rotor Nozzle Sealing (AREA)
  • Butt Welding And Welding Of Specific Article (AREA)

Abstract

PURPOSE: To prevent stress corrosion cracking without having to form each member in special shape or making special treatment, by providing stress buffer part in the anticorrosive piece starting end part.
CONSTITUTION: A corrosion resistant member 2 is welded, by electron beam or the like, to a turbine blade part 1 which may be corroded by water drops in the working vapor, through an intermediate medium metal 3. The position starting shield by an anticorrosive piece 2 is built up by TIG welding, by using a metal which is more easily deformed plastically than the corrosive piece, for example, the same Inconel as the intermediate medium metal 3, as the filler metal, and a stress buffer part 6 is formed. Next, with the main purpose of approaching the blade member welding heat affected zone to the property of the blade base metal, refining heat treatment is applied. In this state, since the coefficient of thermal expansion of the anticorrosive piece is larger than that of other parts, tensile stress remains in the anticorrosive piece. Hence, the stress buffer part is subjected to plastic deformation by peening, and, to the contrary, compressive stress is applied to the anticorrosive piece.
COPYRIGHT: (C)1980,JPO&Japio
JP12252778A 1978-10-06 1978-10-06 Corrosion preventive piece joining method of turbine blade Pending JPS5550991A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP12252778A JPS5550991A (en) 1978-10-06 1978-10-06 Corrosion preventive piece joining method of turbine blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP12252778A JPS5550991A (en) 1978-10-06 1978-10-06 Corrosion preventive piece joining method of turbine blade

Publications (1)

Publication Number Publication Date
JPS5550991A true JPS5550991A (en) 1980-04-14

Family

ID=14838049

Family Applications (1)

Application Number Title Priority Date Filing Date
JP12252778A Pending JPS5550991A (en) 1978-10-06 1978-10-06 Corrosion preventive piece joining method of turbine blade

Country Status (1)

Country Link
JP (1) JPS5550991A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH03269068A (en) * 1990-03-19 1991-11-29 Dainichiseika Color & Chem Mfg Co Ltd Coloring composition for image recording
GB2555211A (en) * 2016-08-29 2018-04-25 Safran Aircraft Engines Turbomachine vane provided with a structure reducing the risk of cracks

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH03269068A (en) * 1990-03-19 1991-11-29 Dainichiseika Color & Chem Mfg Co Ltd Coloring composition for image recording
GB2555211A (en) * 2016-08-29 2018-04-25 Safran Aircraft Engines Turbomachine vane provided with a structure reducing the risk of cracks
GB2555211B (en) * 2016-08-29 2021-10-20 Safran Aircraft Engines Turbomachine vane provided with a structure reducing the risk of cracks

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