JPS5654903A - Turbine blade and its manufacture - Google Patents

Turbine blade and its manufacture

Info

Publication number
JPS5654903A
JPS5654903A JP13131479A JP13131479A JPS5654903A JP S5654903 A JPS5654903 A JP S5654903A JP 13131479 A JP13131479 A JP 13131479A JP 13131479 A JP13131479 A JP 13131479A JP S5654903 A JPS5654903 A JP S5654903A
Authority
JP
Japan
Prior art keywords
turbine blade
manufacture
turbine
leading edge
edge 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
JP13131479A
Other languages
Japanese (ja)
Inventor
Kazuaki Ikeda
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 JP13131479A priority Critical patent/JPS5654903A/en
Publication of JPS5654903A publication Critical patent/JPS5654903A/en
Pending legal-status Critical Current

Links

Landscapes

  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE: To improve the erosion resistance of a turbine blade and permit the manufacture of a large sized turbine, by flame spray coating a layer of Ni-Cr-B onto a point end leading edge part of the turbine blade made of titanium system alloy.
CONSTITUTION: To the point end leading edge part of a turbine blade made of titanium system alloy, a flame spray coating consisting of 60W80% Ni, 15W30% Cr, 5% B and the rest of Fe, Si is applied. Further in the atmosphere of vacuum or inactive gas, heat treatment is applied to provide a diffusion layer in the blade end leading edge part. In this way, wear resistance and erosion resistance of the turbine blade can be improved to obtain the extension of a life. While use of the titanium alloy can form the blade in large length to permit the manufacture of a large sized of the turbine.
COPYRIGHT: (C)1981,JPO&Japio
JP13131479A 1979-10-13 1979-10-13 Turbine blade and its manufacture Pending JPS5654903A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP13131479A JPS5654903A (en) 1979-10-13 1979-10-13 Turbine blade and its manufacture

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP13131479A JPS5654903A (en) 1979-10-13 1979-10-13 Turbine blade and its manufacture

Publications (1)

Publication Number Publication Date
JPS5654903A true JPS5654903A (en) 1981-05-15

Family

ID=15055051

Family Applications (1)

Application Number Title Priority Date Filing Date
JP13131479A Pending JPS5654903A (en) 1979-10-13 1979-10-13 Turbine blade and its manufacture

Country Status (1)

Country Link
JP (1) JPS5654903A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2672833A1 (en) * 1991-02-19 1992-08-21 Grumman Aerospace Corp Process for protecting titanium-based materials by application of diffusion-bonded oxidation-resistant sheets

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2672833A1 (en) * 1991-02-19 1992-08-21 Grumman Aerospace Corp Process for protecting titanium-based materials by application of diffusion-bonded oxidation-resistant sheets

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