GB823111A - Improvements relating to the protection against oxidation of articles of molybdenum or molybdenum base alloy - Google Patents

Improvements relating to the protection against oxidation of articles of molybdenum or molybdenum base alloy

Info

Publication number
GB823111A
GB823111A GB13203/56A GB1320356A GB823111A GB 823111 A GB823111 A GB 823111A GB 13203/56 A GB13203/56 A GB 13203/56A GB 1320356 A GB1320356 A GB 1320356A GB 823111 A GB823111 A GB 823111A
Authority
GB
United Kingdom
Prior art keywords
coating
blade
molybdenum
nickel
sprayed
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.)
Expired
Application number
GB13203/56A
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB823111A publication Critical patent/GB823111A/en
Expired legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)

Abstract

823,111. Turbine blades. GENERAL ELECTRIC CO. April 30, 1956 [May 11, 1955], No. 13203/56. Class 110 (3). [Also in Group XXII] In protecting a turbine blade of molybdenum or molybdenum base alloy a first metallic oxidation resistant coating is applied to the blade, a second metallic oxidation resistant coating having a greater resistance to impact, abrasion and erosion than the first coating is applied to at least part of the coated blade and the second coating is secured to the blade by fusing the first coating. A molybdenum gas turbine blade 1 is cleaned by electro-polishing to a mirror finish then roughtened by grit blasting and then reducing flame sprayed with a nickel-siliconboron alloy 6 to a thickness of 0.005 inch. The blade is then heat treated in a hydrogen furnace by preheating to 1500-1900‹ F. when partial sintering takes place between the sprayed particles, by heating to 2100‹ F. to melt the sprayed coating and by cooling in the hydrogen atmosphere. At least the area of the coating 6 to be further coated is cleaned with emery cloth and carbon tetrachloride or by vapour blast and vapour degreaser. A foil 7 0.003- 0.006 inch thick of 80% nickel, 20% chromium or 78% nickel 15% chromium 7% iron is shaped to the blade and held in position thereon between shaped forms 10, 11 by clamps 15, 16 to cover an area bounded by lines 8 and 9. The assembly is preheated at 1500-1900‹ F. in a hydrogen furnace and is then heated to 2150‹ F., at or above the melting point of the first coating, to melt the first coating which bonds the foil to the blade. After fusing the blade is cooled in the hydrogen atmosphere. The second coating may be surface hardened by cleaning, painting with aluminium and then heating to 1800‹ F. in a reducing atmosphere for 1-4 hours.
GB13203/56A 1955-05-11 1956-04-30 Improvements relating to the protection against oxidation of articles of molybdenum or molybdenum base alloy Expired GB823111A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US823111XA 1955-05-11 1955-05-11

Publications (1)

Publication Number Publication Date
GB823111A true GB823111A (en) 1959-11-04

Family

ID=22170403

Family Applications (1)

Application Number Title Priority Date Filing Date
GB13203/56A Expired GB823111A (en) 1955-05-11 1956-04-30 Improvements relating to the protection against oxidation of articles of molybdenum or molybdenum base alloy

Country Status (1)

Country Link
GB (1) GB823111A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2124126A (en) * 1982-06-23 1984-02-15 Refurbished Turbine Components A method of repairing turbine blades
DE102007016411A1 (en) 2007-04-02 2008-10-09 Gfe Fremat Gmbh Semi-finished refractory metal product for producing ingot has protective layer giving protection against oxidation during hot deformation of semi-finished product

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2124126A (en) * 1982-06-23 1984-02-15 Refurbished Turbine Components A method of repairing turbine blades
US4611744A (en) * 1982-06-23 1986-09-16 Refurbished Turbine Components Ltd. Turbine blade repair
DE102007016411A1 (en) 2007-04-02 2008-10-09 Gfe Fremat Gmbh Semi-finished refractory metal product for producing ingot has protective layer giving protection against oxidation during hot deformation of semi-finished product

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