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GB1298860A - Improvements in methods for the manufacture of a composite refractory metallic element with porous coating and the corresponding metallic elements - Google Patents

Improvements in methods for the manufacture of a composite refractory metallic element with porous coating and the corresponding metallic elements

Info

Publication number
GB1298860A
GB1298860A GB26620/70A GB2662070A GB1298860A GB 1298860 A GB1298860 A GB 1298860A GB 26620/70 A GB26620/70 A GB 26620/70A GB 2662070 A GB2662070 A GB 2662070A GB 1298860 A GB1298860 A GB 1298860A
Authority
GB
United Kingdom
Prior art keywords
brazing
nickel
cobalt
porous
chromium
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
GB26620/70A
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.)
Office National dEtudes et de Recherches Aerospatiales ONERA
Safran Aircraft Engines SAS
Original Assignee
Office National dEtudes et de Recherches Aerospatiales ONERA
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Office National dEtudes et de Recherches Aerospatiales ONERA, Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Office National dEtudes et de Recherches Aerospatiales ONERA
Publication of GB1298860A publication Critical patent/GB1298860A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/001—Interlayers, transition pieces for metallurgical bonding of workpieces
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

1298860 Brazing OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES and SOC NATIONAL D'ETUDES ET DE CONSTRUCTION DE MOTEURS D'AVIATON 2 June 1970 [10 June 1969] 26620/70 Heading B3R In the manufacture of a composite refractory metallic element (e.g. a gas turbine casing element, having a porous lining 2 against which the blade ends A may bear sealingly and which may wear away to accommodate any elongation of the blades in operation) a porous metallic coating 2 is bonded to a metallic support 1 by lightly compressing brazing material 3 between them and heating the assembly to around the melting point of the brazing material while subjecting the brazing material through the porous coating to a halogenated, e.g. fluorinated atmosphere, the whole brazing operation being carried out in a partially gas tight container surrounded by a hydrogenated atmosphere. The support 1 may be of stainless steel or of refractory alloy based on nickel, cobalt or chromium, the porous coating 2 is preferably a nickel felt having a porosity of about 80% or may contain an appreciable proportion of nickel and/or cobalt and/or iron, and the braze material contains phosphorus, and at least one of the group iron, cobalt, nickel. The brazing layer 3 may be 50 to 250 microns in thickness and may be deposited from a lacquer containing the braze material in powder form or by a plasma torch. If the members 1, 2 are ring-shaped the required pressure for the brazing operation may be derived from the expansion of a ring 4 of material of higher coefficient of expansion placed within the assembly prior to brazing. The brazed article may be subjected to a subsequent chromizing or chrome/aluminizing treatment by heating in a partially gas tight container enclosed in a hydrogen atmosphere, the container containing chromium or chromium/aluminium powder together with a halogenide carrier, e.g. an iodide or preferably a bromide or chloride.
GB26620/70A 1969-06-10 1970-06-02 Improvements in methods for the manufacture of a composite refractory metallic element with porous coating and the corresponding metallic elements Expired GB1298860A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR6919210A FR2049448A5 (en) 1969-06-10 1969-06-10

Publications (1)

Publication Number Publication Date
GB1298860A true GB1298860A (en) 1972-12-06

Family

ID=9035490

Family Applications (1)

Application Number Title Priority Date Filing Date
GB26620/70A Expired GB1298860A (en) 1969-06-10 1970-06-02 Improvements in methods for the manufacture of a composite refractory metallic element with porous coating and the corresponding metallic elements

Country Status (7)

Country Link
US (1) US3713206A (en)
CA (1) CA937107A (en)
CH (1) CH516370A (en)
DE (1) DE2028630C3 (en)
FR (1) FR2049448A5 (en)
GB (1) GB1298860A (en)
SE (1) SE365964B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2558026C1 (en) * 2014-03-03 2015-07-27 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Soldering of porous material with substrate

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3807030A (en) * 1972-12-27 1974-04-30 Chrysler Corp Method of preparing oxidation resistant materials
FR2294014A1 (en) * 1974-12-13 1976-07-09 Cerca HOT ASSEMBLY PROCESS
US4119262A (en) * 1977-07-05 1978-10-10 Ford Motor Company Method of joining metal, particularly aluminum or aluminum alloys, using bromine fluxing agent
US4155755A (en) * 1977-09-21 1979-05-22 Union Carbide Corporation Oxidation resistant porous abradable seal member for high temperature service
US4965095A (en) * 1979-03-30 1990-10-23 Alloy Surfaces Company, Inc. Method for refurbishing used jet engine hot section airfoils
US5915193A (en) * 1995-05-18 1999-06-22 Tong; Qin-Yi Method for the cleaning and direct bonding of solids
US6416589B1 (en) 1999-02-18 2002-07-09 General Electric Company Carbon-enhanced fluoride ion cleaning
WO2003010419A1 (en) * 2001-07-23 2003-02-06 Alstom Technology Ltd Device for reducing sealing gaps between moving and stationary components inside a non-positive-displacement machine
DE102005058324A1 (en) * 2005-12-07 2007-06-14 Mtu Aero Engines Gmbh Method for producing an inlet lining
DE102009036405A1 (en) 2009-08-06 2011-02-10 Mtu Aero Engines Gmbh Repair of turbine components and solder alloy for this
US20110086163A1 (en) * 2009-10-13 2011-04-14 Walbar Inc. Method for producing a crack-free abradable coating with enhanced adhesion

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2424878A (en) * 1944-10-28 1947-07-29 Reed Roller Bit Co Method of bonding a liner within a bore
US2561565A (en) * 1946-06-22 1951-07-24 United Aircraft Corp Process of fluxing and joining metal parts
US2585819A (en) * 1946-06-22 1952-02-12 United Aircraft Corp Process of joining metal parts
US2945295A (en) * 1957-12-20 1960-07-19 Westinghouse Electric Corp High temperature metallic joint
US3417460A (en) * 1959-04-13 1968-12-24 Onera (Off Nat Aerospatiale) Methods of brazing
US3025596A (en) * 1959-06-26 1962-03-20 Combustion Eng Braze bonding of concentric tubes and shells and the like

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2558026C1 (en) * 2014-03-03 2015-07-27 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Soldering of porous material with substrate

Also Published As

Publication number Publication date
FR2049448A5 (en) 1971-03-26
SE365964B (en) 1974-04-08
DE2028630C3 (en) 1975-02-27
US3713206A (en) 1973-01-30
DE2028630A1 (en) 1970-12-17
CA937107A (en) 1973-11-20
DE2028630B2 (en) 1974-07-04
CH516370A (en) 1971-12-15

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PE20 Patent expired after termination of 20 years