EP0193429A1 - Struktur, bestehend aus mehreren feuerfesten Schichten und damit versehene Wand - Google Patents

Struktur, bestehend aus mehreren feuerfesten Schichten und damit versehene Wand Download PDF

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Publication number
EP0193429A1
EP0193429A1 EP86400189A EP86400189A EP0193429A1 EP 0193429 A1 EP0193429 A1 EP 0193429A1 EP 86400189 A EP86400189 A EP 86400189A EP 86400189 A EP86400189 A EP 86400189A EP 0193429 A1 EP0193429 A1 EP 0193429A1
Authority
EP
European Patent Office
Prior art keywords
layer
refractory
wall
approximately
structure according
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.)
Granted
Application number
EP86400189A
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English (en)
French (fr)
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EP0193429B1 (de
Inventor
Didier Pineau
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.)
Airbus Group SAS
Original Assignee
Airbus Group 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 Airbus Group SAS filed Critical Airbus Group SAS
Priority to AT86400189T priority Critical patent/ATE39136T1/de
Publication of EP0193429A1 publication Critical patent/EP0193429A1/de
Application granted granted Critical
Publication of EP0193429B1 publication Critical patent/EP0193429B1/de
Expired legal-status Critical Current

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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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/04—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material
    • C23C28/042—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material including a refractory ceramic layer, e.g. refractory metal oxides, ZrO2, rare earth oxides
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21B—MANUFACTURE OF IRON OR STEEL
    • C21B7/00—Blast furnaces
    • C21B7/16—Tuyéres
    • C21B7/163—Blowpipe assembly
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/04—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material
    • C23C28/048—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material with layers graded in composition or physical properties
    • 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
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • 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
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • C23C4/11—Oxides
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24942—Structurally defined web or sheet [e.g., overall dimension, etc.] including components having same physical characteristic in differing degree
    • Y10T428/2495—Thickness [relative or absolute]
    • Y10T428/24967—Absolute thicknesses specified
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24942—Structurally defined web or sheet [e.g., overall dimension, etc.] including components having same physical characteristic in differing degree
    • Y10T428/24992—Density or compression of components

Definitions

  • the present invention relates to a multilayer refractory structure capable of withstanding for hundreds of hours at high temperatures of the order of 2000 ° C to 2500 ° C. Although not exclusively, it is particularly suitable for the production of refractory linings for pipes intended to convey flows of hot gases and it will be more particularly described below in this application.
  • the object of the present invention is therefore a refractory structure, in particular intended to form an internal coating of pipes, capable of withstanding for hundreds of hours at high temperatures of the order of 2000 ° C to 2500 ° C.
  • the present invention notably makes it possible, advantageously, to adapt new heating means, such as plasma generators, to existing industrial installations in order to increase their efficiency.
  • the multilayer refractory structure capable of withstanding for hundreds of hours at high temperatures of the order of 2000 ° C. to 2500 ° C., is remarkable in that it comprises at least two layers, the first of which, directly subjected to said high temperatures and consisting of a single or mixed metal oxide or a zirconate, has a thickness of between approximately 1 mm and 4 mm and a density of between approximately 2.2 and 4.8 and whose second layer, which serves as a support for said first layer, is of the same nature as the latter and has a thickness of between approximately 5 mm and 12 mm and a density of between approximately 2.2 and 4.2.
  • said first layer is thin and consists of a solid ceramic which is not very porous, the maximum temperature of use of which is compatible with the temperatures to be supported. In addition, it has a high chemical inertness vis-à-vis most of the hot gases transported in the pipes of industrial installations. To be able to have high purity and low porosity (and therefore a high resistance to high temperatures), this first layer can be produced by sintering or by another process making it possible to obtain such characteristics, such as for example by hot spraying. Such a hot spraying method is well known and it is for example described in the document FR-A-1 443 142. In the present case, the heat source used for the spraying of said first layer can advantageously be a generator of plasma.
  • said second layer already thermally protected by the first may be more porous than the latter (therefore of lower density).
  • said thermal resistance properties are less critical than those of the first, its production is less delicate and its thickness can therefore be greater.
  • This second layer can also be produced by sintering or by hot spraying.
  • said heat source can be a simple flame (oxyacetylene for example).
  • first and second layers being made of materials of the same kind, their expansion coefficients are little different from each other, so that the thermal expansions resulting from the high temperatures to which the structure according to the invention is subjected cannot cause stresses large enough to cause cracks, cracks or the like.
  • said multilayer refractory structure according to the invention may be intended for the protection of a metal wall, for example. example a steel pipe.
  • said structure comprises a third layer serving as a support for said second layer and made of refractory concrete having a coefficient of linear expansion between approximately 1.4 and 1.8 and a thickness at least equal to 20 mm.
  • such a third layer provides the connection between said second layer and said wall and is perfectly compatible, with regard to the expansion coefficients, both with said second refractory layer, and with the metal support wall. Since this third layer is protected by said first and second layers, its thermal resistance can be lower and enable it to withstand only temperatures of the order of 1500 ° C. without damage.
  • Said third layer may be a concrete incorporating a large proportion of alumina, for example of the order of 80%, incorporating a filler to increase its resistance to thermal shocks.
  • the thickness of the expensive concrete of the third layer may be limited, between said third layer and said wall, a fourth layer of a less expensive refractory material, for example a concrete based on silica and clay, rock wool or a similar raw material.
  • This fourth layer must guarantee mechanical resistance despite possible differences in the expansion coefficients of the third layer and of the metal wall.
  • the multilayer refractory structure When the multilayer refractory structure is intended to protect a metal wall, it can be produced gradually, layer by layer, using said wall as a support. In this case, we start by forming the possible fourth layer on said wall, then said third layer on the fourth (or directly on said wall if said fourth layer does not exist), then the second layer on the third and finally the first on the second.
  • said structure can be produced at least partially, independently of the wall, by using a mold.
  • a mold we start by forming the third layer, or possibly if it does not exist, the second in said mold, then in the first case the second on the third, and finally the first on the second. Then, the structure thus obtained is made integral with said wall by means of an intermediate refractory layer, consisting of the fourth layer, or if the latter does not exist, of the third layer.
  • the present invention also relates to a wall carrying a refractory coating capable of withstanding for hundreds of hours at high temperatures of the order of 2000 ° C to 2500 ° C.
  • a wall is for example a pipe intended to convey flows of hot gases and provided with an internal refractory lining and it is remarkable in that said coating comprises at least two layers, the first of which is directly subjected to said high temperatures and formed by a simple or mixed metal oxide or a zirconate, has a thickness of between approximately 1 mm and 4 mm and a density of between approximately 2.2 and 4.8, and including the second layer, which serves as a support for said first layer , is of the same nature as the latter and has a thickness of between approximately 5 mm and 12 mm and a density of between approximately 2.2 and 4.2.
  • At least one layer of refractory bonding material is. provided between said second layer and said wall.
  • FIG. 1 a portion of the wall 1 of a blast furnace is shown, in which a nozzle 2 for injecting blowing gas is arranged.
  • the nozzle 2 is supplied with blowing gas via a pipe 3.
  • the nozzle 2 and the pipe 3 are aligned and have the same axis X-X.
  • the blowing gas circulating in the pipe 3 is for example at a temperature of 1300 ° C, with a pressure of 1.7 bar relative and its flow rate is for example between 1000 and 6000 N m3 / h.
  • a plasma generator 4 is arranged, the nozzle 5 of which emits a jet of plasma through its outlet orifice.
  • the nozzle 5 enters the pipe 3 and its axis Y-Y makes an acute angle, for example of the order of 40 ° relative to the axis X-X of the pipe 3.
  • the axes X-X and Y-Y intersect at I.
  • the plasma jet emitted by the generator 4 is for example at a temperature of 4000 ° C., with a pressure of 2.5 bars relative and its flow rate is for example between 100 and 1000 Nm 3 / h.
  • the temperature of the mixture downstream from point 1 is of the order of 2000 ° C.
  • the temperature goes from around 1300 ° C (upstream from point I) to around 2000 ° C (downstream from point I).
  • a refractory lining 6 is provided inside said pipe 3.
  • Said first and second layers 7 and 8 can be produced according to the known method, in particular by the French patent mentioned above, consisting in projecting their molten constituent material by means of a heat source.
  • This constituent material is initially in the form of a wire, which is drawn towards said heat source.
  • the heat source can be a plasma generator.
  • the heat source can be only a simple flame.
  • the formation of the refractory lining 6 can take advantage of the presence of the wall 3, using it as a support: we then begin to form the layer 10 on the wall 3, then the layer 9 on the layer 10, the layer 8 on layer 9 and finally layer 7 on layer 8.
  • layer 9 can be produced in a mold (not shown), then layer 8 on layer 9 and layer 7 on layer 8.
  • the monolithic structure of layers 7, 8 and 9 is then made integral with the wall 3 by means of layer 10.
  • layer 10 could consist of rock wool or the like, possibly bonded to layer 9 and / or to wall 3.
  • said first and second layers 7 and 8 do not necessarily consist of zirconia. They can be, for example, calcium zirconate, magnesia or a spinel, the double oxides of which are those of magnesium, aluminum or chromium.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Mechanical Engineering (AREA)
  • Inorganic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Ceramic Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Furnace Housings, Linings, Walls, And Ceilings (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
  • Building Environments (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Laminated Bodies (AREA)
EP86400189A 1985-02-15 1986-01-29 Struktur, bestehend aus mehreren feuerfesten Schichten und damit versehene Wand Expired EP0193429B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT86400189T ATE39136T1 (de) 1985-02-15 1986-01-29 Struktur, bestehend aus mehreren feuerfesten schichten und damit versehene wand.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8502246 1985-02-15
FR8502246A FR2577471B1 (fr) 1985-02-15 1985-02-15 Structure refractaire multicouche et paroi pourvue d'une telle structure refractaire

Publications (2)

Publication Number Publication Date
EP0193429A1 true EP0193429A1 (de) 1986-09-03
EP0193429B1 EP0193429B1 (de) 1988-12-07

Family

ID=9316337

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86400189A Expired EP0193429B1 (de) 1985-02-15 1986-01-29 Struktur, bestehend aus mehreren feuerfesten Schichten und damit versehene Wand

Country Status (9)

Country Link
US (1) US4698255A (de)
EP (1) EP0193429B1 (de)
AT (1) ATE39136T1 (de)
AU (1) AU576940B2 (de)
BR (1) BR8600805A (de)
CA (1) CA1273198A (de)
DE (1) DE3661360D1 (de)
FR (1) FR2577471B1 (de)
ZA (1) ZA861027B (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1994025813A1 (en) * 1993-04-29 1994-11-10 Zaptech Corporation Method and apparatus for flame gunning

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4656071A (en) * 1984-10-29 1987-04-07 Ceramatec, Inc. Ceramic bodies having a plurality of stress zones
FR2685035B1 (fr) * 1991-12-16 1994-03-25 Aerospatiale Dispositif de montage de deux pieces en materiaux a coefficients de dilatation differents, soumises a des variations de temperature elevees.
US6165600A (en) * 1998-10-06 2000-12-26 General Electric Company Gas turbine engine component having a thermal-insulating multilayer ceramic coating
US20110033284A1 (en) * 2009-08-04 2011-02-10 United Technologies Corporation Structurally diverse thermal barrier coatings
TWI750205B (zh) 2016-08-24 2021-12-21 美商維蘇威美國公司 具有包覆的金屬層的冶金容器內襯及將熔融金屬之氧化縮減到最小的方法

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1172867A (fr) * 1956-03-09 1959-02-17 Norton Co Objet composite, et procédé pour revêtir des matières rigides afin de les protéger de l'oxydation
FR1431769A (fr) * 1965-02-01 1966-03-18 Comp Generale Electricite Procédé de protection des métaux et alliages
FR1536493A (fr) * 1966-07-22 1968-08-16 Montedison Spa Enduits protecteurs de grande résistance et procédé correspondant pour leur application sur des surfaces intérieurs de réacteurs de craquage d'hydrocarbure
US3679460A (en) * 1970-10-08 1972-07-25 Union Carbide Corp Composite wear resistant material and method of making same
FR2169864A1 (de) * 1971-12-28 1973-09-14 Uss Eng & Consult
FR2187916A1 (de) * 1972-06-13 1974-01-18 Nippon Steel Corp
GB1353383A (en) * 1970-05-11 1974-05-15 Union Carbide Corp Ceramic coated articles
US3955038A (en) * 1973-04-09 1976-05-04 Sandvik Aktiebolag Hard metal body
US4335190A (en) * 1981-01-28 1982-06-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Thermal barrier coating system having improved adhesion

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL7507155A (nl) * 1974-06-20 1975-12-23 Jenaer Glaswerk Schott & Gen Werkwijze voor de bereiding van donkerrood, door- zichtig glaskeramisch materiaal met een variabele hoge warmtespanningsfactor, meer in het bijzonder voor de vervaardiging van vuurvaste platen.
US4001029A (en) * 1975-09-26 1977-01-04 Kaiser Aluminum & Chemical Corporation Gunnable refractory composition
GB1557705A (en) * 1976-03-29 1979-12-12 Foseco Trading Ag Zircon containing compositions and ceramic bodies formed from such compositions
US4093193A (en) * 1977-06-07 1978-06-06 Electro-Nite Co. Composite high temperature protection tube
US4381716A (en) * 1978-06-05 1983-05-03 Hastings Otis Insulating apparatus and composite laminates employed therein
US4202148A (en) * 1978-06-26 1980-05-13 Industrial Insulations, Inc. Method of making thick-walled refractory fiber modules and the product formed thereby
JPS557428A (en) * 1978-06-30 1980-01-19 Yuasa Battery Co Ltd Multilayer heat insulator
SE7906404L (sv) * 1978-08-28 1980-02-29 Aikoh Co Lansror
US4248023A (en) * 1979-07-26 1981-02-03 A. P. Green Refractories Co. Insulated ceramic fiber refractory module
US4523528A (en) * 1979-12-11 1985-06-18 Transaction Security, Inc. Insulating apparatus and composite laminates employed therein
DE3137731A1 (de) * 1981-09-23 1983-04-14 Battelle-Institut E.V., 6000 Frankfurt Hochtemperatur- und thermoschockbestaendige kompaktwerkstoffe und beschichtungen

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1172867A (fr) * 1956-03-09 1959-02-17 Norton Co Objet composite, et procédé pour revêtir des matières rigides afin de les protéger de l'oxydation
FR1431769A (fr) * 1965-02-01 1966-03-18 Comp Generale Electricite Procédé de protection des métaux et alliages
FR1536493A (fr) * 1966-07-22 1968-08-16 Montedison Spa Enduits protecteurs de grande résistance et procédé correspondant pour leur application sur des surfaces intérieurs de réacteurs de craquage d'hydrocarbure
GB1353383A (en) * 1970-05-11 1974-05-15 Union Carbide Corp Ceramic coated articles
US3679460A (en) * 1970-10-08 1972-07-25 Union Carbide Corp Composite wear resistant material and method of making same
FR2169864A1 (de) * 1971-12-28 1973-09-14 Uss Eng & Consult
FR2187916A1 (de) * 1972-06-13 1974-01-18 Nippon Steel Corp
US3955038A (en) * 1973-04-09 1976-05-04 Sandvik Aktiebolag Hard metal body
US4335190A (en) * 1981-01-28 1982-06-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Thermal barrier coating system having improved adhesion

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1994025813A1 (en) * 1993-04-29 1994-11-10 Zaptech Corporation Method and apparatus for flame gunning
US5401003A (en) * 1993-04-29 1995-03-28 Zaptech Corporation Method and apparatus for flame gunning

Also Published As

Publication number Publication date
FR2577471B1 (fr) 1987-03-06
EP0193429B1 (de) 1988-12-07
ATE39136T1 (de) 1988-12-15
ZA861027B (en) 1986-09-24
US4698255A (en) 1987-10-06
AU5343686A (en) 1986-08-21
AU576940B2 (en) 1988-09-08
FR2577471A1 (fr) 1986-08-22
BR8600805A (pt) 1986-11-04
DE3661360D1 (en) 1989-01-12
CA1273198A (fr) 1990-08-28

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