US3031331A - Metal-ceramic laminated skin surface - Google Patents
Metal-ceramic laminated skin surface Download PDFInfo
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- US3031331A US3031331A US848478A US84847859A US3031331A US 3031331 A US3031331 A US 3031331A US 848478 A US848478 A US 848478A US 84847859 A US84847859 A US 84847859A US 3031331 A US3031331 A US 3031331A
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- 239000000919 ceramic Substances 0.000 title claims description 9
- 238000000576 coating method Methods 0.000 claims description 29
- 239000011248 coating agent Substances 0.000 claims description 27
- 239000000463 material Substances 0.000 claims description 15
- 239000011253 protective coating Substances 0.000 claims description 10
- 238000005260 corrosion Methods 0.000 claims description 9
- 230000007797 corrosion Effects 0.000 claims description 9
- 229910052751 metal Inorganic materials 0.000 claims description 9
- 239000002184 metal Substances 0.000 claims description 9
- 239000007789 gas Substances 0.000 claims description 8
- 239000000126 substance Substances 0.000 claims description 7
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 6
- 229910052750 molybdenum Inorganic materials 0.000 claims description 6
- 239000011733 molybdenum Substances 0.000 claims description 6
- 230000035939 shock Effects 0.000 claims description 6
- 229910052741 iridium Inorganic materials 0.000 claims description 5
- CPLXHLVBOLITMK-UHFFFAOYSA-N magnesium oxide Inorganic materials [Mg]=O CPLXHLVBOLITMK-UHFFFAOYSA-N 0.000 claims description 5
- 229910052715 tantalum Inorganic materials 0.000 claims description 5
- 229910052721 tungsten Inorganic materials 0.000 claims description 5
- 229910052725 zinc Inorganic materials 0.000 claims description 5
- 239000011701 zinc Substances 0.000 claims description 5
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 claims description 4
- 230000000694 effects Effects 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 4
- GKOZUEZYRPOHIO-UHFFFAOYSA-N iridium atom Chemical compound [Ir] GKOZUEZYRPOHIO-UHFFFAOYSA-N 0.000 claims description 4
- 239000000395 magnesium oxide Substances 0.000 claims description 4
- 239000010955 niobium Substances 0.000 claims description 4
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 claims description 4
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 4
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 4
- 239000007787 solid Substances 0.000 claims description 4
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims description 4
- 239000011135 tin Substances 0.000 claims description 4
- 229910052718 tin Inorganic materials 0.000 claims description 4
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 4
- 239000010937 tungsten Substances 0.000 claims description 4
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 claims description 3
- 238000005275 alloying Methods 0.000 claims description 3
- 229910017052 cobalt Inorganic materials 0.000 claims description 3
- 239000010941 cobalt Substances 0.000 claims description 3
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 3
- 229910000449 hafnium oxide Inorganic materials 0.000 claims description 3
- WIHZLLGSGQNAGK-UHFFFAOYSA-N hafnium(4+);oxygen(2-) Chemical compound [O-2].[O-2].[Hf+4] WIHZLLGSGQNAGK-UHFFFAOYSA-N 0.000 claims description 3
- AXZKOIWUVFPNLO-UHFFFAOYSA-N magnesium;oxygen(2-) Chemical compound [O-2].[Mg+2] AXZKOIWUVFPNLO-UHFFFAOYSA-N 0.000 claims description 3
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 claims description 3
- MTPVUVINMAGMJL-UHFFFAOYSA-N trimethyl(1,1,2,2,2-pentafluoroethyl)silane Chemical compound C[Si](C)(C)C(F)(F)C(F)(F)F MTPVUVINMAGMJL-UHFFFAOYSA-N 0.000 claims description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 5
- 238000002844 melting Methods 0.000 description 4
- 230000008018 melting Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 description 4
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 3
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 3
- 229910052796 boron Inorganic materials 0.000 description 3
- 229910052804 chromium Inorganic materials 0.000 description 3
- 239000011651 chromium Substances 0.000 description 3
- 230000003628 erosive effect Effects 0.000 description 3
- 238000005470 impregnation Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 150000002739 metals Chemical class 0.000 description 3
- 229910052759 nickel Inorganic materials 0.000 description 3
- 230000008016 vaporization Effects 0.000 description 3
- 238000009834 vaporization Methods 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- -1 furenes Chemical class 0.000 description 2
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 2
- 229910052737 gold Inorganic materials 0.000 description 2
- 239000010931 gold Substances 0.000 description 2
- 150000004820 halides Chemical class 0.000 description 2
- 229910052697 platinum Inorganic materials 0.000 description 2
- 229920001296 polysiloxane Polymers 0.000 description 2
- 229910052703 rhodium Inorganic materials 0.000 description 2
- 239000010948 rhodium Substances 0.000 description 2
- MHOVAHRLVXNVSD-UHFFFAOYSA-N rhodium atom Chemical compound [Rh] MHOVAHRLVXNVSD-UHFFFAOYSA-N 0.000 description 2
- 229910052710 silicon Inorganic materials 0.000 description 2
- 239000010703 silicon Substances 0.000 description 2
- LIVNPJMFVYWSIS-UHFFFAOYSA-N silicon monoxide Chemical compound [Si-]#[O+] LIVNPJMFVYWSIS-UHFFFAOYSA-N 0.000 description 2
- 229910052709 silver Inorganic materials 0.000 description 2
- 239000004332 silver Substances 0.000 description 2
- 238000000859 sublimation Methods 0.000 description 2
- 230000008022 sublimation Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 239000004593 Epoxy Substances 0.000 description 1
- 229910000640 Fe alloy Inorganic materials 0.000 description 1
- 229910001182 Mo alloy Inorganic materials 0.000 description 1
- 241001387976 Pera Species 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- WGLPBDUCMAPZCE-UHFFFAOYSA-N Trioxochromium Chemical compound O=[Cr](=O)=O WGLPBDUCMAPZCE-UHFFFAOYSA-N 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 238000005269 aluminizing Methods 0.000 description 1
- 229910052793 cadmium Inorganic materials 0.000 description 1
- BDOSMKKIYDKNTQ-UHFFFAOYSA-N cadmium atom Chemical compound [Cd] BDOSMKKIYDKNTQ-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000005524 ceramic coating Methods 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 229910000423 chromium oxide Inorganic materials 0.000 description 1
- 238000005254 chromizing Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 125000003700 epoxy group Chemical group 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000012212 insulator Substances 0.000 description 1
- 239000002648 laminated material Substances 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 150000001247 metal acetylides Chemical class 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005121 nitriding Methods 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 150000002989 phenols Chemical class 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000002310 reflectometry Methods 0.000 description 1
- 238000005475 siliconizing Methods 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
Classifications
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- 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
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
-
- 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
- C23C24/00—Coating starting from inorganic powder
-
- 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
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S428/00—Stock material or miscellaneous articles
- Y10S428/922—Static electricity metal bleed-off metallic stock
- Y10S428/923—Physical dimension
- Y10S428/924—Composite
-
- 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
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S428/00—Stock material or miscellaneous articles
- Y10S428/922—Static electricity metal bleed-off metallic stock
- Y10S428/923—Physical dimension
- Y10S428/924—Composite
- Y10S428/926—Thickness of individual layer 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
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S428/00—Stock material or miscellaneous articles
- Y10S428/922—Static electricity metal bleed-off metallic stock
- Y10S428/9335—Product by special process
- Y10S428/937—Sprayed metal
-
- 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
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
- Y10T428/12576—Boride, carbide or nitride component
-
- 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
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
- Y10T428/12611—Oxide-containing component
-
- 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
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
- Y10T428/12625—Free carbon containing component
-
- 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
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12632—Four or more distinct components with alternate recurrence of each type component
-
- 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
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12771—Transition metal-base component
- Y10T428/12778—Alternative base metals from diverse categories
-
- 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
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12986—Adjacent functionally defined components
-
- 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
- Y10T428/24975—No layer or component greater than 5 mils thick
Definitions
- the present invention relates to protective coatings. More particularly, it relates in one embodiment to a distinctive form of outer surface for a laminated coating which enables the latter to better resist intense heat and/ or the corrosive effects of highevelocity gases.
- each metallic layer of the laminated coating acts both as a cementing agent and as a surface to which further ceramic material can readily adhere. Furthermore, each ceramic layer performs the function of an insulator, so that the temperature of a base member protected by such a laminated coating levels oil at a figure as low as approximately 520 F. after 30 seconds exposure to a 5,000 F. blast. This is due at least in part to the inherent porosity of the material, the entrapped air not only raising the insulating quality of the coating but also increasing its thermal shock resistance.
- a multi-layer coating of the type disclosed in application Serial No. 848,477 is further treated to yield the following additional advantages:
- this is accomplished by adding vaporization or sublimation material to the laminated coating in some suitable manner as by diffusion or post-impregnation.
- an outer surface covering is chosen for the specific protective property possessed thereby, such, for example, as high heat reflectivity or degree of corrosion resistance, or its ability to control the rate of cooling of the base member following the latters elevation to relatively high temperature.
- One object of the present invention is to provide an improved form of multi-layer coating designed to protect the member upon which it is applied from heat and/or the corrosive efiects of high-velocity gases, and to provide a process for making such a coating.
- Another object of the invention is to provide a laminated form of protective coating for a base member in which layers of metallic material alternate with layers of an insulating substance having high thermal shock resistance, and then to provide an outer layer for such a laminated coating which not only protects the base member at temperatures well above the respective melting points of all of the materials used in the coatings manufacture, but also extends the life of such protection and increases the resistance of such member to the efiects of corrosive fluids and gases.
- Protection of a multi-layer metal-ceramic coating at temperatures well above the respective melting points of the substances used therein can be achieved, in a preferred embodiment of the present invention, by impregnating the coating with a vaporization or sublimation material.
- a vaporization or sublimation material examples include tin, zinc, nickel, cobalt, and certain of the halides, silicones, furenes, phenols and epoxies. They may be introduced by some preferred method such as post-impregnation or controlled dual application, according to the conditions under which the process is carried out and by the results desired. It is essential, however, that the material employed pass directly from a solid to a gaseous state without apparent liqui-fication.
- the relationship between the protective coating, the base member, and the outer surface covering of the article may be expressed by means of the following symbolic diagram Zn, Sn, Ni, 00
- Base Member A final surface coating of the nature described above protects the base member at temperatures well in excess of the respective melting points of all of the materials incorporated therein. Furthermore, if the substance employed should be a silicone, halide, or one of the metallic compounds of higher vaporization point, impregnation of the coating thereby can be carried out so that subsequent cooling of the base member will proceed along essentially predetermined lines.
- Such a coating also extends the base members life at high temperatures. This results from the fact that many B.t.u.s are needed to vaporize or sublimate the impregnating material, and obviously the B.t.-u.s so utilized take no part in heating the base member itself.
- a coating with high heat-reflective properties as the top or final layer extends the life of base members subjected to elevated temperatures from an outside source. While the particular type of reflective coating selected should, of course, be determined by the character of the environmental conditions and by the magnitude of the temperatures to be encountered, it has been found that such materials as aluminum, gold, silver, platinum and rhodium (protected by silicon monoxide) are especially suitable for this purpose.
- a. highly emissive top'coating (such, for example, as chromium oxide and certain carbides) can reduce the heat caused by atmospheric friction on re-entry.
- a base member having a protective coating thereon said coating being designed to provide high corrosion resistance for the base member and to withstand the effects of heat and/or high-velocity gases, said coating being made up of individually flame-sprayed layers of a metal each layer having a thickness not exceeding approximately .0025 inch, such metal being selected from a group consisting of boron, columbium, iridium, molybdenum, tantalum and tungsten alternating with individually flamesprayed layers each layer not exceeding approximately .005 inch in thickness of a ceramic having high thermal shock resistance and selected from a group consisting of aluminum oxide, magnesium oxide, hafnium oxide, silicon carbide and titanium carbide, said protective coating possessing as an outer surface covering a material selected from a group consisting of zinc, tin, nickel and cobalt, each of the said flame-sprayed layers possessing a porosity which permits a high degree of coherence and adherence to adjacent layers without .the necessity of baking the ceramic substance or of bonding the respective layers as by alloying, the
- a base member having a protective coating thereon said coating being designed to provide high corrosion resistance for the base member and to withstand the effects of heat and/or high-velocity gases, said coating being made up of individually flame-sprayed layers of a metal each layer having a thickness not exceeding approximately .0025 inch, such metal being sclected from a group consisting of boron, columbium, iridium, molybdenum, tantalum and tungsten alternating with individually flame-sprayed layers each layer not exceeding approximately .005 inch in thickness of a ceramic selected from a group consisting of aluminum oxide, magnesium oxide, hafnium oxide, silicon carbide and titanium carbide, said protective coating possessing as an outer surface covering a high heat-reflective material selected from a group consisting of aluminum, gold, silver, platinum and rhodium, each of the said flame-sprayed layers possessing a porosity which permits a high degree of coherence and adherence to adjacent layers without the necessity of baking the ceramic substance or of bonding the respective layers as
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Coating By Spraying Or Casting (AREA)
Description
United States Patent METAL-CERAMIC LAMINATED SKIN SURFACE Wllllfilll L. Aves, Jr., Arlington, and Robert A. Hart,
Hurst, Tex., assignors, by mesne assignments, to the United States of America as represented by the Secretary of the Navy No Drawing. Filed Oct. 23, 1959, Ser. No. 848,478
2 Claims. (Cl. 117-46) The present invention relates to protective coatings. More particularly, it relates in one embodiment to a distinctive form of outer surface for a laminated coating which enables the latter to better resist intense heat and/ or the corrosive effects of highevelocity gases.
In a co-pending US. patent application of William L. Aves, Serial No. 848,477, filed concurrently herewith, there is disclosed a protective coating which combines the erosion resistance and excellent bonding properties of a metal such as molybdenum with the good thermal shock resistance and insulating properties of a ceramic such as aluminum oxide. These two substances are applied to a base member as a multi-layer coating, of a total thickness and with a number of laminations governed by the particular environmental conditions to be encountered. Such a multi-layer coating possesses excellent erosive, thermal shock and temperature resistance when employed to contain a rocket motor blast, for example, where temperatures in the neighborhood of 5,000 F. are developed in conjunction with high-velocity gases. By utilizing the invention set forth in this co-pending application, it is possible to work within the strict space, weight and fabrication limitations imposed by the design requirements of many types of guided missiles and other superand hyper-sonic space flight vehicles.
One important feature contributing to the satisfactory results obtained from the material set forth in the copending application above referred to is that each metallic layer of the laminated coating acts both as a cementing agent and as a surface to which further ceramic material can readily adhere. Furthermore, each ceramic layer performs the function of an insulator, so that the temperature of a base member protected by such a laminated coating levels oil at a figure as low as approximately 520 F. after 30 seconds exposure to a 5,000 F. blast. This is due at least in part to the inherent porosity of the material, the entrapped air not only raising the insulating quality of the coating but also increasing its thermal shock resistance.
It has been indicated in the mentioned co-pending application that relatively high-melting-point metals are preferred for the multi-layer coating, some representative examples being boron, chromium, iridium, molybdenum, tantalum, and tungsten. It has now been found that the properties of a laminated material such as set forth in the co-pending application can be materially improved in several important respects without changing the basic character of the coating or the method by which it is applied.
In accordance with a feature of the present invention, a multi-layer coating of the type disclosed in application Serial No. 848,477 is further treated to yield the following additional advantages:
(1) Protection at temperatures well above the respective melting points of all of the materials used in the coatings fabrication.
(2) Extension of the period during which protection is ailorded at high temperatures.
(3) Increased corrosion resistance for long shelf life.
In a broad sense, this is accomplished by adding vaporization or sublimation material to the laminated coating in some suitable manner as by diffusion or post-impregnation. Such an outer surface covering is chosen for the specific protective property possessed thereby, such, for example, as high heat reflectivity or degree of corrosion resistance, or its ability to control the rate of cooling of the base member following the latters elevation to relatively high temperature.
One object of the present invention, therefore, is to provide an improved form of multi-layer coating designed to protect the member upon which it is applied from heat and/or the corrosive efiects of high-velocity gases, and to provide a process for making such a coating.
Another object of the invention is to provide a laminated form of protective coating for a base member in which layers of metallic material alternate with layers of an insulating substance having high thermal shock resistance, and then to provide an outer layer for such a laminated coating which not only protects the base member at temperatures well above the respective melting points of all of the materials used in the coatings manufacture, but also extends the life of such protection and increases the resistance of such member to the efiects of corrosive fluids and gases.
Other objects and many of the attendant advantages of the invention will be readily appreciated as the latter becomes better understood by reference to the following detailed description.
Protection of a multi-layer metal-ceramic coating at temperatures well above the respective melting points of the substances used therein can be achieved, in a preferred embodiment of the present invention, by impregnating the coating with a vaporization or sublimation material. Examples of such a material include tin, zinc, nickel, cobalt, and certain of the halides, silicones, furenes, phenols and epoxies. They may be introduced by some preferred method such as post-impregnation or controlled dual application, according to the conditions under which the process is carried out and by the results desired. It is essential, however, that the material employed pass directly from a solid to a gaseous state without apparent liqui-fication.
In a preferred embodiment of the invention, the relationship between the protective coating, the base member, and the outer surface covering of the article may be expressed by means of the following symbolic diagram Zn, Sn, Ni, 00
A1203, MgO, HfOz, SiC, TiO
B, Cb, Ir, Mo, Ta, W
Base Member A final surface coating of the nature described above protects the base member at temperatures well in excess of the respective melting points of all of the materials incorporated therein. Furthermore, if the substance employed should be a silicone, halide, or one of the metallic compounds of higher vaporization point, impregnation of the coating thereby can be carried out so that subsequent cooling of the base member will proceed along essentially predetermined lines.
Such a coating also extends the base members life at high temperatures. This results from the fact that many B.t.u.s are needed to vaporize or sublimate the impregnating material, and obviously the B.t.-u.s so utilized take no part in heating the base member itself.
Finally, corrosion protection essential for long shelf life can be readily attained. Metals such as zinc and cadmium ofier such corrosion resistance to most base materials in a sacrificial manner, and they need not be dense to protect the latter under the usual storage conditions. Chromizing, siliconizing, aluminizing (and in some cases nitriding) of the laminated coating also pro vides a high degree of corrosion resistance. When chromium and silicon are diffused into the surface of molybdenum or ferrous alloys, both element-s greatly enhance the metals resistance to corrosion at all temperatures in both oxidizing and reducing environments. Furthermore, chromium, silicon, nitrogen, and in some cases carbon will increase substantially the resistance of the metallic layers to hot gas erosion and particle abrasion.
Employing a coating with high heat-reflective properties as the top or final layer extends the life of base members subjected to elevated temperatures from an outside source. While the particular type of reflective coating selected should, of course, be determined by the character of the environmental conditions and by the magnitude of the temperatures to be encountered, it has been found that such materials as aluminum, gold, silver, platinum and rhodium (protected by silicon monoxide) are especially suitable for this purpose.
It should be noted that in the case of space vehicles, a. highly emissive top'coating (such, for example, as chromium oxide and certain carbides) can reduce the heat caused by atmospheric friction on re-entry.
Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.
I claim:
1. A base member having a protective coating thereon, said coating being designed to provide high corrosion resistance for the base member and to withstand the effects of heat and/or high-velocity gases, said coating being made up of individually flame-sprayed layers of a metal each layer having a thickness not exceeding approximately .0025 inch, such metal being selected from a group consisting of boron, columbium, iridium, molybdenum, tantalum and tungsten alternating with individually flamesprayed layers each layer not exceeding approximately .005 inch in thickness of a ceramic having high thermal shock resistance and selected from a group consisting of aluminum oxide, magnesium oxide, hafnium oxide, silicon carbide and titanium carbide, said protective coating possessing as an outer surface covering a material selected from a group consisting of zinc, tin, nickel and cobalt, each of the said flame-sprayed layers possessing a porosity which permits a high degree of coherence and adherence to adjacent layers without .the necessity of baking the ceramic substance or of bonding the respective layers as by alloying, the said outer surface covering acting to sublimate in that upon heating it passes directly from a solid to a gaseous state Without apparent liquification.
2. A base member having a protective coating thereon, said coating being designed to provide high corrosion resistance for the base member and to withstand the effects of heat and/or high-velocity gases, said coating being made up of individually flame-sprayed layers of a metal each layer having a thickness not exceeding approximately .0025 inch, such metal being sclected from a group consisting of boron, columbium, iridium, molybdenum, tantalum and tungsten alternating with individually flame-sprayed layers each layer not exceeding approximately .005 inch in thickness of a ceramic selected from a group consisting of aluminum oxide, magnesium oxide, hafnium oxide, silicon carbide and titanium carbide, said protective coating possessing as an outer surface covering a high heat-reflective material selected from a group consisting of aluminum, gold, silver, platinum and rhodium, each of the said flame-sprayed layers possessing a porosity which permits a high degree of coherence and adherence to adjacent layers without the necessity of baking the ceramic substance or of bonding the respective layers as by alloying, the said outer surface covering acting to sublimate in that upon heating it passes directly from a solid to a gaseous state without apparent liquification.
References Cited in the file of this patent UNITED STATES PATENTS 2,683,305 Goetzel July 13, 1954 2,696,662 Le Sech Dec. 14, 1954 2,697,670 Gaudenzi Dec. 21, 1954 2,763,919 Kempe et a1. Sept. 29, 1956 2,775,531 Montgomery et al. Dec. 25, 1956 2,823,139 Schulze et al Feb. 11, 1958 2,839,292 Bellamy June 17, 1958 2,903,375 Peras Sept. 8, 1959
Claims (1)
1. A BASE MEMBER HAVING A PROTECTIVE COATING THEREON, SAID COATING BEING DESIGNED TO PROVIDE HIGH CORROSION RESISTANCE FOR THE BASE MEMBER AND TO WITHSTAND THE EFFECTS OF HEAT AND/OR HIGH-VELOCITY GASES, SAID COATING BEING MADE UP OF INDIVIDUALLY FLAME-SPRAYED LAYERS OF A METAL EACH LAYER HAVING A THICKNESS NOT EXCEEDING APPROXIMATELY .0025 INCH, SUCH METAL BEING SELECTED FROM A GROUP CONSISTING OF BORON, COLUMBIUM, IRIDIUM, MOLYBDENUM, TANTALUM AND TUNGSTEN ALTERNATING WITH INDIVIDUALLY FLAMESPRAYED LAYERS EACH LAYER NOT EXCEEDING APPROXIMATELY .005 INCH IN THICKNESS OF A CERAMICHAVING HIGH THERMAL SHOCK RESISTANCE AND SELECTED FROM A GROUP CONSISTING OF ALUMINUM OXIDE, MAGNESIUM OXIDE, HAFNIUM OXIDE, SILICON CARBIDE AND TITANIUM CARBIDE, SAID PROTECTIVE COATING POSSESSING AS AN OUTER SURFACE COVERING A MATERIAL SELECTED FROM A GROUP CONSISTING OF ZINC, TIN, NICKEL AND COBALT, EACH OF THE SAID FLAME-SPRAYED LAYERS POSSESSING A POROSITY WHICH PERMITS A HIGH DEGREE OF COHERENCE AND ADHERENCE TO ADJACENT LAYERS WITHOUT THE NECESSITY OF BAKING THE CERAMIC SUBSTANCE OR OF BONDING THE RESPECTIVE LAYERS AS BY ALLOYING, THE SAID OUTER SURFACE COVERING ACTING TO SUBLIMATE IN THAT UPON HEATING IT PASSES DIRECTLY FROM A SOLID TO A GASEOUS STATE WITHOUT APPARENT LIQUIFICATION.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US848478A US3031331A (en) | 1959-10-23 | 1959-10-23 | Metal-ceramic laminated skin surface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US848478A US3031331A (en) | 1959-10-23 | 1959-10-23 | Metal-ceramic laminated skin surface |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3031331A true US3031331A (en) | 1962-04-24 |
Family
ID=25303385
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US848478A Expired - Lifetime US3031331A (en) | 1959-10-23 | 1959-10-23 | Metal-ceramic laminated skin surface |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US3031331A (en) |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3205199A (en) * | 1961-12-28 | 1965-09-07 | Monsanto Co | Polymers from bis-phenolamides |
| US3243313A (en) * | 1960-04-25 | 1966-03-29 | Ling Temco Vought Inc | Heat-resistant article |
| US3293064A (en) * | 1962-07-23 | 1966-12-20 | Ling Temco Vought Inc | Method of making heat resistant article |
| US3340084A (en) * | 1959-02-19 | 1967-09-05 | Gen Electric | Method for producing controlled density heterogeneous material |
| US3560006A (en) * | 1967-10-04 | 1971-02-02 | Riken Piston Ring Ind Co Ltd | Piston rings |
| US3841151A (en) * | 1970-03-17 | 1974-10-15 | J Marten | Coating for vehicle test bed rollers |
| US3849175A (en) * | 1971-01-26 | 1974-11-19 | Miele & Cie | Method for coating steel parts with enamel |
| US3857682A (en) * | 1973-02-07 | 1974-12-31 | G White | High temperature resistive and dry lubricated film surfaces |
| JPS5097608A (en) * | 1973-12-26 | 1975-08-02 | ||
| US3967017A (en) * | 1970-03-17 | 1976-06-29 | John Anthony Marten | Method of coating a vehicle test bed rollers |
| EP0075228A3 (en) * | 1981-09-23 | 1984-04-25 | Battelle-Institut e.V. | Heat insulating ceramic coating having a resistance to high temperatures and to thermal shocks |
| USRE32110E (en) * | 1971-05-26 | 1986-04-15 | General Electric Co. | Aluminum oxide coated cemented carbide product |
| USRE33876E (en) * | 1975-09-11 | 1992-04-07 | United Technologies Corporation | Thermal barrier coating for nickel and cobalt base super alloys |
| US5169674A (en) * | 1990-10-23 | 1992-12-08 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method of applying a thermal barrier coating system to a substrate |
| EP0992614A1 (en) * | 1998-10-02 | 2000-04-12 | Asea Brown Boveri AG | Coatings for turbine components |
| US6652987B2 (en) * | 2001-07-06 | 2003-11-25 | United Technologies Corporation | Reflective coatings to reduce radiation heat transfer |
| US10406774B2 (en) * | 2016-10-17 | 2019-09-10 | U.S. Department Of Energy | Diffusion bonding of silicon carbide using iridium and hermetic silicon carbide-iridium bonds |
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| US2696662A (en) * | 1947-10-27 | 1954-12-14 | Snecma | Member to be used in thermic engines |
| US2697670A (en) * | 1952-07-28 | 1954-12-21 | Bbc Brown Boveri & Cie | Ceramic coated chromium steel |
| US2763919A (en) * | 1950-07-28 | 1956-09-25 | Thompson Prod Inc | Coated refractory body |
| US2775531A (en) * | 1949-05-10 | 1956-12-25 | Univ Ohio State Res Found | Method of coating a metal surface |
| US2823139A (en) * | 1952-05-23 | 1958-02-11 | Ver Deutsche Metallwerke Ag | Method of increasing the scaling resistance of metallic objects |
| US2839292A (en) * | 1954-08-09 | 1958-06-17 | Harry T Bellamy | Refractory reservoir for aluminum |
| US2903375A (en) * | 1956-08-08 | 1959-09-08 | Renault | Method of coating a mould for use in a foundry |
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| US2696662A (en) * | 1947-10-27 | 1954-12-14 | Snecma | Member to be used in thermic engines |
| US2775531A (en) * | 1949-05-10 | 1956-12-25 | Univ Ohio State Res Found | Method of coating a metal surface |
| US2683305A (en) * | 1949-07-15 | 1954-07-13 | Sintercast Corp | Molybdenum coated article and method of making |
| US2763919A (en) * | 1950-07-28 | 1956-09-25 | Thompson Prod Inc | Coated refractory body |
| US2823139A (en) * | 1952-05-23 | 1958-02-11 | Ver Deutsche Metallwerke Ag | Method of increasing the scaling resistance of metallic objects |
| US2697670A (en) * | 1952-07-28 | 1954-12-21 | Bbc Brown Boveri & Cie | Ceramic coated chromium steel |
| US2839292A (en) * | 1954-08-09 | 1958-06-17 | Harry T Bellamy | Refractory reservoir for aluminum |
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Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3340084A (en) * | 1959-02-19 | 1967-09-05 | Gen Electric | Method for producing controlled density heterogeneous material |
| US3243313A (en) * | 1960-04-25 | 1966-03-29 | Ling Temco Vought Inc | Heat-resistant article |
| US3205199A (en) * | 1961-12-28 | 1965-09-07 | Monsanto Co | Polymers from bis-phenolamides |
| US3293064A (en) * | 1962-07-23 | 1966-12-20 | Ling Temco Vought Inc | Method of making heat resistant article |
| US3560006A (en) * | 1967-10-04 | 1971-02-02 | Riken Piston Ring Ind Co Ltd | Piston rings |
| US3967017A (en) * | 1970-03-17 | 1976-06-29 | John Anthony Marten | Method of coating a vehicle test bed rollers |
| US3841151A (en) * | 1970-03-17 | 1974-10-15 | J Marten | Coating for vehicle test bed rollers |
| US3849175A (en) * | 1971-01-26 | 1974-11-19 | Miele & Cie | Method for coating steel parts with enamel |
| USRE32110E (en) * | 1971-05-26 | 1986-04-15 | General Electric Co. | Aluminum oxide coated cemented carbide product |
| US3857682A (en) * | 1973-02-07 | 1974-12-31 | G White | High temperature resistive and dry lubricated film surfaces |
| JPS5097608A (en) * | 1973-12-26 | 1975-08-02 | ||
| USRE33876E (en) * | 1975-09-11 | 1992-04-07 | United Technologies Corporation | Thermal barrier coating for nickel and cobalt base super alloys |
| EP0075228A3 (en) * | 1981-09-23 | 1984-04-25 | Battelle-Institut e.V. | Heat insulating ceramic coating having a resistance to high temperatures and to thermal shocks |
| US4471017A (en) * | 1981-09-23 | 1984-09-11 | Battelle-Institut E.V. | High-temperature and thermal-shock-resistant thermally insulating coatings on the basis of ceramic materials |
| US5169674A (en) * | 1990-10-23 | 1992-12-08 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method of applying a thermal barrier coating system to a substrate |
| EP0992614A1 (en) * | 1998-10-02 | 2000-04-12 | Asea Brown Boveri AG | Coatings for turbine components |
| US6652987B2 (en) * | 2001-07-06 | 2003-11-25 | United Technologies Corporation | Reflective coatings to reduce radiation heat transfer |
| SG102661A1 (en) * | 2001-07-06 | 2004-03-26 | United Technologies Corp | Reflective coatings to reduce radiation heat transfer |
| US10406774B2 (en) * | 2016-10-17 | 2019-09-10 | U.S. Department Of Energy | Diffusion bonding of silicon carbide using iridium and hermetic silicon carbide-iridium bonds |
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