US2922721A - Method for coating and infiltrating a porous refractory body - Google Patents
Method for coating and infiltrating a porous refractory body Download PDFInfo
- Publication number
- US2922721A US2922721A US576230A US57623056A US2922721A US 2922721 A US2922721 A US 2922721A US 576230 A US576230 A US 576230A US 57623056 A US57623056 A US 57623056A US 2922721 A US2922721 A US 2922721A
- Authority
- US
- United States
- Prior art keywords
- metal
- skeleton
- coating
- infiltration
- primary
- 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 - Lifetime
Links
- 238000000576 coating method Methods 0.000 title claims description 99
- 239000011248 coating agent Substances 0.000 title claims description 96
- 238000000034 method Methods 0.000 title claims description 27
- 229910052751 metal Inorganic materials 0.000 claims description 120
- 239000002184 metal Substances 0.000 claims description 120
- 239000000463 material Substances 0.000 claims description 45
- 238000001764 infiltration Methods 0.000 claims description 43
- 230000008595 infiltration Effects 0.000 claims description 43
- 238000002844 melting Methods 0.000 claims description 29
- 230000008018 melting Effects 0.000 claims description 29
- 150000001875 compounds Chemical class 0.000 claims description 13
- 238000005275 alloying Methods 0.000 claims description 6
- 230000008093 supporting effect Effects 0.000 claims description 6
- 230000001427 coherent effect Effects 0.000 claims description 5
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 69
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 35
- 229910052759 nickel Inorganic materials 0.000 description 31
- 229910045601 alloy Inorganic materials 0.000 description 28
- 239000000956 alloy Substances 0.000 description 28
- 239000000843 powder Substances 0.000 description 25
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 20
- 229910052804 chromium Inorganic materials 0.000 description 20
- 239000011651 chromium Substances 0.000 description 20
- 239000002131 composite material Substances 0.000 description 20
- 229910052742 iron Inorganic materials 0.000 description 17
- 239000011230 binding agent Substances 0.000 description 15
- 150000002739 metals Chemical class 0.000 description 13
- 239000011148 porous material Substances 0.000 description 12
- 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 description 12
- 238000005507 spraying Methods 0.000 description 11
- 239000010941 cobalt Substances 0.000 description 10
- 229910017052 cobalt Inorganic materials 0.000 description 10
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 10
- 239000003870 refractory metal Substances 0.000 description 10
- 238000004519 manufacturing process Methods 0.000 description 9
- 238000010438 heat treatment Methods 0.000 description 8
- 239000000203 mixture Substances 0.000 description 8
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 8
- 229910052721 tungsten Inorganic materials 0.000 description 8
- 239000010937 tungsten Substances 0.000 description 8
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 7
- 150000002736 metal compounds Chemical class 0.000 description 7
- 229910052750 molybdenum Inorganic materials 0.000 description 7
- 239000011733 molybdenum Substances 0.000 description 7
- 235000016768 molybdenum Nutrition 0.000 description 7
- 229920005989 resin Polymers 0.000 description 7
- 239000011347 resin Substances 0.000 description 7
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 6
- 229910052782 aluminium Inorganic materials 0.000 description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 6
- 238000005253 cladding Methods 0.000 description 6
- 238000005245 sintering Methods 0.000 description 6
- 229910052719 titanium Inorganic materials 0.000 description 6
- 239000010936 titanium Substances 0.000 description 6
- 239000010955 niobium Substances 0.000 description 5
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 5
- 239000002245 particle Substances 0.000 description 5
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 4
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 description 4
- 239000007788 liquid Substances 0.000 description 4
- 230000003647 oxidation Effects 0.000 description 4
- 238000007254 oxidation reaction Methods 0.000 description 4
- 229920001568 phenolic resin Polymers 0.000 description 4
- 239000000047 product Substances 0.000 description 4
- 239000000725 suspension Substances 0.000 description 4
- ZCUFMDLYAMJYST-UHFFFAOYSA-N thorium dioxide Chemical compound O=[Th]=O ZCUFMDLYAMJYST-UHFFFAOYSA-N 0.000 description 4
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 3
- 239000000470 constituent Substances 0.000 description 3
- 230000007797 corrosion Effects 0.000 description 3
- 238000005260 corrosion Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 238000007598 dipping method Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 230000014509 gene expression Effects 0.000 description 3
- 150000001247 metal acetylides Chemical class 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000035939 shock Effects 0.000 description 3
- 229910052715 tantalum Inorganic materials 0.000 description 3
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 229910052726 zirconium Inorganic materials 0.000 description 3
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 description 2
- LTPBRCUWZOMYOC-UHFFFAOYSA-N Beryllium oxide Chemical compound O=[Be] LTPBRCUWZOMYOC-UHFFFAOYSA-N 0.000 description 2
- 239000001856 Ethyl cellulose Substances 0.000 description 2
- ZZSNKZQZMQGXPY-UHFFFAOYSA-N Ethyl cellulose Chemical compound CCOCC1OC(OC)C(OCC)C(OCC)C1OC1C(O)C(O)C(OC)C(CO)O1 ZZSNKZQZMQGXPY-UHFFFAOYSA-N 0.000 description 2
- 230000001464 adherent effect Effects 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- -1 columbinm Chemical compound 0.000 description 2
- 230000006866 deterioration Effects 0.000 description 2
- GNTDGMZSJNCJKK-UHFFFAOYSA-N divanadium pentaoxide Chemical compound O=[V](=O)O[V](=O)=O GNTDGMZSJNCJKK-UHFFFAOYSA-N 0.000 description 2
- 230000003628 erosive effect Effects 0.000 description 2
- 229920001249 ethyl cellulose Polymers 0.000 description 2
- 235000019325 ethyl cellulose Nutrition 0.000 description 2
- SLGWESQGEUXWJQ-UHFFFAOYSA-N formaldehyde;phenol Chemical compound O=C.OC1=CC=CC=C1 SLGWESQGEUXWJQ-UHFFFAOYSA-N 0.000 description 2
- 229910002804 graphite Inorganic materials 0.000 description 2
- 239000010439 graphite Substances 0.000 description 2
- 238000000227 grinding Methods 0.000 description 2
- 230000006698 induction Effects 0.000 description 2
- 239000007791 liquid phase Substances 0.000 description 2
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 2
- QSHDDOUJBYECFT-UHFFFAOYSA-N mercury Chemical compound [Hg] QSHDDOUJBYECFT-UHFFFAOYSA-N 0.000 description 2
- 229910052753 mercury Inorganic materials 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000000025 natural resin Substances 0.000 description 2
- 229910052758 niobium Inorganic materials 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- 238000010422 painting Methods 0.000 description 2
- 239000005011 phenolic resin Substances 0.000 description 2
- 239000012255 powdered metal Substances 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 239000011253 protective coating Substances 0.000 description 2
- 239000002904 solvent Substances 0.000 description 2
- 229910052720 vanadium Inorganic materials 0.000 description 2
- GPPXJZIENCGNKB-UHFFFAOYSA-N vanadium Chemical compound [V]#[V] GPPXJZIENCGNKB-UHFFFAOYSA-N 0.000 description 2
- ZSLUVFAKFWKJRC-IGMARMGPSA-N 232Th Chemical compound [232Th] ZSLUVFAKFWKJRC-IGMARMGPSA-N 0.000 description 1
- 229910052580 B4C Inorganic materials 0.000 description 1
- 241001058146 Erium Species 0.000 description 1
- PMVSDNDAUGGCCE-TYYBGVCCSA-L Ferrous fumarate Chemical group [Fe+2].[O-]C(=O)\C=C\C([O-])=O PMVSDNDAUGGCCE-TYYBGVCCSA-L 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 229910052776 Thorium Inorganic materials 0.000 description 1
- 229910026551 ZrC Inorganic materials 0.000 description 1
- OTCHGXYCWNXDOA-UHFFFAOYSA-N [C].[Zr] Chemical compound [C].[Zr] OTCHGXYCWNXDOA-UHFFFAOYSA-N 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 238000003483 aging Methods 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 229910052790 beryllium Inorganic materials 0.000 description 1
- ATBAMAFKBVZNFJ-UHFFFAOYSA-N beryllium atom Chemical compound [Be] ATBAMAFKBVZNFJ-UHFFFAOYSA-N 0.000 description 1
- INAHAJYZKVIDIZ-UHFFFAOYSA-N boron carbide Chemical compound B12B3B4C32B41 INAHAJYZKVIDIZ-UHFFFAOYSA-N 0.000 description 1
- 239000011449 brick Substances 0.000 description 1
- 239000001913 cellulose Substances 0.000 description 1
- 229920002678 cellulose Polymers 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- UFGZSIPAQKLCGR-UHFFFAOYSA-N chromium carbide Chemical compound [Cr]#C[Cr]C#[Cr] UFGZSIPAQKLCGR-UHFFFAOYSA-N 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000002939 deleterious effect Effects 0.000 description 1
- 229910003460 diamond Inorganic materials 0.000 description 1
- 239000010432 diamond Substances 0.000 description 1
- 238000001035 drying Methods 0.000 description 1
- 238000011049 filling Methods 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 239000012467 final product Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- WHJFNYXPKGDKBB-UHFFFAOYSA-N hafnium;methane Chemical compound C.[Hf] WHJFNYXPKGDKBB-UHFFFAOYSA-N 0.000 description 1
- 238000009998 heat setting Methods 0.000 description 1
- 238000007731 hot pressing Methods 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 238000009863 impact test Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 150000002500 ions Chemical class 0.000 description 1
- 150000002611 lead compounds Chemical class 0.000 description 1
- 229910000464 lead oxide Inorganic materials 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 150000004767 nitrides Chemical class 0.000 description 1
- YEXPOXQUZXUXJW-UHFFFAOYSA-N oxolead Chemical compound [Pb]=O YEXPOXQUZXUXJW-UHFFFAOYSA-N 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 239000012071 phase Substances 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 229910010271 silicon carbide Inorganic materials 0.000 description 1
- 239000002002 slurry Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 229910003470 tongbaite Inorganic materials 0.000 description 1
- UONOETXJSWQNOL-UHFFFAOYSA-N tungsten carbide Chemical compound [W+]#[C-] UONOETXJSWQNOL-UHFFFAOYSA-N 0.000 description 1
- 150000003682 vanadium compounds Chemical class 0.000 description 1
- 239000002966 varnish Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
- B22F3/26—Impregnating
-
- 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
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
- Y10T29/49337—Composite blade
-
- 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
- Y10T428/12007—Component of composite having metal continuous phase interengaged with nonmetal continuous phase
Definitions
- FIG. IB is a diagrammatic representation of FIG. IB.
- FIG. IA is a diagrammatic representation of FIG. IA.
- the present invention.- relates to coated refractory metal compound composites, and more particularly to a method for obtaining adherent metal coatings upon refractory metal carbide materials characterized by improved metallurgical'quality, improved resistance to oxidation, improved resistance to thermal and mechanical impact or shock, and generally improved properties at elevated temperatures.
- a refractory carbide material consisting of about equal proportions by weight of titaniurn carbide and an alloy of the so-called super alloy type usually containing nickel or cobalt as major alloying constituents, and chromium, tungsten, molybdenum, titanium, iron, aluminum, etc. as other alloying constituents.
- This material could either be prepared by the well-known cementing method employed in the powder metallurgical production of carbide tools, that is by mixing refractory carbide particles with a given amount of binder metal, for example nickel or cobalt or an alloy based on these metals, followed by pressing the mixture into a desired shape and thereafter sintering it; or the material could be produced by forming a sintered porous skeleton comprising a refractorymetal carbide and thereafter infiltrating it with a heat resistant metal or alloy to form a strong composite structure. The latter method was preferred over the former as it enabled the consistent production of superior materials.
- binder metal for example nickel or cobalt or an alloy based on these metals
- thermal elements produced by infiltration comprising about 50% by Weight of titanium carbide and about 50% by weight of a nickel base alloy containing about 13% 2,922,721 Patented Jan. 26, 1960 to 15% chromium and about 6% to 7% iron as alloying constituents could withstand a stress of about 42,000 p.s.i. at a temperature of about 875 C. for 100 hours in an oxidizing atmosphere before it would rupture. It was, also found that the same material at 985 C. would withstand a stress of 16,000 psi. before it would rupture after 100 hours of testing. At the lower temperature, the thermal elements after testing exhibited an elongation of the order of about 2% to 3% and an impact strength of about 10 ft. lbs. for a Charpy-type unnotched bar, while at the higher temperature they exhibited an elongation of about 4% to 8% and an impact strength of about 6.5 ft. lbs.
- the protective coating could be achieved during infiltration, of a porous skeleton body by first producingthe porous body (.e.g. a turbine blade) slightly undersized, centering it in the cavity of a mold comprising a substantially inert refractory, the cavity conforming in shape to but being slightly larger than the body, infiltrating the body and allowing for suificient excess infiltrant to fill the space between the blade and the mold walls to provide for the coating.
- the porous body .e.g. a turbine blade
- Coatings of controlled thickness produced in this manner markedly improve the properties of turbine buckets, providing extreme care was taken in indexing the skeleton in the mold cavity to insure obtaining the desired coating dimensions and also provided the heating cycle was carefully controlled to minimize non-uniformshrinkage or warpage of the inert refractory. Also care had to be taken to control the infiltration process so that the infiltrant'metal during infiltration did not gush down the sides of the skeleton and erode its surface.
- the present invention differs over the'foregoing concepts m that an entirely new approach is utilized for coating metal compound composites produced by infiltratron. It is particularly applicable to the production of coated products having a tapered configuration, for example, fluid guiding members, such as turbine buckets or nozzle .vanes, characterized by a thick portion near the lead ng edge tapering smoothly and arcuately to a relatively thin trailing edge portion.
- fluid guiding members such as turbine buckets or nozzle .vanes
- tapered bodies area little more ditficult to coat substantially uniformly, particularly when the coating is carried out simultaneously with infiltration in amold.
- Another important advantage is that the improved method also minimizes erosion of the skeleton surface during the combined infiltration and. coating step. It is the object of the invention to provide a combined infiltration and coating process for producing coated infiltrated composites comprising a high melting point re fractory metal compound material, for example titanium carbide.
- Another object is to provide a method for producing a coating of improved metallurgical quality on infiltrated refractorymetal compound materials.
- Figs. 1A to 1F depict inflow sheet arrangement the steps and materials which may be employed in carrying out an embodiment of the invention
- Fig. 2 illustrates an expanded view of the boundary conditions which prevail in an embodiment of the invention between the mold and the skeleton prior to in filtration in the production of a coated body;
- Fig. 3 is. similar-to Fig. 2 but shows the penetration of the infiltrant metal into the interstices of the skeleton and the" primary coating by infiltration;
- Flg. 4 is a representation of a photomicrograph at 250' magnificationof a transverse section of the final productv showing a relatively sharp line of demarcation between the coating and the base material.
- the porous skeleton body to be infiltrated is provided with a foundation layer or primary coating of a metal alloyable with the infiltrant metal, the thickness of the primarymetal coating determining to a large extent thedesired thickness of the final coating.
- the primary coating of the composite skeleton also serves mold comprises the porous skeleton on one side, a primary metal coating of desired thickness on the surface thereof and on the other side of the primary coating a back-up support of substantially inert refractory oxide material.
- the composite skeleton is subjected to infiltration in the usual manner with a matrixforming metal which flows through the skeleton filling u'p'the pores and on out through the surface thereof merging and al-' loying with the primary coating.
- the flowing of the molten infiltrant metal but of the skeleton surface and into the primary coating is referred to as exfiltration and the use of this and equivalent expressions hereinafter is meant to cover the aforementioned phenomenon.
- the primary coating metal employed in carrying out the invention should be one which will combine with the infiltrant to form a coating having the desired properties, i.e. having resistance to corrosion, erosion and oxidation and adequate ductility, hardness, etc.
- the metal should have a melting point higher than the melting point of the matrix-forming infiltrant metal so that the foundation layer provided by the primarycoating will not be prematurely disrupted before completion of the exfiltration step.
- the melting point of the coating metal should be atleast 50 degrees higher than the melting point of the infiltrant metal in the pores of the skeleton.
- the primary metal coat should not combine with the material of the skeleton to form a liquid phase at a temperature below the melting point of the matrix-forming infiltrant metal.
- a suspension of the metal in a liquid containing a fugitive binder has been found very satisfactory.
- concentration of metal powder in the liquid binder may range from 1' to 3 grams per cubic centimeter of binder solution.
- the coating may be applied by painting, spraying or dipping, which after drying forms a hard layer capable of withstanding the usual amounts of shock which prevail during handling, etc.
- the dried coating can be shaped to the desired thickness, making allowances for volume changes during treatment, and the coated skeleton inserted into an investment pack for heating to remove the fugitive binder and to sinter to some degree the metal powder to form in this case a porous primary coating into which the infiltrant metal flows by exfilt'ration from the skeleton during the subsequent infiltration process. Since the infiltrant phase is substantially common to both the skeleton body and the finally produced coating, a dense metallurgical' bond is assured.
- a t Nickel has been found very satisfactory as the primary coating material. Finely divided nickel powder, preferably 'finer than 140 mesh size (U.S. standard), suspended in a liquid varnish or resin binder, has proven particularly successful as a primary coat former.
- substantially all of the powder should preferably range in size from about minus to plus 325 mesh.
- the nickel primary coat maybe produced by spraying using a metallizing gun and nickel wire as the material source, I re insure someadherence of the coating.
- the surface of the skeleton is treated with a phenolic resin solution of medium viscosity (e.g. phenol formaldehyde) the excessLofwhichis wiped ofiand the material remaining on the surface and in the surface pores then cured at a temperature of about 350 F.
- the surface is lightly sand-blasted and then followed by spraying of the nickel to produce a primary coating which adheres to the resin treated surface As I before the resin is removed by volatilization either durplied a primary coating comprising bonded nickel powder shown in Fig. 1D.
- the skeleton with primary coat isv inserted in a refractory oxide powder pack in the mold shown in Fig 1E as comprising in cross section a graphite flask ⁇ against which is supported powder pack 3 which in 'turn supports the composite skeleton comprising ti- 'tanium carbide with primary nickel coat 1.
- Thetop. root portion 4 of the blade skeleton is left uncoated and has applied to it infiltrant metal 5 plus sufficient excess ready for infiltration into the pores of the skeleton and exfiltration from' the surface of the skeleton into the primary coating to form the final dense coating 6 shown in Fig. 1F.
- Fig. 2 which shows the flask portion 2a, a packing of refractory oxide 3; adjacent it supporting the composite skeleton comprising a porous foundation layer of nickel primary coating 1;: adhering to'the" porous skeleton portion 7 of titanium carbide.
- Fig. 3 is the same as Fig. 2 except that it shows the infiltration metal 8 in skeleton body 7. and also in primary coat 1c after exfiltration from the skeleton into the voids of the primary coatingat the instantbefore the, infiltrant has completely combined and alloyed with the material of the primary coating.
- the infiltrant 8 surrounding the titanium carbide particles 7 being slightly enriched in titanium carbide due to the rounding ofi of the particles, and the infiltrant surround ing the partially dissolved primary coat 1a being enriched in ni kel- Qt Q set e i filt n i hqm enized te u the s a ns sul in n. ompl l ion ft e.
- Fi 4 whic s a n escm ti 9 a nhq omi m rap is theactual appearance of the boundary conditions after. complete infiltration and exiiltration has occurred with complete alloying of thefinfiltrantwith thecoating reuit a bs a ti y o o ene m t x s u tur on ainin me p ecip tated t tan mrarb de own.
- Example 1 A-suspens oa o 2 r ins f, a b nyl c e p wde of 400 mesh size. (U.S.. standard). in cubic centi meters of a cementing solution comprising a natural resin dissolved in a chlorinated solvent (of the type sold The figure also illustrates-.
- a given amount of a heat-resistant nickel-base infiltrant alloy including an excess for exfiltration purposes (about nickel to 20% chromium), was placed on top of the uncoated end face of the, skeleton and the whole subjected to infiltration at above the melting point of the alloy but below the melting point ofthe nickel primary coating.
- the alloy had a melting point of slightly more than 50 C. below that of nickel.
- the infiltration was carriedout at a subatmospheric pressure of about 5 microns in an induction furnace to the point of completion of exfiltration.
- v Impact resistance of the coated specimen ranged from 7. to 9 inch-pounds based on an Izod drop impact test on a 3/ inch square cross section specimen.
- the assembly was packed in thoria powder with the uncoated end faceleft exposed to which was applied a heat-resisting nickel-base alloy comprising by weight about 13% to 16% chromium, about 6% to 8% iron, about 0.4 to 0.8 aluminum, about. 2.25 to 2.65% titanium, about 0.2 to 1.2% columbium, up to about 0.1% carbon, and the balancesubstantially nickel.
- the assembly was heated slowly at a subatmosphe'ric pressure of about 10 microns in an induction furnace to theinfiltration temperature during which time the residual binder in the primary coat was driven off leaving behind a partially sintered primary coat of nickel powder illustrated in i Fig. 2.
- the final infiltration temperature was'above the infiltrantmelting point of about 14lQ C.
- the photornicrograph showed a structure similar to that illustrated in Fig. 4, that is it revealed a substantially sharp boundary line between the carbide base material and the dense alloy coating.
- Example 3 The procedure asoutline'd in Example 2 was followed except that another-type binding solution was employed informing thenickel' slurry. yThe 20 grams ofnickel powder was suspended in a solution ofcthyl; cellulose 1. await and acetone (solution prepared by dissolving one gram of ethyl cellulose in 10 cubic centimeters of acetone) and reach the temperature, at which temperature it was'held for an additional hour to insure'freeing the primary coat-- ing of the ethyl cellulose binder and to effect at least a partial sintering of the nickel powder. The coated skeleton was then furnace cooled under hydrogen to room temperature after which it was subjected to infiltration in accordance with the steps of Example 2. Y
- a skeleton titanium carbide body the same as that described in-Example 2, was coated with a 0.02 inch nickel layer by dipping the skeleton in'a medium viscosity phenolic resin' (heat setting type, e phenol-formaldehyde) and the excess wiped olf. The top face was left uncoated to provide contact with the infiltrant. The dipped skeleton was cured for 20 minutes atabout 250 F. (177 C.) to harden the coating.
- a medium viscosity phenolic resin' heat setting type, e phenol-formaldehyde
- the body was'cooled and then sand blasted at about 25 pounds per square inch air pressure using 60'mesh al uminu'm' oxide abrasive and then followed by spraying using'a Brown and Sharpe gauge nickel wire and a Metco 4E gun manufactured by the Metallizing Engineering Company, the bar being rotated in a lathe during spraying. Ihe spraying was started at a distance of 15 to 18 inches, and after'acontinuous coat was applied, the nozzle of the "gun was brought to within 10 inches of the specimen for'the balance of the spraying.
- the coated body wasthen infiltrated-as described in- ExampleZ with the-nickel-base alloy defined in said example.
- the microstructure of the final product was as sound as that illustrated by the photomicrograph of Fig. 4.
- the impact strength of the bar after grinding down to 0.19 by 0.19 inch square cross section (i.e. to a coating thickness of about 0.01 inch), was about 7.5 inch-pounds at room temperature and about 10 inch-poundsat 1800 F. (about 982 C.).
- the bar exhibited .thesame impact value even after heating for 2-4 hours in still air at Example 5 In producing an airfoil-like shape having approximate dimensions of about 4 inches long, 2'inches wide, and a employed. Thus, in.
- Example 5 the method of the invention as described in Examples 1 to 2, and in particular in Example 5, is especially adapted to the coating of tapered bodiesysuch'as turbine buckets, diaphragm nozzles and varies, and other fluid guiding members characteri'zed 'by a relatively thick section tapering smoothly and 'arcuately into relatively thin edges.
- steps outlined in the flow sheet of Figs. 1A to IP would be employed.
- nickel may be employed in producing aprimary coating, provided these metals are compatible with the infiltrant r'netalarid alloy with it in pro.- ducing the desired coatingij such other metals may include cobalt, iroin. chromium, tungsten, molybdenum,
- tantalum, ,niobium or any other metal, or mixture, or'
- the infiltrant alloy upon which the infiltrant alloy may be based, provided the metal oralloy has a higher melting point than the 'infiltrant.
- porous skeleton of refractory metal compound on which theprimary. coating is formed may'be produced in accordance with the method outlined in copending application U .S'. Serial No. 442,564, filed July 12, 1954, now U.S..'Patent No. 2,752,666, inrthe names of Claus G. Goetzel and John -B. Adamec, also assigned to the present assignee.
- U.S'. Serial No. 442,564 filed July 12, 1954
- U.S..'Patent No. 2,752,666 inrthe names of Claus G. Goetzel and John -B. Adamec, also assigned to the present assignee.
- hot or cold pressing may be employed. It is preferred that these 7 materials, prior to pressing, be mixed with a binder metal in amounts up to 15% for example such binder metals as iron, nickel, cobalt, etc.
- the powdermixture is cold-pressed into a porous 1 body, it-is given a pre-s'intering treatment in a reducing atmosphere of ordinary or sub-atmospheric pressure below I 25.00 microns ofr'mercury column,kpreferably at a te'r'n-' sintering treatment is not required provided the hot pressing temperature is above the liquefaction, temperature of the cementing component.
- the skeleton body is produced'it may be machined to a size close torthe final specifications if necessary, by cutting with cemented carbide tools, orby refractory wheel grinding, diamond chipping, orother methods commonly employedin thefabrication of'hard carbideproducts.” In machining the body,
- an over-size shrinkage allowance of about 2% to 10% is generally made, in order to compensate for the shrinkage which occurs in subsequent heating operations.
- Final coating thickness ofthe infiltrated article may range from one-thousandth toone-sixteenth .of an inch, preferably from five-thousandths to'thirty-thousandths,
- the thus preparedskeleton body is'thensubjected to a high temperature sintering treatment in order to effect additional bonding of the carbide particles'into 'a porous skeleton 'of sufficient strength to enable the body to retain'its shape during subsequent infiltration treatment.
- a technical vacuum corresponding to a sub-atmospheric pressure rang ing froman initial pressure'of preferably notrmore than microns down to a final or, finishing pressure of 50 microns, of mercury and'preferably downto 10 microns.
- the surrounding gas at such subatrnospheric pressure must be non-oxidizing to the body, i.e. .reducing or inert,'tol
- chromium molybdenum,tungsten, vanadium, columbinm, tantalum, etc., and mixtures of two or more of these compounds. or the refractory compoundirnay' also include.
- Theinvention is preferably applicableto refractory metal carbides,
- titanium-base carbide may comprise up to about by volume of each of such metal carbides
- titanium-base carbide a carbide comprising substantially titanium carbide.
- the matrix-forming metals which may be employed in the metalliferous systems referred to herein include the iron group metals iron, nickel and; cobalt, rr'iixturesthereof, and heat-resistant alloys based on these metals,-i.e. heat resistant nickel-base, cobalt-base and iron base.
- nickel-base, matrix-forming alloys examples include; 80% nickel and 20% chromium; 80% nickel, 14% chromium and 6% iron; chromium, 7% iron, 1% niobium, 2.5% titanium, 0.7% aluminum and the balance nickel; 58% nickel, 15% chromium, 17% molybdenum, 5% tungsten and 5% iron; 95% nickel, 4.5% aluminum and 0.5% manganese, etc. 1
- cobalt-base alloys which may. be employed as matrix-forming metals include: 69% cobalt, 25 chromium, and 6% molybdenum; 65% cobalt, 25 chromium, 6% tungsten, 2% nickel, 1% iron and other elements making up the balance of 1%; 56% cobalt, 10% nickel, 26% chromium, and 7.5% tungsten, and some carbon; and 51.5% cobalt, 10% nickel, chromium, 15% tungsten, 2% iron, and 1.5% manganese, etc.
- iron-base matrix-forming alloys include: 53% iron, nickel, 16% chromium, and 6% molyb denum; 74% iron, 18%. chromium and 8% nickel; 86% iron and 14% chromium; 82% iron and 18% chromium; 73% iron and 27% chromium, etc.
- the matrix-forming infiltrant metal or alloy may contain up to about by weight of a metal selected from the group consisting of chromium, molybdenum and tungsten, the sum of the metals of said group preferably not exceeding 40%, substantially the. balance being at least one iron group metal selected from the group consisting of iron, cobalt and nickel, the sum of the iron group metals being'preferably at least about 40% by weight of the matrix-forming alloy.
- the matrixfonning allo'y may also contain up to about 8% total of at least one metal from the group columbium, tantalum, and vanadium.
- refractory metal compounds e.g. titanium-base carbide
- matrix-forming metals may be produced over a wide range of compositions.
- the refractory metal compound may range from about 40% to 80% by volume (preferably about 45% to 75%) and the matrix-forming metal range from about 60% to 20% by volume (preferably about 55% to 25%
- the present invention is also applicable to the production of cladded products generally, for example, to the production of cladded plates or other shapes of refractory carbide, or of other refractory compound material, wherein at least one side is cladded.
- the invention may be utilized in the production of brazeable cladded surfaces for use as mold liners in brick molds and other similar wear-resisting applications. Or, if desired, the invention may be employed in producing laminated structures comprising a series of alternate layers of a hard refractory compound and substantially ductile metal. In this case the laminated product would be produced from a laminated composite skeleton comprising,
- coat, coating, clad, cladding, etc.,'as employed herein are meant to include thelayer of one material ontop of another, or a layer of, material between two other layers.
- the expression .composite skeleton is meant to designate a porous skeleton body of refractory compound material having adhering to it a primary metal coating.
- an infiltration mold assembly comprising means for confining a powder pack of refractory oxide in which is supported snugly an infiltratable c0mposite skeleton body, the skeleton having on at least one surface thereof or between two surfaces a foundation metallayer or primary metal coating of predetermined thickness.
- such a mold assembly may define at one side thereof an inner confining wall (efg. graphite) against which is packed refractory oxide powder (e.g. zirconia or thoria) which in turn is packed snugly against a composite'skeleton comprising a primary metal coating on a surface comprised substantially of a refractory metal compound (e.g. titanium carbide) which may or may not alternate with the primary metal coating.
- refractory oxide powder e.g. zirconia or thoria
- a composite'skeleton comprising a primary metal coating on a surface comprised substantially of a refractory metal compound (e.g. titanium carbide) which may or may not alternate with the primary metal coating.
- a method for simultaneously: infiltrating and coat ing a porous refractory body which comprises producing a coherent porous skeletonof desired shape comprising a high melting point refractory compound material adapted for infiltration with a matrix-forming metal, providing the surface of said skeleton with a primary coating of metal of predetermined thickness, said metal having a melting point higher than the matrix-forming metal subsequently contained in the pores of said skeleton, adequately supporting the;coated surface of said skeleton in a pack of substantially inert refractory oxide material leaving a portion exposed for receiving infiltrant metal,
- a method for simultaneously infiltrating and coating a porous refractory body which comprises producing a coherent porous skeleton of desired shape comprising a high melting point refractory compound material adapted for infiltration with a matrix-forming metal, providing the surface of said skeleton with a substantially adherent primary coating of metal in particulate form of predetermined thickness, said metal having a melting point at least 50 C.
- a methodfor simultaneously infiltrating and coating a porous refractory body which comprises producing a coherent porous skeleton'of desired shape comprising a high melting point refractory compound material adapted for infiltration with a matrix-forming metal, providing the surface of said skeleton with a primary coating of metal powder of predetermined thickness bonded together with a vaporizable binder, said metal having a melting point at least 50? :C. higher'than the matrix-forming metal subsequently contained in the pores of said skeleton,'adequately supporting the surface of said coatedskeletonin a bed of substantially inert refractory oxide powder leaving a portion exposed for receiving infiltrant metal, subjecting said coated.
- a method for simultaneously infiltrating and coating a porous refractory body which comprises producing a coherent porous skeleton of desired shape comprising a high melting point refractory compound material adapted for infiltration with a matrix-forming metal, providing the, surface pores of said skeleton with a heat curable resin, curing said resin in said pores, spraying said surface with a metal layer of predetermined thickness, said metal having a melting point at least 50 C. higher than the matrix forming metal subsequently con-.
- An infiltration and cladding mold assembly comprising a mold having'confined thereina powder pack substantially inert refractory oxide material, a com.-
- An infiltration and cladding mold assembly comprising a mold having confined therein a powder pack of substantially inert refractory oxide material, a composite porous skeleton body having a primary metal coating of predetermined thickness on at least one surface thereof and supported by said powder pack at least adjacent said coated surface and means associated with one end of said skeleton for receiving infiltrant metal, theprimary coat ing having a melting point higher than the infiltrant metal.
- An infiltration and cladding mold assembly comprising a mold having confined therein a powder packof substantially inert refractory. oxide material, a composite porous skeleton body having a porous primary metal coating of predetermined thickness covering the surface thereof and supported by said powder pack surrounding snugly said coated surface and means associated with one end of said skeleton for receiving infiltrant metal, the primary metalrcoating having a melting point at least 50 C. higher than the infiltrant metal.
- An infiltration and cladding mold assembly comprising a mold having confined therein a powder pack of substantially inert refractory oxide material, a composite porous skeleton body having a porous primary metal coating of predetermined thickness covering the surface thereof and supported ,by saidpowder pack surrounding snugly saidcoated surface, the primary metal coating comprising particles of metal ranging in size 'substantially from minus 140 mesh to 'plus 325 mesh, and means associated with one end of said skeleton'for receiving infiltrant metal, the primary-metal coating having a melting point at least C. higher than'the infiltrant metal.
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Mechanical Engineering (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Description
Jan. 26, 1960 s. E. TARKAN ET AL 2,922,721
METHOD FOR COATING AND INFILTRATING A POROUS REFRACTORY BODY Filed April 2, 1956 2 Sheets-Sheet 1 FIG. IE.
FIG. IB.
and $2110.? 6. 6057251.
FIG. IA.
Jan. 26, 1960 s. E. TARKAN ET AL 2,922,721
METHOD FOR COATING AND INFILTRATING A POROUS REFRACTORY BODY Filed April 2, 1956 2 Sheets-Sheet 2 .5 IQF'ACE R p 6 a 7 x i 5 5 i 7x A 1! Y {a j COAT/N6 I N V EN TORS 572/44? TE. 72.?K/IV, #5440!!! Z Ih EWQ METHOD FOR COATING AND INFIL'IRATING A POROUS REFRACTORY BODY Stuart E. Tarkan and Henry W. Lawendel, New York,
and Claus G. Goetzel, Yonkers, N.Y., assignors to Sintercast Corporation of America, Yonkers, N.Y., a corporation of New York Application April 2, 1956, Serial No. 576,230 11 Claims. (21. 117-55 The present invention.- relates to coated refractory metal compound composites, and more particularly to a method for obtaining adherent metal coatings upon refractory metal carbide materials characterized by improved metallurgical'quality, improved resistance to oxidation, improved resistance to thermal and mechanical impact or shock, and generally improved properties at elevated temperatures.
The advent of modern jet engines, rockets and other types of prime movers involving heat engines operating at elevated temperatures ofup to about 1000 C. and higher has provoked intensive research in the development of high temperature materials, particularly in the development of thermal elements, for example fluid guiding elements such as turbine blades, buckets, nozzles, vanes, guides, partitions, etc., which inuse are exposed to corrosive gaseous atmospheres. The use of special fuels containing lead compounds, vanadium compounds and other compounds either present as additives or inherent in the fuel composition have been particularly troublesome in view of harmful vapors of lead oxide, vanadium pentoxide, etc. which are given off during combustion of the fuel and which readily chemically attack and corrode unprotected component parts of heat engines at elevated temperatures.
In an attempt to solve the foregoing problem, certain wrought and cast heat resistant alloys of special corrosion resistant compositions were. developed. However, these alloys were limited in their application because of their melting points which range in the neighborhood of about 1300 C. to 1500 C. As more powerful jet engines were designed to operate at higher temperatures, additional burdens were placed on these alloys which had to be replaced by more stable materials of higher melting point.
An outstanding material which was developed and proposed to meet this need was a refractory carbide material consisting of about equal proportions by weight of titaniurn carbide and an alloy of the so-called super alloy type usually containing nickel or cobalt as major alloying constituents, and chromium, tungsten, molybdenum, titanium, iron, aluminum, etc. as other alloying constituents. This material could either be prepared by the well-known cementing method employed in the powder metallurgical production of carbide tools, that is by mixing refractory carbide particles with a given amount of binder metal, for example nickel or cobalt or an alloy based on these metals, followed by pressing the mixture into a desired shape and thereafter sintering it; or the material could be produced by forming a sintered porous skeleton comprising a refractorymetal carbide and thereafter infiltrating it with a heat resistant metal or alloy to form a strong composite structure. The latter method was preferred over the former as it enabled the consistent production of superior materials. It was found that thermal elements produced by infiltration comprising about 50% by Weight of titanium carbide and about 50% by weight of a nickel base alloy containing about 13% 2,922,721 Patented Jan. 26, 1960 to 15% chromium and about 6% to 7% iron as alloying constituents could withstand a stress of about 42,000 p.s.i. at a temperature of about 875 C. for 100 hours in an oxidizing atmosphere before it would rupture. Itwas, also found that the same material at 985 C. would withstand a stress of 16,000 psi. before it would rupture after 100 hours of testing. At the lower temperature, the thermal elements after testing exhibited an elongation of the order of about 2% to 3% and an impact strength of about 10 ft. lbs. for a Charpy-type unnotched bar, while at the higher temperature they exhibited an elongation of about 4% to 8% and an impact strength of about 6.5 ft. lbs.
The foregoing properties have been found satisfactory for parts to be used in short time applications in jet engines, and performance records of up to about 100 hours have been established in actual service tests. However, present demands for increasedservice life under more aggravated service conditions prevailing in the latest jet engine and rocket designs have necessitated the development of even better high temperature materials. It was found that it was necessary to improve oxidation resistance, strength, thermal shock and impact resistance of refractory metal carbide composition at temperatures in the range between 950 C. and 1050 C. and bring these properties in closer accord with the extremely good properties which were established for these same materials at 875 C. v
It was observed that while these materials were a substantial improvement over Wrought or cast heat resistant alloys, they tended to fail during prolonged service as a result of surface deterioration due to oxidation and cor-' rosion at temperatures above 900 C. and of the order of about 950 C. to 1050 C. It was found that surface, deterioration would occur due to corrosion which markedly deleteriously affected the impact resistance and strength of the material. The failure was usually of a type characteristic of brittle materials. It was felt that, in order to inhibit such surface attacks and sustain the properties of the material, it would be necessary to'provide a protective surface coating around the exposed working surfaces of the metal carbide composite was to protect it from hot corrosive atmospheres. Various, methods have been proposed for providing such protective coatings to refractory'compound composites. Thus, according to US. Patent No. 2,714,245, granted to Claus G. Goetzel on August 2, 1955, and assigned to the present assignee, the protective coating could be achieved during infiltration, of a porous skeleton body by first producingthe porous body (.e.g. a turbine blade) slightly undersized, centering it in the cavity of a mold comprising a substantially inert refractory, the cavity conforming in shape to but being slightly larger than the body, infiltrating the body and allowing for suificient excess infiltrant to fill the space between the blade and the mold walls to provide for the coating. Coatings of controlled thickness produced in this manner markedly improve the properties of turbine buckets, providing extreme care was taken in indexing the skeleton in the mold cavity to insure obtaining the desired coating dimensions and also provided the heating cycle was carefully controlled to minimize non-uniformshrinkage or warpage of the inert refractory. Also care had to be taken to control the infiltration process so that the infiltrant'metal during infiltration did not gush down the sides of the skeleton and erode its surface.
In copending application U.S. Serial No. 485,568, filed January 28, 1955, in the names of Claus G. Goetzel,
Nicholas J. Grant, Leonard P. Skolnick and Jack A.-
Yoblen, and assigned to the present assignee, a method for coating refractory metal compound composites is disbonded, relatively ductile coating by controlling the relative temperatures of the composite and the cbatingma:
teriall so as to'preverit embrittle'rnent of the coating by excessive diffusion of the base material into it. Improved results could be consistently obtained by this; concept provrdedzthe necessary care was 'taken to control the relative temperatures of the materials to be joined.
. The present invention differs over the'foregoing concepts m that an entirely new approach is utilized for coating metal compound composites produced by infiltratron. It is particularly applicable to the production of coated products having a tapered configuration, for example, fluid guiding members, such as turbine buckets or nozzle .vanes, characterized by a thick portion near the lead ng edge tapering smoothly and arcuately to a relatively thin trailing edge portion. Generally speaking, tapered bodies area little more ditficult to coat substantially uniformly, particularly when the coating is carried out simultaneously with infiltration in amold. Even whenihe skeleton fluid-memberis'properly indexed in a mold 'with'a space provided between .the'skeleton and the mold for receiving the infiltrant metal coating, movement of the body withinjhe'mold or movement of the mold walls themselves during heating isapt' to throw off the indexed skeleton sufliciently to effect deleteriou sly the uniformity of the coating. V
An improved method has now been discovered whereby ,the foregoing disadvantages are .greatly minimized wherein the skeleton body prior to infiltration is produced as a composite structure which obviates thenecessity of accurately indexing the skeleton in the mold when'producing a coated body by infiltration.
Another important advantage is that the improved method also minimizes erosion of the skeleton surface during the combined infiltration and. coating step. It is the object of the invention to provide a combined infiltration and coating process for producing coated infiltrated composites comprising a high melting point re fractory metal compound material, for example titanium carbide. I
Another object is to provide a method for producing a coating of improved metallurgical quality on infiltrated refractorymetal compound materials.
, These and other objects will more clearly' appear when taken in conjunction with the accompanying drawing wherein:
Figs. 1A to 1F depict inflow sheet arrangement the steps and materials which may be employed in carrying out an embodiment of the invention;
Fig. 2 illustrates an expanded view of the boundary conditions which prevail in an embodiment of the invention between the mold and the skeleton prior to in filtration in the production of a coated body;
Fig. 3 is. similar-to Fig. 2 but shows the penetration of the infiltrant metal into the interstices of the skeleton and the" primary coating by infiltration; and
Flg. 4 is a representation of a photomicrograph at 250' magnificationof a transverse section of the final productv showing a relatively sharp line of demarcation between the coating and the base material.
In carrying the invention into practice, the porous skeleton body to be infiltrated is provided with a foundation layer or primary coating of a metal alloyable with the infiltrant metal, the thickness of the primarymetal coating determining to a large extent thedesired thickness of the final coating. Once the skeleton body is prm vided with the primary coating, it need only be inserted in -a powder pack of substantially inert refractory, e.g. thoria, zirconia, beryllia, alumina, etc, without taking the usual precautions of indexing the body to insure a' coating of accurate dimensions. In other 'words, the
primary coating of the composite skeleton also serves mold comprises the porous skeleton on one side, a primary metal coating of desired thickness on the surface thereof and on the other side of the primary coating a back-up support of substantially inert refractory oxide material. The composite skeleton is subjected to infiltration in the usual manner with a matrixforming metal which flows through the skeleton filling u'p'the pores and on out through the surface thereof merging and al-' loying with the primary coating. The flowing of the molten infiltrant metal but of the skeleton surface and into the primary coating is referred to as exfiltration and the use of this and equivalent expressions hereinafter is meant to cover the aforementioned phenomenon.
The primary coating metal employed in carrying out the invention should be one which will combine with the infiltrant to form a coating having the desired properties, i.e. having resistance to corrosion, erosion and oxidation and adequate ductility, hardness, etc. The metal should have a melting point higher than the melting point of the matrix-forming infiltrant metal so that the foundation layer provided by the primarycoating will not be prematurely disrupted before completion of the exfiltration step. Thus it is preferred that the melting point of the coating metal should be atleast 50 degrees higher than the melting point of the infiltrant metal in the pores of the skeleton. Additionally,,the. primary metal coat should not combine with the material of the skeleton to form a liquid phase at a temperature below the melting point of the matrix-forming infiltrant metal.
Goodresults are obtained by applying the metal coating in particulate form, powdered metal being preferably employed as the primary coating metal, although the coating metal may be applied by wire spraying, metal plating, etc; V
In building up a primary coating on a skeleton surface from powdered metal, a suspension of the metal in a liquid containing a fugitive binder has been found very satisfactory. The concentration of metal powder in the liquid binder may range from 1' to 3 grams per cubic centimeter of binder solution. The coating may be applied by painting, spraying or dipping, which after drying forms a hard layer capable of withstanding the usual amounts of shock which prevail during handling, etc. The dried coating can be shaped to the desired thickness, making allowances for volume changes during treatment, and the coated skeleton inserted into an investment pack for heating to remove the fugitive binder and to sinter to some degree the metal powder to form in this case a porous primary coating into which the infiltrant metal flows by exfilt'ration from the skeleton during the subsequent infiltration process. Since the infiltrant phase is substantially common to both the skeleton body and the finally produced coating, a dense metallurgical' bond is assured. a t Nickel has been found very satisfactory as the primary coating material. Finely divided nickel powder, preferably 'finer than 140 mesh size (U.S. standard), suspended in a liquid varnish or resin binder, has proven particularly successful as a primary coat former. When employing metal powders generally as the primary coat, substantially all of the powder should preferably range in size from about minus to plus 325 mesh. After thecoating is formed on a skeleton body by painting, dipping or spraying, and the resin cured by heating to an elevated 'curing temperature, the coated body is then subjected to an infiltration cycle during which the binder is volatilized and driven off. 'If the resin has a high vapor pressuredeleterious to the infiltrationfcycle, the volatilizationis then eflected prior to infiltration under substantially inert conditions while the composite skeletonisiembedded in the refractory ,powder pack.
If-desired, the nickel primary coat maybe produced by spraying using a metallizing gun and nickel wire as the material source, I re insure someadherence of the coating. to the skeleton, the surface of the skeleton is treated with a phenolic resin solution of medium viscosity (e.g. phenol formaldehyde) the excessLofwhichis wiped ofiand the material remaining on the surface and in the surface pores then cured at a temperature of about 350 F. The surface is lightly sand-blasted and then followed by spraying of the nickel to produce a primary coating which adheres to the resin treated surface As I before the resin is removed by volatilization either durplied a primary coating comprising bonded nickel powder shown in Fig. 1D. The skeleton with primary coat isv inserted in a refractory oxide powder pack in the mold shown in Fig 1E as comprising in cross section a graphite flask} against which is supported powder pack 3 which in 'turn supports the composite skeleton comprising ti- 'tanium carbide with primary nickel coat 1. Thetop. root portion 4 of the blade skeleton is left uncoated and has applied to it infiltrant metal 5 plus sufficient excess ready for infiltration into the pores of the skeleton and exfiltration from' the surface of the skeleton into the primary coating to form the final dense coating 6 shown in Fig. 1F.
he: bo nda y nd t ons te a l bet n t e @91 1 surface, the primary coating, and the skeleton, is illustrated by the expanded cross-sectional representation of Fig. 2 which shows the flask portion 2a, a packing of refractory oxide 3;; adjacent it supporting the composite skeleton comprising a porous foundation layer of nickel primary coating 1;: adhering to'the" porous skeleton portion 7 of titanium carbide. Fig. 3 is the same as Fig. 2 except that it shows the infiltration metal 8 in skeleton body 7. and also in primary coat 1c after exfiltration from the skeleton into the voids of the primary coatingat the instantbefore the, infiltrant has completely combined and alloyed with the material of the primary coating.
It will be appreciated that at this point of. the infiltration a concentration gradient will exist in the infiltrant, the infiltrant 8 surrounding the titanium carbide particles 7 being slightly enriched in titanium carbide due to the rounding ofi of the particles, and the infiltrant surround ing the partially dissolved primary coat 1a being enriched in ni kel- Qt Q set e i filt n i hqm enized te u the s a ns sul in n. ompl l ion ft e.
primary co a sho n, Fi
Fi 4 whic s a n escm ti 9 a nhq omi m rap is theactual appearance of the boundary conditions after. complete infiltration and exiiltration has occurred with complete alloying of thefinfiltrantwith thecoating reuit a bs a ti y o o ene m t x s u tur on ainin me p ecip tated t tan mrarb de own.
by a transversesection through the base surface and the finally produced coating. the relatively sharp line of demarcation resulting from this method of coating thus showing that the originalv surface vof.the carbide is not disrupted to any significant degree.
As illustrative of the invention, thefollowing examples aregiven;
' Example 1 A-suspens oa o 2 r ins f, a b nyl c e p wde of 400 mesh size. (U.S.. standard). in cubic centi meters of a cementing solution comprising a natural resin dissolved in a chlorinated solvent (of the type sold The figure also illustrates-.
by the Wall Colmonoy Company under the trademark Nicrobraz is employed in producing a primary coating on a sintered porous body of titanium carbide (60% dense) of approximately 0.2 inch square and 2 inches long. A layer of about 0.01 inch of the nickel was applied to the surface of the bar leaving one end face of the bar uncoated for receiving the infiltrant metal. After the coating hardened the resulting composite skeleton was packed in a ceramic powder pack, e.g. thoria, in the manner shown in Fig. 1E. A given amount of a heat-resistant nickel-base infiltrant alloy including an excess for exfiltration purposes (about nickel to 20% chromium), was placed on top of the uncoated end face of the, skeleton and the whole subjected to infiltration at above the melting point of the alloy but below the melting point ofthe nickel primary coating. The alloy had a melting point of slightly more than 50 C. below that of nickel. The infiltration was carriedout at a subatmospheric pressure of about 5 microns in an induction furnace to the point of completion of exfiltration. Photomicrographs of a mounted section similar to Fig. 4 indicated that the interface between the body and the coating was entirely sound and that substantially no deformation of the original skeleton occurred, that is a relatively sharp boundary line between the carbide base material and the coating was maintained, v Impact resistance of the coated specimen ranged from 7. to 9 inch-pounds based on an Izod drop impact test on a 3/ inch square cross section specimen.
, Examp A titaniumcarbide. skeleton body (about 60% dense) was produced measuring 0.17 by 0.17 inch square and approximately 2 inches long. 20-grams of relatively coarse nickel powderall passing through a mesh (U.S. standard) screen but remaining on a 325 'mesh screen suspended in 10' cubic centimeters of cementing solution comprising a; natural resin dissolved in a chlorinated solvent defined in Examplel was employed in producing the nickel coating. The coating thickness was about 0.03 inch over the surface of the bar with the exception of one end face which was used as the infiltrant contact face. After, the coating was. allowed to harden, the coated-skeleton. was packed in thoria powder with the uncoated end faceleft exposed to which was applied a heat-resisting nickel-base alloy comprising by weight about 13% to 16% chromium, about 6% to 8% iron, about 0.4 to 0.8 aluminum, about. 2.25 to 2.65% titanium, about 0.2 to 1.2% columbium, up to about 0.1% carbon, and the balancesubstantially nickel. The assembly was heated slowly at a subatmosphe'ric pressure of about 10 microns in an induction furnace to theinfiltration temperature during which time the residual binder in the primary coat was driven off leaving behind a partially sintered primary coat of nickel powder illustrated in i Fig. 2. The final infiltration temperature .was'above the infiltrantmelting point of about 14lQ C. but below the meltingpointof the nickel primary coat. The temperature was held for about 20 minutes at and near the 'mel ting point. The molten in'filtrant spread through the interconnectingpores of the skeleton by virtue of the capillary action thereof assisted by the force of gravity. The excess infiltrant exfiltrated from the surface of the carbide skeleton into the overlying primary coating and merged with it to form a dense coating of uniform alloy composition. Like Example 1, the photornicrograph showed a structure similar to that illustrated in Fig. 4, that is it revealed a substantially sharp boundary line between the carbide base material and the dense alloy coating.
Example 3 The procedure asoutline'd in Example 2 was followed except that another-type binding solution was employed informing thenickel' slurry. yThe 20 grams ofnickel powder was suspended in a solution ofcthyl; cellulose 1. await and acetone (solution prepared by dissolving one gram of ethyl cellulose in 10 cubic centimeters of acetone) and reach the temperature, at which temperature it was'held for an additional hour to insure'freeing the primary coat-- ing of the ethyl cellulose binder and to effect at least a partial sintering of the nickel powder. The coated skeleton was then furnace cooled under hydrogen to room temperature after which it was subjected to infiltration in accordance with the steps of Example 2. Y
Example. 4
A skeleton titanium carbide body, the same as that described in-Example 2, was coated with a 0.02 inch nickel layer by dipping the skeleton in'a medium viscosity phenolic resin' (heat setting type, e phenol-formaldehyde) and the excess wiped olf. The top face was left uncoated to provide contact with the infiltrant. The dipped skeleton was cured for 20 minutes atabout 250 F. (177 C.) to harden the coating. The body was'cooled and then sand blasted at about 25 pounds per square inch air pressure using 60'mesh al uminu'm' oxide abrasive and then followed by spraying using'a Brown and Sharpe gauge nickel wire and a Metco 4E gun manufactured by the Metallizing Engineering Company, the bar being rotated in a lathe during spraying. Ihe spraying was started at a distance of 15 to 18 inches, and after'acontinuous coat was applied, the nozzle of the "gun was brought to within 10 inches of the specimen for'the balance of the spraying.
The coated body wasthen infiltrated-as described in- ExampleZ with the-nickel-base alloy defined in said example. The microstructure of the final product was as sound as that illustrated by the photomicrograph of Fig. 4.
The impact strength of the bar, after grinding down to 0.19 by 0.19 inch square cross section (i.e. to a coating thickness of about 0.01 inch), was about 7.5 inch-pounds at room temperature and about 10 inch-poundsat 1800 F. (about 982 C.). The bar exhibited .thesame impact value even after heating for 2-4 hours in still air at Example 5 In producing an airfoil-like shape having approximate dimensions of about 4 inches long, 2'inches wide, and a employed. Thus, in. preparinga primary coat of about 0.01 inch on all airfoil surfaces, the same suspension of nickel powder in the cementing solution is used, an end face of the airfoil being left uncoated to receive infiltrant metal-Q Thereafter, the prepared airfoil section'is infiltrated in the same manner as the method described in Example 2. p v
'As has been indicated hereinbefore, the method of the invention as described in Examples 1 to 2, and in particular in Example 5, is especially adapted to the coating of tapered bodiesysuch'as turbine buckets, diaphragm nozzles and varies, and other fluid guiding members characteri'zed 'by a relatively thick section tapering smoothly and 'arcuately into relatively thin edges. In utilizing the foregoing methods in the production'of a' turbine bucket, the steps outlined in the flow sheet of Figs. 1A to IP would be employed.
'Besides nickel, other metals may be employed in producing aprimary coating, provided these metals are compatible with the infiltrant r'netalarid alloy with it in pro.- ducing the desired coatingij such other metals may include cobalt, iroin. chromium, tungsten, molybdenum,
tantalum, ,niobium,"or any other metal, or mixture, or'
alloy of these metals, upon which the infiltrant alloy may be based, provided the metal oralloy has a higher melting point than the 'infiltrant.
The porous skeleton of refractory metal compound on which theprimary. coating is formed may'be produced in accordance with the method outlined in copending application U .S'. Serial No. 442,564, filed July 12, 1954, now U.S..'Patent No. 2,752,666, inrthe names of Claus G. Goetzel and John -B. Adamec, also assigned to the present assignee. According to this copending application, in producing refractory carbide skeletons or refractory compound skeletons having intercommunicating pores,'hot or cold pressingmay be employed. It is preferred that these 7 materials, prior to pressing, be mixed with a binder metal in amounts up to 15% for example such binder metals as iron, nickel, cobalt, etc. I p s I I-f the powdermixture is cold-pressed into a porous 1 body, it-is given a pre-s'intering treatment in a reducing atmosphere of ordinary or sub-atmospheric pressure below I 25.00 microns ofr'mercury column,kpreferably at a te'r'n-' sintering treatment is not required provided the hot pressing temperature is above the liquefaction, temperature of the cementing component. 1 After'the skeleton body is produced'it may be machined to a size close torthe final specifications if necessary, by cutting with cemented carbide tools, orby refractory wheel grinding, diamond chipping, orother methods commonly employedin thefabrication of'hard carbideproducts." In machining the body,
an over-size shrinkage allowance of about 2% to 10% is generally made, in order to compensate for the shrinkage which occurs in subsequent heating operations.
Final coating thickness ofthe infiltrated article may range from one-thousandth toone-sixteenth .of an inch, preferably from five-thousandths to'thirty-thousandths,
' The thus preparedskeleton body is'thensubjected to a high temperature sintering treatment in order to effect additional bonding of the carbide particles'into 'a porous skeleton 'of sufficient strength to enable the body to retain'its shape during subsequent infiltration treatment.
In carrying out thehigh temperature sintering operation,
it is preferred so 'sinterthe skeleton bodyat -a tempera- ,ture between, 50 C. and 250 CL above the temperature;
used inthe subsequent infiltration operation in a technical vacuum corresponding to a sub-atmospheric pressure rang ing froman initial pressure'of preferably notrmore than microns down to a final or, finishing pressure of 50 microns, of mercury and'preferably downto 10 microns. The surrounding gas at such subatrnospheric pressure must be non-oxidizing to the body, i.e. .reducing or inert,'tol
borides, nitrides, silicid es, etc., of titanium, zirconium,
chromium, molybdenum,tungsten, vanadium, columbinm, tantalum, etc., and mixtures of two or more of these compounds. or the refractory compoundirnay' also include.
such refractory oxidesas'oxi'des of aluminum, beryllium,
zirconium, thorium, magnesium,c erium etc: Theinvention ispreferably applicableto refractory metal carbides,
s particularly titanium carbide, or a carbide, based on titanium. Thus, titanium-base carbide may comprise up to about by volume of each of such metal carbides,
as silicon carbide, boron carbide, and up to about by volume each of chromium carbide, columbium carbide, tungsten carbide, zirconium carbide, or hafnium carbide, the total amounts'of these carbides generally not exceeding 25% by volume ofthe titanium-base carbide. By titanium-base carbide is meant a carbide comprising substantially titanium carbide.
The matrix-forming metals which may be employed in the metalliferous systems referred to herein include the iron group metals iron, nickel and; cobalt, rr'iixturesthereof, and heat-resistant alloys based on these metals,-i.e. heat resistant nickel-base, cobalt-base and iron base.
Examples of nickel-base, matrix-forming alloys include; 80% nickel and 20% chromium; 80% nickel, 14% chromium and 6% iron; chromium, 7% iron, 1% niobium, 2.5% titanium, 0.7% aluminum and the balance nickel; 58% nickel, 15% chromium, 17% molybdenum, 5% tungsten and 5% iron; 95% nickel, 4.5% aluminum and 0.5% manganese, etc. 1
Examples of cobalt-base alloys which may. be employed as matrix-forming metals include: 69% cobalt, 25 chromium, and 6% molybdenum; 65% cobalt, 25 chromium, 6% tungsten, 2% nickel, 1% iron and other elements making up the balance of 1%; 56% cobalt, 10% nickel, 26% chromium, and 7.5% tungsten, and some carbon; and 51.5% cobalt, 10% nickel, chromium, 15% tungsten, 2% iron, and 1.5% manganese, etc.
Some of the iron-base matrix-forming alloys include: 53% iron, nickel, 16% chromium, and 6% molyb denum; 74% iron, 18%. chromium and 8% nickel; 86% iron and 14% chromium; 82% iron and 18% chromium; 73% iron and 27% chromium, etc.
The matrix-forming infiltrant metal or alloy may contain up to about by weight of a metal selected from the group consisting of chromium, molybdenum and tungsten, the sum of the metals of said group preferably not exceeding 40%, substantially the. balance being at least one iron group metal selected from the group consisting of iron, cobalt and nickel, the sum of the iron group metals being'preferably at least about 40% by weight of the matrix-forming alloy. If desired, the matrixfonning allo'y may also contain up to about 8% total of at least one metal from the group columbium, tantalum, and vanadium.
Alloys of the aforementioned types containing effective amounts of so-called well-known strengthening or agehardening elements, such as zirconium, titanium, aluminum, etc., may also be employed in matrix-forming metals or alloys.
'Metalliferous systems based on refractory metal compounds (e.g. titanium-base carbide) and matrix-forming metals, may be produced over a wide range of compositions. In producing bodies by liquid phase sintering or by infiltration, the refractory metal compound may range from about 40% to 80% by volume (preferably about 45% to 75%) and the matrix-forming metal range from about 60% to 20% by volume (preferably about 55% to 25% It will be appreciated that the present invention is also applicable to the production of cladded products generally, for example, to the production of cladded plates or other shapes of refractory carbide, or of other refractory compound material, wherein at least one side is cladded. The invention may be utilized in the production of brazeable cladded surfaces for use as mold liners in brick molds and other similar wear-resisting applications. Or, if desired, the invention may be employed in producing laminated structures comprising a series of alternate layers of a hard refractory compound and substantially ductile metal. In this case the laminated product would be produced from a laminated composite skeleton comprising,
for example, sintered, porous, layers of titanium carbide alternating with sinteredporous layers of the primary metal coating. Upon infiltration, the pores of the carbide and the alternate layers of primary coating would absorb the. infiltrant metal to form a solid laminated product,
The expressions coat, coating, clad, cladding, etc.,'as employed herein are meant to include thelayer of one material ontop of another, or a layer of, material between two other layers. The expression .composite skeleton is meant to designate a porous skeleton body of refractory compound material having adhering to it a primary metal coating.
While. the present invention has been described as a process for producing coated or cladded composites, it will be appreciated it also provides a combined infiltration and cladding mold assembly for carrying out saidprocess. Thus, an infiltration mold assembly is providedcomprising means for confining a powder pack of refractory oxide in which is supported snugly an infiltratable c0mposite skeleton body, the skeleton having on at least one surface thereof or between two surfaces a foundation metallayer or primary metal coating of predetermined thickness.
In cross-section such a mold assembly may define at one side thereof an inner confining wall (efg. graphite) against which is packed refractory oxide powder (e.g. zirconia or thoria) which in turn is packed snugly against a composite'skeleton comprising a primary metal coating on a surface comprised substantially of a refractory metal compound (e.g. titanium carbide) which may or may not alternate with the primary metal coating.
Although the present invention has been described in conjunction with preferred embodiments, it is to be understood that modifications and variations may be resorted to without departing from the spirit and scope of the invention as those skilled in the art will readily understand. Such modifications and variations are considered to be within the purview and scope of the invention and appended claims. 4
We claim:
1. A method for simultaneously: infiltrating and coat ing a porous refractory body which comprises producing a coherent porous skeletonof desired shape comprising a high melting point refractory compound material adapted for infiltration with a matrix-forming metal, providing the surface of said skeleton with a primary coating of metal of predetermined thickness, said metal having a melting point higher than the matrix-forming metal subsequently contained in the pores of said skeleton, adequately supporting the;coated surface of said skeleton in a pack of substantially inert refractory oxide material leaving a portion exposed for receiving infiltrant metal,
posed portion with said matrix-forming metal at a temperature below the melting point of the primary metal coating, and continuing said infiltration in said skeleton body whereby excess matrix-forming metal exfiltrates through the coated surface thereof and into the overlying metal coating and merges therewith by alloying.
2. A method for simultaneously infiltrating and coating a porous refractory body which comprises producing a coherent porous skeleton of desired shape comprising a high melting point refractory compound material adapted for infiltration with a matrix-forming metal, providing the surface of said skeleton with a substantially adherent primary coating of metal in particulate form of predetermined thickness, said metal having a melting point at least 50 C. higher than the matrix-forming metal subsequently contained in the pores of said skeleton, ardequately supporting the coated surface of said skeleton in a bed of substantially inert refractory oxide material leaving a portion exposed for receiving infiltrant metal, subjecting said coated skeleton to infiltration at the exposed portion with said matrix-forming metal at a temperature below the melting point of the primary metal coating,
11 and continuing said infiltrationwhereby excess matrixforming metal exfiltrates through the surface thereof and into the overlyingp'rimary metallcoating and merges therewith.
3.- The method of claim 2wherein the primary metal coating in particulate form is applied by metal spraying. 4. The method of claim'2 wherein the primary metal coating in particulate form. is derived from a suspension of metal powder in a liquid binder solution. 1 i
5. The method of claim 4 wherein the metal powder suspension ranges in mesh size from minus 140 to plus 325. 1
6. A methodfor simultaneously infiltrating and coating a porous refractory bodywhich comprises producing a coherent porous skeleton'of desired shape comprising a high melting point refractory compound material adapted for infiltration with a matrix-forming metal, providing the surface of said skeleton with a primary coating of metal powder of predetermined thickness bonded together with a vaporizable binder, said metal having a melting point at least 50? :C. higher'than the matrix-forming metal subsequently contained in the pores of said skeleton,'adequately supporting the surface of said coatedskeletonin a bed of substantially inert refractory oxide powder leaving a portion exposed for receiving infiltrant metal, subjecting said coated. skeleton to heating to vaporize said binder, infiltrating said' coated skeleton with said infiltrant metal, and continuing said infiltration whereby excess matrixforming metal exfiltrates through the surface of said skeleton and into the overlying metal coating and merges and alloys therewith.
' 7 A method for simultaneously infiltrating and coating a porous refractory body which comprises producing a coherent porous skeleton of desired shape comprising a high melting point refractory compound material adapted for infiltration with a matrix-forming metal, providing the, surface pores of said skeleton with a heat curable resin, curing said resin in said pores, spraying said surface with a metal layer of predetermined thickness, said metal having a melting point at least 50 C. higher than the matrix forming metal subsequently con-.
tained in the pores of said skeleton, adequately sup porting the surface ofsaid coated skeleton 'in a bed. of substantially inert refractory oxide powder leaving a portion exposed for receiving infiltrant metal, subjecting said coated skeleton to heating to vaporize said. binder, infiltratingsaid coated skeleton with said matrix-forming metal, and continuing said infiltration whereby excess matrix-forming metal exfiltrates through thesurface of said skeleton and into the overlying metal coating and merges and alloys therewith. 7 v
8. An infiltration and cladding mold assembly comprising a mold having'confined thereina powder pack substantially inert refractory oxide material, a com.-
posite porous skeletonbody having ,a primary metal coat? ing of predeterminedfthickness .onfa't least one surface thereofand supported by saidpowderpack 'at least adjacent said =coated surface, and means associated with one end of said skeleton for'receiving infiltrant metal.
9. An infiltration and cladding mold assembly comprising a mold having confined therein a powder pack of substantially inert refractory oxide material, a composite porous skeleton body having a primary metal coating of predetermined thickness on at least one surface thereof and supported by said powder pack at least adjacent said coated surface and means associated with one end of said skeleton for receiving infiltrant metal, theprimary coat ing having a melting point higher than the infiltrant metal.
10. An infiltration and cladding mold assembly comprising a mold having confined therein a powder packof substantially inert refractory. oxide material, a composite porous skeleton body having a porous primary metal coating of predetermined thickness covering the surface thereof and supported by said powder pack surrounding snugly said coated surface and means associated with one end of said skeleton for receiving infiltrant metal, the primary metalrcoating having a melting point at least 50 C. higher than the infiltrant metal.
11. An infiltration and cladding mold assembly comprising a mold having confined therein a powder pack of substantially inert refractory oxide material, a composite porous skeleton body having a porous primary metal coating of predetermined thickness covering the surface thereof and supported ,by saidpowder pack surrounding snugly saidcoated surface, the primary metal coating comprising particles of metal ranging in size 'substantially from minus 140 mesh to 'plus 325 mesh, and means associated with one end of said skeleton'for receiving infiltrant metal, the primary-metal coating having a melting point at least C. higher than'the infiltrant metal. i
References Cited in the file of this patent UNITED STATES PATENTS 7 2,119,989 Higgins June 7, 1938 2,325,553 Schleicher a July- 27, 1943 2,667,427 Nolte Jan. 26,1954 2,719,095 Scanlon Sept. 27, 1955 2,733,167 Stookey Jan. 31, 1956 2,751,293 Haller June 19, 1956 2,768,099 Hoyer Oct. 23, 1956 2,769,611 Schwarzkopf Nov. 6, 1956 2,798,577 .La Forge July 9, 1957 FOREIGN PATENTS 661,031 Great Britain Nov. 14, 1951
Claims (1)
1. A METHOD FOR SIMULTANEOUSLY INFILTRATING AND COATING A POROUS REFRACTORY BODY WHICH COMPRISES PRODUCING A COHERENT POROUS SKELETON OF DESIRED SHAPE COMPRISING A HIGH MELTING POINT REFRACTORY COMPOUND MATERIAL ADAPTED FOR INFILTRATION WITH A MATRIX-FORMING METAL, PROVIDING THE SURFACE OF SAID SKELETON WITH A PRIMARY COATING OF METAL OF PREDETERMINED THICKNESS, SAID METAL HAVING A MELTING POINT HIGHER THAN THE MATRIX-FORMING METAL SUBSEQUENTLY CONTAINED IN THE PORES OF SAID SKELETON, ADEQUATELY SUPPORTING THE COATED SURFACE OF SAID SKELETON IN A PACK OF SUBSTANTIALLY INERT REFRACTORY OXIDE MATERIAL LEAVING A PORTION EXPOSED FOR RECEIVING INFILTRANT METAL, SUBJECTING SAID COATED SKELETON TO INFILTRATION AT THE EXPOSED PORTION WITH SAID MATRIX-FORMING METAL AT A TEMPERATURE BELOW THE MELTING POINT OF THE PRIMARY METAL COATING, AND CONTINUING SAID INFILTRATION IN SAID SKELETON BODY WHEREBY EXCESS MATRIX-FORMING METAL EXFILTRATES THROUGH THE COATED SURFACE THEREOF AND INTO THE OVERLYING METAL COATING AND MERGES THEREWITH BY ALLOYING.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US576230A US2922721A (en) | 1956-04-02 | 1956-04-02 | Method for coating and infiltrating a porous refractory body |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US576230A US2922721A (en) | 1956-04-02 | 1956-04-02 | Method for coating and infiltrating a porous refractory body |
Publications (1)
Publication Number | Publication Date |
---|---|
US2922721A true US2922721A (en) | 1960-01-26 |
Family
ID=24303488
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US576230A Expired - Lifetime US2922721A (en) | 1956-04-02 | 1956-04-02 | Method for coating and infiltrating a porous refractory body |
Country Status (1)
Country | Link |
---|---|
US (1) | US2922721A (en) |
Cited By (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3261894A (en) * | 1961-02-27 | 1966-07-19 | Wasagchemie Ag | Method of manufacturing foamed silicate structures |
US3294496A (en) * | 1963-11-29 | 1966-12-27 | Union Carbide Corp | Metal ceramic compositions |
US3360846A (en) * | 1965-03-15 | 1968-01-02 | Herman J. Schellstede | Method of securing a collar on a pipe |
US3366463A (en) * | 1965-07-20 | 1968-01-30 | Siemens Ag | Sintered shaped structure formed of penetration-bonded metal, particularly for arcing electric contacts |
US3384464A (en) * | 1966-02-16 | 1968-05-21 | Mallory & Co Inc P R | Tungsten structures |
US3390026A (en) * | 1960-11-25 | 1968-06-25 | Nat Res Corp | Process of forming a protective coating on particulate material, and coated article obtained thereby |
US3949804A (en) * | 1973-03-26 | 1976-04-13 | Toyota Jidosha Kogyo Kabushiki Kaisha | Method of manufacturing a metal-impregnated body |
US3969553A (en) * | 1973-02-13 | 1976-07-13 | Toyota Jidosha Kogyo Kabushiki Kaisha | Method of manufacturing a metal-impregnated body |
US4314399A (en) * | 1976-01-28 | 1982-02-09 | Severinsson Lars M | Method of producing moulds |
US4471008A (en) * | 1981-08-21 | 1984-09-11 | Mtu Motoren-Und-Turbinen Union Munchen Gmbh | Metal intermediate layer and method of making it |
US4642027A (en) * | 1984-03-03 | 1987-02-10 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Method and structure for preventing the ignition of titanium fires |
US4659282A (en) * | 1984-03-03 | 1987-04-21 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh | Apparatus for preventing the spreading of titanium fires in gas turbine engines |
US5196273A (en) * | 1990-09-18 | 1993-03-23 | Noranda Inc. | Tantalum carbide composite materials |
US5630879A (en) * | 1994-07-22 | 1997-05-20 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh | Method and apparatus for the partial coating of sets of structural components |
US20060018760A1 (en) * | 2004-07-26 | 2006-01-26 | Bruce Robert W | Airfoil having improved impact and erosion resistance and method for preparing same |
US20070020134A1 (en) * | 2005-07-23 | 2007-01-25 | Rolls-Royce Plc | Method of making metal components |
US20080118355A1 (en) * | 2005-01-14 | 2008-05-22 | Cvrd Inco Limited | Turbine Vane for Turbo-Machines and Method for Fabricating |
US20090239058A1 (en) * | 2008-03-18 | 2009-09-24 | Stephen Craig Mitchell | Erosions systems and components comprising the same |
US11028486B2 (en) | 2018-12-04 | 2021-06-08 | General Electric Company | Coating systems including infiltration coatings and reactive phase spray formulation coatings |
Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2119989A (en) * | 1937-08-13 | 1938-06-07 | Higgins Ray | Metal coating for ceramic bodies |
US2325553A (en) * | 1941-04-14 | 1943-07-27 | Scovill Manufacturing Co | Refractory and method of producing the same |
GB661031A (en) * | 1947-12-16 | 1951-11-14 | American Electro Metal Corp | Improvements in parts for jet propulsion engines and their manufacture |
US2667427A (en) * | 1951-07-27 | 1954-01-26 | Gen Electric | Method of metalizing a ceramic member |
US2719095A (en) * | 1951-06-13 | 1955-09-27 | American Electro Metal Corp | Production of corrosion-resistant coatings on copper infiltrated ferrous skeleton bodies |
US2733167A (en) * | 1956-01-31 | Method of adhering gold to a non- | ||
US2751293A (en) * | 1951-07-31 | 1956-06-19 | Allied Prod Corp | Process of making perforated powdered metal article |
US2768099A (en) * | 1952-10-16 | 1956-10-23 | Gibson Electric Company | Method of making powdered compacts |
US2769611A (en) * | 1951-08-15 | 1956-11-06 | Schwarzkopf Dev Co | Gas turbine rotors and their production |
US2798577A (en) * | 1952-08-01 | 1957-07-09 | Eitel Mccullough Inc | Metalized ceramic structure for vacuum tube envelopes and method of making the same |
-
1956
- 1956-04-02 US US576230A patent/US2922721A/en not_active Expired - Lifetime
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2733167A (en) * | 1956-01-31 | Method of adhering gold to a non- | ||
US2119989A (en) * | 1937-08-13 | 1938-06-07 | Higgins Ray | Metal coating for ceramic bodies |
US2325553A (en) * | 1941-04-14 | 1943-07-27 | Scovill Manufacturing Co | Refractory and method of producing the same |
GB661031A (en) * | 1947-12-16 | 1951-11-14 | American Electro Metal Corp | Improvements in parts for jet propulsion engines and their manufacture |
US2719095A (en) * | 1951-06-13 | 1955-09-27 | American Electro Metal Corp | Production of corrosion-resistant coatings on copper infiltrated ferrous skeleton bodies |
US2667427A (en) * | 1951-07-27 | 1954-01-26 | Gen Electric | Method of metalizing a ceramic member |
US2751293A (en) * | 1951-07-31 | 1956-06-19 | Allied Prod Corp | Process of making perforated powdered metal article |
US2769611A (en) * | 1951-08-15 | 1956-11-06 | Schwarzkopf Dev Co | Gas turbine rotors and their production |
US2798577A (en) * | 1952-08-01 | 1957-07-09 | Eitel Mccullough Inc | Metalized ceramic structure for vacuum tube envelopes and method of making the same |
US2768099A (en) * | 1952-10-16 | 1956-10-23 | Gibson Electric Company | Method of making powdered compacts |
Cited By (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3390026A (en) * | 1960-11-25 | 1968-06-25 | Nat Res Corp | Process of forming a protective coating on particulate material, and coated article obtained thereby |
US3261894A (en) * | 1961-02-27 | 1966-07-19 | Wasagchemie Ag | Method of manufacturing foamed silicate structures |
US3294496A (en) * | 1963-11-29 | 1966-12-27 | Union Carbide Corp | Metal ceramic compositions |
US3360846A (en) * | 1965-03-15 | 1968-01-02 | Herman J. Schellstede | Method of securing a collar on a pipe |
US3366463A (en) * | 1965-07-20 | 1968-01-30 | Siemens Ag | Sintered shaped structure formed of penetration-bonded metal, particularly for arcing electric contacts |
US3384464A (en) * | 1966-02-16 | 1968-05-21 | Mallory & Co Inc P R | Tungsten structures |
US3969553A (en) * | 1973-02-13 | 1976-07-13 | Toyota Jidosha Kogyo Kabushiki Kaisha | Method of manufacturing a metal-impregnated body |
US3949804A (en) * | 1973-03-26 | 1976-04-13 | Toyota Jidosha Kogyo Kabushiki Kaisha | Method of manufacturing a metal-impregnated body |
US4314399A (en) * | 1976-01-28 | 1982-02-09 | Severinsson Lars M | Method of producing moulds |
US4471008A (en) * | 1981-08-21 | 1984-09-11 | Mtu Motoren-Und-Turbinen Union Munchen Gmbh | Metal intermediate layer and method of making it |
US4642027A (en) * | 1984-03-03 | 1987-02-10 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Method and structure for preventing the ignition of titanium fires |
US4659282A (en) * | 1984-03-03 | 1987-04-21 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh | Apparatus for preventing the spreading of titanium fires in gas turbine engines |
US5196273A (en) * | 1990-09-18 | 1993-03-23 | Noranda Inc. | Tantalum carbide composite materials |
US5630879A (en) * | 1994-07-22 | 1997-05-20 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh | Method and apparatus for the partial coating of sets of structural components |
US20060018760A1 (en) * | 2004-07-26 | 2006-01-26 | Bruce Robert W | Airfoil having improved impact and erosion resistance and method for preparing same |
US7186092B2 (en) * | 2004-07-26 | 2007-03-06 | General Electric Company | Airfoil having improved impact and erosion resistance and method for preparing same |
US7581933B2 (en) | 2004-07-26 | 2009-09-01 | General Electric Company | Airfoil having improved impact and erosion resistance and method for preparing same |
US20080118355A1 (en) * | 2005-01-14 | 2008-05-22 | Cvrd Inco Limited | Turbine Vane for Turbo-Machines and Method for Fabricating |
US7726023B2 (en) * | 2005-07-23 | 2010-06-01 | Rolls-Royce Plc | Method of making metal components |
US20070020134A1 (en) * | 2005-07-23 | 2007-01-25 | Rolls-Royce Plc | Method of making metal components |
US20090239058A1 (en) * | 2008-03-18 | 2009-09-24 | Stephen Craig Mitchell | Erosions systems and components comprising the same |
US20090236771A1 (en) * | 2008-03-18 | 2009-09-24 | Stephen Craig Mitchell | Methods for making components having improved erosion resistance |
US7875354B2 (en) | 2008-03-18 | 2011-01-25 | General Electric Company | Erosions systems and components comprising the same |
US7998393B2 (en) * | 2008-03-18 | 2011-08-16 | General Electric Company | Methods for making components having improved erosion resistance |
US11028486B2 (en) | 2018-12-04 | 2021-06-08 | General Electric Company | Coating systems including infiltration coatings and reactive phase spray formulation coatings |
US11946146B2 (en) | 2018-12-04 | 2024-04-02 | General Electric Company | Coating systems including infiltration coatings and reactive phase spray formulation coatings |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US2922721A (en) | Method for coating and infiltrating a porous refractory body | |
CA1138170A (en) | Method for the production of precision shapes | |
US2581252A (en) | Powder metallurgy articles | |
US6436470B1 (en) | Method of applying a hard-facing material to a substrate | |
EP0550439B1 (en) | Powder metallurgy repair technique | |
EP0339894B1 (en) | Method for making composite articles that include complex internal geometry | |
US3888663A (en) | Metal powder sintering process | |
US3353954A (en) | Method of producing compacts by reacting particulate ingredients | |
EP1860084B1 (en) | Method of making metallic composite foam components | |
US3752655A (en) | Sintered hard metal product | |
US6585930B2 (en) | Method for article fabrication using carbohydrate binder | |
US4568516A (en) | Method of manufacturing an object of a powdered material by isostatic pressing | |
US4060413A (en) | Method of forming a composite structure | |
KR930010150B1 (en) | Abrasive surface coating process for superalloys | |
US4104782A (en) | Method for consolidating precision shapes | |
US4883639A (en) | Method of manufacturing an object of a powdered material by isostatic pressing | |
US2828225A (en) | Methods of infiltrating high melting skeleton bodies | |
US2753261A (en) | Sintering process for forming a die | |
US2942970A (en) | Production of hollow thermal elements | |
US2714245A (en) | Sintered titanium carbide alloy turbine blade | |
US2843501A (en) | Method for the precision production of infiltrated articles | |
JPH08501500A (en) | Method for manufacturing ceramic-metal composite material | |
US2899338A (en) | Thermal element | |
US2714556A (en) | Powder metallurgical method of shaping articles from high melting metals | |
US2828226A (en) | Method of interstitially casting metal in high melting skeleton bodies |