CA2044775A1 - Duplex coatings for various substrates - Google Patents

Abstract

DUPLEX COATINGS FOR VARIOUS SUBSTRATES
Abstract of the Disclosure A duplex coating for substrates that comprises an undercoat of tungsten carbide-cobalt having a strain-to-fracture of greater than 4.3x10-3 inch per inch and a top coat of a ceramic material such as alumina in which the ratio of the thickness of the top coat to the undercoat is from 6:1 to 1:3.

Description

DUPL~ ATINGS ~OR Y~RIQ~ ~UBSTRATES

Field of ~he Invention The invention relates to a duple~ coating that eshibits good fatigue characteristics comprising an undercoat of tungsten carbide-c~balt with a top coat of a ceramic: material, such as alumina.
Backqround o_~he InYention A variety of rotary seals are used in gas turbine engines which are generally of the type including rotating members cooperating across a narrow gap with another member which is relatively stationary. Such seals are used, in some cases, between stationary members and a rotating shaft or drum for the purpose of maintaining different pressures in chambers on each side of the seal. For example, in one type of gas turbine engine, a plurality of rows of rotor blades e~tend radially outward from a rotor shaft across a flow path for the working medium gases. Collaterally, a plurality of rows of stator vanes e~tend radially inward across the flow path from a stator case or shroud.
In some types, the stator vanes are cantilevered inward from the stator case. The vanes are positioned to direct the working gases toward or away from the adjacent rotor blades. A stator has a sealing surface circumscribing the tips of blades in each row of blades and, in the cantilever stator vane types, the rotor is provided with a sealing sur~ace circumscribing the tips of the stator vanes in each stator vane row.

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As ~he clearance between ~he tips of the blades or vane-s in each row and the corresponding sealing surface is increased, substantial amounts of working medium gas escape circumferentially over the tips of the blades and/or st:ators, reducing the aerodynamic efficiency. Furthermore, when the clearance is increased, additional amounts of working medium gases leak a~sially over the tips from the downstream end to the upstream end of the blades or rotors. Therefore it is desirable to keep the clearance to a minimum. However, it is also necessary to accommodate various dimensional changes which occur during initial startup, thermal excursions, high G turns, etc. Generally, there is soma wear-in of the parts under these conditions, particularly during engine startup.
It is known that the more desirable condition is for the tips or knife edges to cut grooves into the corresponding sealing surface rather than for the tips or knife edges to sustain wear. U.S. Patents 4,238,170 and 4,239,452 provide the sealing surfac~ of the stator or shroud with interior circumferential grooves circumscribing the tips of the blades, but this arrangement presents alignment difficulties while failing to accommodate thermally-induced a~ial displacement of the blades relative to the stator or shroud.
A variety of rotary seal arrangements have been disclosed in the literature in which rotating members generate, cut or abrade a path in a softer, e.g., abradable, cooperating member such as filled ~~ honeycomb, porous metal, friable ceramic or the 3 ~ 7 7 ~
li~e. In $ome of these arrangements, ~t has been ~ound that inadequate sealing or seizing of the cooperating members can result. In other such arrangements, local ~hot-spots~ and burning of - 5 non-abrading members can result. E~amples of seals utilizing an abradable member are disclosed in U.S.
Patents 3,068,016; 3,481,715; 3,519,282; 3,817,719;
3,843,278; 3,918,925: 3,964,877; 3,975,165;
~,377,371 and 4,540,336. The abradable seal is adapted to flake off or abre~de, when there is a thermal transient or shock loading causing the blade tip to strike the seal. U.S. Patent 4,377,371 points out that certain materials used as abradable seals are vulnerable to large scale spalling propagated by the presence of cracks in the seal surfacP and discloses the glazing of the seal surface by the use o~ a laser beam to produce a fine micro-crack network in the seal surface. In a paper ~Development of Improved-Durability Plasma Sprayed Ceramic Coatings for Gas Turbine Engines~, presented by I.E. Sumner and D. Ruckle at the AIAA~SAE~ASME
16th Joint Propulsion Conference, AI M -80-1193, segmented laser scanned coatings were reported to perform poorly.
British Patents 853,314 and 1,008,526 disclose turbine or compressor blades formed with ribs on their tips for providing a seal with a rotor or stator shroud, the ribs or cooperating seal surface being removable when worn out. ~.S. Patent 4,148,494 discloses a gas turbine blade or vane having an abrasive tip comprising an electrodeposited matri~ of nickel or an alloy -, , ~tDining ni~kel in which are ~ntrapped abrasiv~
particles, e.g., borazon particles, protruding from the tip. Abrasive tips of the type described in this patent are difficult to produce and are estremely e~pensive. U.S. Patent 3,33~,933 discloses blade teeth coated with bonded alumina which e~pand into cooperating honeycomb members to form a seal. U.S. Patent 3,537,713 discloses a rotating sleeve having inwardly projecting teeth coated with a hard protective material, such as a molybdenum or nickel aluminide, which displaces a rub-resistant material on a stationary cooperating member to form alternate ridges and grooves.
U.S. Patent 4,884,820 discloses the laser treatment of the tip of a blade that was coated with a ceramic or metallic carbide coating to form a plurality of laser-formed depressions that produce a wear-resistant, cutting surface capable of cuttîng into an abradable material in a rotary gas seal.
Although the above coatings provide a good wear-resistant, cutting surface for blades, the coatings sometimes do not adhere sufficiently to the blades to remain bonded to the blades when used in high temperature environments. For e~ample, although ceramic coatings such as alumina-based coatings, provide good wear-resistant, cutting surfaces for many substrates, they do have poor bond strength to substrates such as titanium alloys.
However, if the substrate, such as a titanium alloy, is roughened by grit blasting w~th an abrasive material, such as alumina grit, then a good bond can be obtained for the ceramic coatings.

2'~3_ b Vnfortunately, tAe grit bla6t operation will generally cause a large fatigue debit to t~e substrate. Fatigue is the progressive phenomenon of failure that occurs in materials when they are subjected to cyclic loading at stresses having a ma~imum value less than the tensile strength of the materials. Fatigue can generally culminate in fracture after a sufficient number of cyclic loadings. Since fatigue causes materials to fail sooner and/or at lower loads than would be expected, its net e~fect has been to either shorten the useful life period of materials at the same load or reduce the allowable load for the same life period. Thus the use of grit blast is not desired since it can cause fatique debit in the substrate.
U.S. Patent 4,826,734 discloses substrates coated with tungsten carbide-cobalt coatings that have a strain-to-fracture of greater than 4.3xlO 3 inch per inch. However, although it will provide an adequate wear-resistant and cutting surface, the ceramic coatings generally provide a more desirable wear-resistant cutting surface for use in the tip of blades for compressors.
It is an object of the present invention to provide a duplex coating for substrates that has good fatigue characteristics whil~ also providing a ~ood wear-resistant cutting surface.
It is another object of the present invention to provide a duple~ coating for substrates such as titanium that comprises an undercoat of tungsten carbide-cobalt and a top coat of a ceramic ~~ coating.

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It is another ~bject of the present invention to provide a duple~ coating for titanium based substrates comprising an undercoat of tungsten carbide-cobalt having a strain-to-fracture greater than 4.3 x 10 3 inch per inch and a top coat of an alumina-based coating.
The foregoing and additional objects will become more apparent from the description and disclosure hereinafter.
S~MMARY OF THE INVENTION
The invention relates to a coated article comprising a substrate, such as a titanium alloy, having an undercoat layer of tungsten carbide-cobalt bonded to the substrate and a top coat layer of a ceramic material such as an alumina-based material secured to the undercoat layer. Preferably the tungsten carbide-cobalt undercoat should have a strain-to-fracture of greater than 4.3 ~ 10 3 inch per inch, preferably greater than 5.0 ~ 103 inch per inch and more preferably greater than 5.S g 103 inch per inch. The compressive residual stress of the tungsten carbide- cobalt undercoat should preferably be between about 30 to about 5p kilopounds per square inch (KSI). Preferably the undercoat layer should have a surface roughness of at least 100 microinch Xa so that the top coat can be sufficiently secured to the undercoat layer.
Preferably, the ratio of the top coat thickness to the undercoat thickness should be from 6:1 to 1:3;
and more preferably from 3:1 to 1:2.
It has been found that the novel duplex coating of this invention provides an undercoat :
.

~IL,1, loyer that h~s good bond ~trength to t~e ~ubstrate and good fatigue properties while the top coat provides a surface having e~cellent wear-resistant, cutting characteristics. Th~s good fatigue property of the undercoat will effectively prevent the propagation of any cracks in the top coat to the substrate when the coated sulbstrate is put in operation, particularly an operation where it is subjected to cyclic loading. Thus the duple~ coated substrate of this invention ~will survive longer under cyclic loading conditions than a coated substrate having only a coated layer of a ceramic material.
The undercoat layer of this invention has good fatigue properties and bond strength and can be deposited on a substrate by means such as the detonation gun process. The thickness of the undercoat layer has to be sufficient so that it can stop the propagation of any top coat cracks so that the fatigue properties of the substrate are not significantly lowered. For most applications the thickness of the top coat can be from at least 2 mils to about 20 mils, preferably at least 3 mils to about lO mils. The surface of the undercoat should have a roughness of at least lO0 microinch Ra, preferably at least 150 microinch Ra, so as to secure the top coat when deposited thereon.
The top coat of this invention should have a good wear-resistant, cutting surface and be capable of adhering to the undercoat layer so that it will not spall off when used in its intended operation. This top coat can be applied to the .

2 ~
undercoat using convention~l detonation gun proces~es. For most appli~ations, the thickness of the top coat should be sufficient so that it provides a good wear-resistant, cutting surface for its intended application. Generally a thickn~ss ~ from at least 1 mil to about 20 mils would be suitable with a thickness from at least 2 mils to about 10 to 15 mils being prleferred~
The tungsten carbid~e-cobalt undercoat layer should comprise from about 7 to about 25 weight percent cobalt, from about 0.5 to about 5 weiqht percent carbon, and from about 70 to about 92.5 weight percent tungsten. Preferably the cobalt should be from about 8 to about 18 weight percent, the carbon from about 2 to about 4 weight percent, and the tungsten from about 78 to about 90 weight percent. The most preferred coating would comprise from about 9 to about 15 weight percent cobalt, from about 2.5 to about 4.0 weight percent carbon, and from about 81 to about 8B.5 weight percent tungsten.
The tungsten carbide-cobalt coating material for the invention could include a small amount of chromium, preferably from about 3 to about 6 weight percent and most preferably about 4 weight percent. The addition of chromium is to improve the corrosion characteristics of the coating.
The top coat layer of ceramic would include alumina, compositions (which shall include alloys and mixtures) of alumina with titania, chromia, and/or zirconia; compositions of chromia and alumina; compositions of zirconia mixed with silica, yttria, calcia and/or magnesia; chromium carbide; and the like.

Pr~ferably the top coat would be alumina and compositions of alumina with titania, chromia, and/or ~irconia; with alumina being the most preferred.
The substrate could comprise titanium, aluminum, steel, cobalt, nickel, alloys thereof and the like. Preferably the substrate would be an alloy of titanium. When the substrate is a titanium alloy, the preferred top coating would be an alumina-based material such as alumina and the undercoat layer would be tungsten carbide-cobalt comprising from 7 to 25 weight percent cobalt, from O.S to 5 weight percent carbon, and from 70 to 92.5 weight percent tungsten. The thickness of the undercoat would be from 2 to 20 mils and the top coat would be from 1 to 20 mils. Generally, the ratio of the top coat layer to the undercoat layer would be from 6:1 to 3:1.
It has been found that with a titanium alloy substrate, the undercoat of tungsten carbide-cobalt will provide an excellent bond to the titanium alloy without effectively altering the fatigue properties of the titanium alloy while providing a surface having a roughness onto which ~he top coat can be secured. The top coat of the alumina-based material will provide an e~cellent wear-resistant, cutting surface that can be used in various applications under cyclic loading without failure. To further enhance the surface of the top coat, a laser treatment can be performed to provide a plurality of depressions defined by elevated land areas which can act as a collection of cutting ~ ~J~t7 edges. Further, the depressions ~efined by the land ~reas are balieved to enhance the cutting ability by providing space for receiving fine cutting debris when the duplex coated substrate is used as a blade in a compressor. Upon cooling, the tip of the blade -- would retract and the debris would be released ~rom the surface.
The preferred method for depositing the undercoat would be to flame plate with a detonation gun comprising the steps of introducing desired fuel and o~idant gases into the detonation gun to form a detonatable mi~ture, introducing a comminuted coating material into said detonatable mi~ture within the gun, and detonating the fuel-o~idant mi~ture to impinye the coating material onto a substrate to be coated. Prsferably the fuel-osidant mi~ture would comprise an o~idant and a fuel mixture of at least two combustible gases selected from the group of saturated and unsaturated hydrocarbons.
Preferably the o~idant employed would generally be ogygen and the combustible fuel mi~ture would be acetylene gas and propylene gas.
The powders of the coating material for use ~- in obtaining the undercoat layer are preferably powders made by the cast and crushed process. In this process, the constituents of the powders are melted and cast into a shell-shaped ingot.
Subsequently, this ingot is crushed to obtain the desired particle size distribution. The resulting powder particles contain angular carbides of varying sizes. Varying amounts of metallic phase are associated with each particle. This morphology causes the individual particles to have non-uniform melting chDracteristics. In ~act, under some 2~
coating conditions some of the particles containing some of the larger angular carbides may not melt at all. The preferred powder produces a coating having a polished metallographic appearance consisting of appro~imately 2-20% angular tungsten carbide particles, generally sized from 1 to 25 microns and distributed in a matri~ consisting o W2C, mi~ed carbides such as Co3W3C, and Co phases.
The powders of the coating material for use in obtaining the top coat are preferably powders made by calcining metal salts. The resulting powder particles should generally be sized in the range of 1 to 45 microns.
In the testing of coated samples, various data were observed and some of the data were obtained using the following test procedures.
Strain-T~-Fra~ture Test The strain-to-fracture of the coatings in the e~amples was determined by using a four point bend test. Specifically, a beam of rectangular cross-section made of 4140 steel hardened to 40-45 Hardness Rockwell C scale (HRC) is coated on one side with the material to be tested. The typical substrate dimensions are 0.50 inch wide, 0.25 inch thick and 10 inches long. The coating area is 0.50 inch by about 7 inches, and is centered along the 10 inch length of the substrate. The coating thickness is typically 0.015 inch, although the applicability of the test is not affected by the coating thickness - in the range between 0.010 to 0.020 inch. An acoustic transducer is attached to the sample, using t a couplnnt suGh as Dow Corning hiyh ~ac~um grease, ~nd masking tape. The acoustic transducer is piezoelectric, and has a narrow response band located approsimately between 90 and 120 KHz. The transducer is attached to a preamplifier with a fised gain of 40 dB which passes the signal to an amplifier with its gain set iat 30 dB. Thus the total system gain is 70 dB. The amplifier is attached to a counter which counts the number of times the signal e~ceeds a threshold value of 1 millivolt, and outputs a voltage proportional to the total counts. In addition, a signal proportional to the peak amplitude of an event is also recorded.
The coated beam is placed in a bending fi~ture. The bending fi~ture is designed to load the beam in four point bending with the coating in tension. The outer loading points are 8 inches apart on one side of the beam, while the middle points of loading are 2-3/4 inches apart on the opposite side of the substrate. This test geometry places the middle 2-3/4 inches of the coated beam in a uniform stress state. A universal test machine is used to displace the two sets of loading points relative to each other, resulting in bending of the test sample at the center. The sample is bent so that the coating is convex, i.e., the coating is placed in tension. During bending the deformation of the sample is monitored by either a load cell attached to the universal test machine or a strain gage attached to the sample. If the load is measured, engineering beam theory is used to ~~ calculate the strain in the coating. During bending, the acoustic counts and peak amplitude are also recorded. The data are simultaneously collected with a three pen chart recorder and a computer. When cracking of the coating occurs, it is accompanied by acoustic emissionO The signature of acoustic emission associated with through-thickness cracking includes about 104 counts per event and a peak amplitude of 100 dB
relative to 1 millivolt at the transducer. The strain present when cracking begins is recorded as lo the strain-to-fracture of the coating.

Residual Stress Test The residual stress of the coatings in the examples was determined using a blind hole test.
The specific procedure is a modified version of ASTM
Standard E-387. Specifically, a strain gage rosette is glued onto the sample to be tested. The rosatte used is sold by Texas Measurements, College Station, Texas under its trademark FRS-2. This device consists of three gages ~oriented at 0, 90 and 225 degrees to each other and mounted on a foil backing. The centerline diameter of the gages is 5.12 mm (0.202 in), the gage length is 1.5 mm (0.059 in), and the gage width is 1.4 mm (0.055 in). The procedure to attach the rosette to the sample is as recommended in Bulletin B-127-9 published by Measurements Group Inc., Raleigh, North Carolina. A metal mask is glued onto the strain gage to help position the hole at the time of drilling and to protect the strain gage during the drilling of the hole. The mask has an annular geometry, having an outer diameter equal to 0.382 inch, an inner diameter equal to 0.160 inch, and a thickness of 0.0485 inch. This mask is ~' ~ $i ~, A~
positione~ to be csncentric with the ~train g~ges, using a microscope at `6~. When it--is center~d, a drop of glue is applied at the edges and allowed to dry, fi~ing the mask in placle. The three gages are hooked up to three identical signal conditioners, which provide B reading in units of strain. Prior to starting a test, all three units are adjusted to give zero readings.
The test equipment includes a rotating grit blast nozzle mounted on a plate which can travel vertically and in one direction horizontally. The grit blast nozzle is made by S.S. White of Piscataway, New Jersey, and has an inner diameter of 0.026 in~h and an outer diameter of 0.076 inch. The nozzle is offset from its center of rotation, so the result is a trepanned hole with a diameter between 0.096 and .1002 inch. The sample to be drilled is placed in the cabinet, and the strain gage is centered under the rotating nozzle. Positioning of the part is accomplished by rotating the nozzle with no flow of either abrasive media or air, and manually adjusting the location of the sample so that the nozzle rotation is concentric with the mask. The standoff between the nozzle and the part is set at 0.020 inch. The location of the plate is marked by stops. The abrasive used to drill the holes is 27 microns of alumina, carried in air at 60 psi. The erodent or abrasiv~ media is used at a rate of 25 grams per minute ~gpm~. The abrasive is dispensed by a conventional powder dispenser. The hole is drilled for 30 seconds, at which time the -- flow of the abrasive and air is stopped. The nozzle ~ Q~
is ~oved away from the part. The positions at the top of the strain gage and the bottom of the hole are measured with a portable focusing microscope and the difference recorded. The depth of hole is the difference minus the thickness of the strain gage.
The strain released around the hole is indicated by the signal conditioners, and these values are also recorded. The sample is not moved during the recording of data, so the nozzle can be brought back to its initial starting point and the test continued.
The test is repeated until the hole depth is greater than the thickness of the coating, at which time the test is terminated. The strain released in an incremental layer at a given hole lS depth is related to the stress in that layer empirically, using data from a calibration sample of mild steel loaded to a known stress state. From this data the residual stress is determined.
The correlation between the strain-to-fracture and the residual stress o a coating is as follows. When the material is under a combined set of loads, the stresses and strains from each of the loading conditions may be calculated, and the total stress and strain map may be determined by superimposing the stresses resulting from each load. Applying this fact to coatings, the residual stress in the coating must be added to the stress applied during the four point bend test to determine the actual stress state of the coating at the time that fracture occurs. The four point bend test is run such that the coating is plac~d in tension. Thus, using the fact that stress and 2 ~ 7 ~
~tr~in are relsted by a constant, ~he total ~tr~ss in a coating at failure is actually ~iven ~y ~t EEf ~ ~r (eg~ 1) ~t ~ applied stress - 5 E ~ coating elastic modulus Ef - strain-to-fracture from four point bend test ar ' coating rlesidual stress, measured from blind hole test (by convention com-pressive stresses are negative values~
In general, the coating will crack at a constant value of stress, regardless of whether that stress came about as a result of residual or applied stress or a combination of the two. A coating with a given compressive residual stress must be subjected to an equal amount of applied tensile stress before the coating is placed in tension.
Rearranging eq. 1 to e~press the strain-to-fracture as a function of residual stress, it is apparent that an increased compressive stress in a coating will result in an increased strain-to-fracture of the coating~

~f ~ (~t ~ ~r) (eq. 2) E
Thus, the stress or strain which can be applied before the coating fractures is affected by the amount of residual stress or strain present in the _ ~oating.
Additional information on the blind hole test for measuring residual stress can be found in the publication titled Residual Stress in Design, Process and Materials Selection, published by ASN
International, Metals Park, Ohio. This publication contains an article given by L.C. Cox at the ASM
Con~erence of the same title on April 27-29, 1987 in Cincinnati, Ohio.
Bond Strenqth Test The bond strength of the coating to the substrate was determined using the method disclosed in ASTM 633 except that the coating layer was a thinner layer.
Specifically, the coating to be tested was deposited on a set of six cylindrical bond test specimens, each measuring 1 inch in diameter. The surface of the coated layer was ground with a diamond wheel to provide a smooth surface normal to the axis of the cylinder.
The cylindrical specimens were then each secured to a matching uncoated cylindrical specimen using an epoxy adhesive, sold under the Trade Mark "SCOTCH-WELD EPOXY
ADHESIVES 2214 NON-METALLIC" by the 3M Corp. This epoxy adhesive is composed of the following:
Inqredients Percent epoxy resin blend 70.0 - 80.0 aliphatic glycidyl ether 1.0 - 10.0 nitrile latex 1.0 - 10.0 dicyandiamide 1.0 - 10.0 3-p-chlorophenyl)-1,1-dimethyl urea 1.0 - 10.0 amorphous silicon dioxide 1.0 - 10.0 water 1.0 - 10.0 ~fter curing the epoxy, *h~ cylindrical ~pecimens were pulled apart to rupture ~n~ the load at rupture was observed. After this test each coated cylindrical specimen was inspected to determine whether the rupture occurred in the coated bonded area or the epo~y bonded area.
Fatiaue Test The fatigue specimens were machined into cylindrical test b~rs measuring 3.5 inches in length with segment portions at each end measuring 0.8 inch in length and having a 0.6 inch diameter. The inner portion of each end segment was inwardly tapered to produce a central segment measuring 0.75 inch in length with a 0.25 inch diameter. The central segment is referred to as the gage section of the test bar. A coating is applied to the gage section and the onwardly tapered segments using a detonation ~un. The coating is tested in its ~as-coated"
state, preserving the natural surface roughness of the coating. The atigue test is conducted as an a~ial tension-tension test with a minimum to ma~imum stress ratio R of 0.1. The test is conducted in air at ambient temperature on a simple load-controlled, a~ial fatigue testing machine at 30 Hz. For all specimens, the ma~imum stress was derived as the ma~imum load over the gage cross-section of the substrate material. Each test was run until the specimen fractured in the gage section (gage section failure . GSF) or until ten million cycles were reached (run out ~ RO).
Some e~amples are provided below to illustrate the present invention. In these ~amples, ~oatings ~ere ma~e using the powder compositions ~hown in Table 1.

TABLE l ~oatinq Materisl_~Q~5~

53mple CQm~Qsi~ion - wt X _ PQ~der Si~e Powder Al O Co C Fe Other ~ % thru ~ksh~ ~ax. X Df Min. Si~e ~ _ .
A - 9.0 to 4.3 to1.5 0.3 Bal. 95X thru lOX less than 5 Cast & 10.0 4.B~ax. nax. 325 ~icrons Crushed 99.1X - - _ - 99X thru min. 325 U.S. Standard Hesh Size.

EXAMPLE~I
The gaseous fuel-oxidant mixtures of the compositions shown in Table 2 were each introduced to a detonatîon gun to form a detonatable mixture having an o~ygen to carbon atomic ratio as shown in Table 2. The sample coating powder as shown in Table 2 was also fed into the detonation gun. The ~0 flow rate of each gaseous fuel-o~idant mi~ture, the feed rate of each coating powder, the gaseous fuel-mi~ture in volume percent, and the atomic ratio of o~ygen to carbon for each coating e~ample are also shown in Table 2. The coating sample powder was fed into the detonation gun at the same time as the gaseous fuel-oxidant mi~ture. The detonation gun was fired at a rate of about 8 times per second and the ~oating powder in the detonation gun was .- impinged onto a variety of steel and titanium su~trates to form a dense, adherent coating of 6haped microscopic leaves interlocking ~nd overlapping with each other.
The percent by weight of the cobalt and carbon in the coated layer of Sample Coatings 1 and 2 were determined along with the hardness of the coating. The hardnesses of the Sample Coatin~s 1 thru 3 in Table 2 were measured using a Rockwell superficial hardness tester and Rockwell hardness numbers were converted into Vickers hardness numbers. The Rockwell superficial hardness method employed is per ASTM standard method E-18. The hardness is measured on a smooth and flat surface of the coating deposited on a hardened cteel substrate. The Rockwell hardness number was converted to a Yickers hardness number by the following formula:
HVo 3 - -1774 ~ 34.433 HR45N

where HVo 3 designates a Vickers hardness obtained with 0.3 kgf load and HR45N designates the Rockwell superficial hardness obtained on the N scale with a diamond penetrator and a 45 kgf load.
The strain-to-fracture values and the residual stress values were obtained as described above and the data obtained are shown in Table 2.

' 7 ~ ~

C
L ~ N
3~ ~
., V
~, o o~

.. ~ o ~ C
~ ~ a ~ 9~
U , ~ ,S~ ~D ~,~ e I ~
z~ I æ~

~0 ~q C C C~ o 10 L

L~

..

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Qne inch dinmeter test bars of Ti-6Al-4V
were coated at their end face using the same method and powder composition as was used for Sample Coating 3 of Esample I. Each cylindrical bar ~as then secured to a mating bar along its longitudinal axis using SCOTCH-WELD eposy adhesive. After the epo~y was cured, the two cylindrical bars were pulled apart to rupture and t:he load at rupture was recorded for each sample. The test bars were then e~amined to determine if the rupture occurred at the coated bonded area (referred to as coating to substrate bond - CSD) or at the eposy bonded area (Epo~y). The thickness of the coating, the bond strength to rupture and the type of ruptu~e observed are shown in Table 3.
TA8~E 3 Bond Strenath of Power B Coated S~bstrat~
Sample Coating Bond Rupture SPecimen ThicknessSt~enath TYpe (inch) (PSI) 1 0.0067 4,762 CSD
2 0~0066 2,979 CSD
3 0.0069 3,731 CSD
4 0.0073 7,334 CSD
0.0065 8,518 CSD

6 0.0067 5,373 CSD
Avg. 5,450 ~ .

- 23 ~

~AMPLE III
One inch diameter test-bars of Ti-6Al-4V
were coated at their end face using the ~ame method and powder composition as was used for Sample Coating 2 of E~ample I. In addition, a top coat was applied using the same method and powder composition as was used for Sample Coating 3 of ~ample I. Each duplex coated cylindrical bar was then secured to a mating bar along its longitudinal a~is using SCOTCH-WELD epo~y adhesive. After the eposy was ~ured, the two cylindrical bars were pulled apart to rupture and the load at rupture was recorded or each sample. The test bars were examined to determine if the rupture occurred at the coated bonded area (CSD) or at the epo2y bonded area (Epo~y). The thickness of each coated layer, the bond strength to rupture and the type of rupture observed are shown in Table 4. There was some minor edge chipping of the coating. The averaye bond strength of the duplex coating of this invention was far superior to the average bond strength of the samples shown in E~ample II.

- ~ - 24 -~L~ 4 ~ond ~tren~LQf ~u~ Qat~d Su~stra~

Undercoat Top Coat ~ample Coating Coating ~ond Rupture fiPecimen (inch) Thick ess stren~th Tv~e 1 0.0005 .006610,963 chipping 2 0.0005 .006811,485 Epoxy 3 0.0005 .006412,274 Epo2y + edge chipping 9 0.0005 .006510,759 Epo~y ~ edge chipping 0.0005 .006613,178 Epoxy + edge chipping Avg. 11,732 .

' ~MPL~ IY
One inch ~iameter test bars of Ti-6Al-4V
were coated at their end face using the same method and powder ~omposition as was used for Sample Coating 1 of Example I. In addition, a top coat was supplied using the sams method and powder composition as was used for Sample Coating 3 of Example I. Each duplex coated cylindrical bar was then secured to a mating bar along its longitudinal axis using SCOTCH-WELD epo~y adhesive. After the eposy was cured, the two cylindrical bars were pulled apart to rupture and the load at rupture was recorded for each sample. The test bars were e~amined to determine if the rupture occurred at the coated bonded area (CSD) or at the eposy bonded area (Epoxy). The thickness of each coated layer, the bond strength to rupture and the type of rupture observed are shown in Table 5. In some instances, there was some minor edge chipping of the coating.
The average bond strength of the duple~ coating of this invention was far superior to the average bond strength of the samples shown in Example II.

,.

_ 26 - 2~

TA~LE 5 ~pnd Stren~th Qf DuPle~ Coated S~strate Undercoat Top Coat Sample Coating Coating Bond ~upture Speci~en Thickne6~ Thicknes6 ~ n~5h Tv~e (inch) (inch) (PSI) 1 0.0005 .0094 11,867 ~poxy 2 0.0005 .0093 11,612 Epoxy I ed8e chipping 3 0.0005 .0088 10,797 Epoxy 4 0.0005 .0090 11,561 Epoxy ~ edge chipping 0.0005 .0105 . 9,140 Epoxy 6 0.0005 .0088 10,975 Epoxy Avg. 11,510 ~-16010 ' : ~.- ~; ., ''; ~

;
. .

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- 27 ~ , ~AMP~E V
F~tigue test bars made of Ti-6-4 ~lloy made as described above were coated on their central or gage portions with the coatecl composition of ~ample Coating 1, 2 or 3 of E~ample I using the process and gaseous fuel mi~ture as shown in Table 2 for Sample Coating 1, 2 or 3, respectively. Additional ~atigue test bars were coated on their gage portions with an undercoat of the coated composition of Sample Coating 1 or 2 over which was deposited the coat~d composition of Sample Coating 3 of E~ample I. These test bars were coated with different thicknesses of the coated composition of Sample Coating 1, 2 or 3 of Example I, as shown in Table 6. Prior to coating, the test bars were not grit blasted, with the exception of the test bars coated only with the Sample Coating 3 of Table 2 of E~ample I, which were grit blasted with 60 mesh angular particles of alumina to promote a good bond strength between the Sample Coating 3 and the test bars. Together with some uncoated fatigue bars, the coated fatigue bars were subjected to the fatigue test as described above. Table 6 shows the maximum stress each individual bar was subjected to and the number of cycles it sustained before the bar broke in fatigue in the gage portion or if it did not break after 107 cycles, then the test was interrupted and described as a run-out.
The data from Table 3 of E~ample 11 shows that test bars coated with A12O3 all ruptured at the coated bonded area while the data from Table 4 ~~ of E~ample III shows that the test bars coated .

- 28 ~

~ith a duples coating in accordance ~ith this invention ruptured at the epo~y ~onded area ana not the coated bonded area. These tests demonstrate that the A12O3 coating did not adhere effectively to the substrate when it was u~ed as a single coating but did adhere effectively to a tungsten carbide-cobalt undercoat as shown in Esample III. Thus, although A12O3 coatings provide a good wear-resistant cutting surface for blades, the coatings sometimes do not adhere sufficiently to the blades to remain bonded to the blades when used in their intended applications.
However, if the substrate, such as a blade is first coated with a tungsten carbide-cobalt undercoat and then coated with a A12O3 coating, the A12O3 coating will adhere to and provide a good bond with the undercoat layer. This can be accomplished without the need for grit blasting the substrate which could cause a large fatigue debit to the substrate.
The data in Table 2 shows that a coating applied using the combination of two combustible gases gave better strain-to-fracture and residual stress than a coatiny which was applied using a conventional detonation gun process using only one combustible gas. In Table 6, Test Bar 16 was made using a conventional detonation process of only one combustible gas and survived 1.86 x 105 cycles at a stress o S0 RSl. ~he same coating composition and thickness of the layers of the duplex coating were also applied using a detonation gun process -- using two combustible gases ~Test Bar 18) and this - ~9 -r7 >~ ~3 Test Bar lS ~urvived 1.~166 s 107 cys:les at a stress of 50 KSl. Thus the process used to deposit the undercoat on the substrate should be selected to insure that the undercoat of tungsten carbide-cobalt has a strain-to-fracture of greater than 4.3 10 3 inch per inch.
It is to be understood that although the present invention has been described with reference to particular details thereof, it is not intended that these details shall be construed as limiting the scope of this invention.

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Claims (14)

1. A duplex coating for use on substrates comprising an under coat of tungsten carbide-cobalt with a strain-to-fracture of greater than 4.3 x 10-3 inch per inch and a top coat of a ceramic material in which the thickness ratio of the top coat to the undercoat is from 6:1 to 1:3; wherein the tungsten carbide-cobalt under coat has a cobalt content of from about 7 to about 25 weight percent, a carbon content from about 0.5 to about 5 weight percent and tungsten content of from about 70 to 92.5 weight percent; a roughness of at least 100 microinch Ra and a thickness of at least 2 mil and the top coat is at least one mil thick.

2. The duplex coating of claim 1 wherein the thickness ratio of the top coat to the undercoat is from 3:1 to 1:2.

3. The duplex coating of claim 1 wherein the tungsten carbide-cobalt undercoat has a strain to fracture of greater than 5.0 x 10-3 inch per inch.

4. The duplex coating of claim 1 wherein the ceramic material is an alumina based material.

5. The duplex coating of claim 1 wherein the ceramic material is selected from the group comprising alumina, composition of alumina with at least one member selected from the group consisting of titanium, chromia and zirconia; compositions of chromia and alumina; composition of zirconia with at least one member selected from the group consisting of magnesia, silica, yttria, and calcia; and chromium carbide.

6. The duplex coating of claim 1 wherein said undercoat contains up to 6 weight percent chromium.

7. The duplex coating of claim 1 wherein said undercoat contains from about 3 to about 5 weight percent chromium.

8. The duplex coating of claim 1, 7 or 8 wherein the cobalt content is from about 8 to about 18 weight percent, the carbon content is from about 2.0 to about 4.0 weight percent and the tungsten content is from about 78 to about 90 weight percent.

9. The duplex coating of claim 1 wherein said undercoat is from 2 mils to 20 mils inch thick and said top coat is from 1 mil to 20 mils thick.

10. The duplex coating of claim 1 for use on a substrate selected from the group comprising titanium, steel, aluminum, cobalt, nickel and alloys thereof.

11. The duplex coating of claim 10 wherein the substrate is a blade.

12. The duplex coating of claim 11 wherein the blade is coated at its tip.

13. The duplex coating of claim 11 wherein the blade is a titanium blade and the top coat is an alumina based material.

14. The duplex coating of claim 10 wherein said undercoat contains up to 6 weight percent chromium.
16010AC.CFO