METHOD OF REPAIRING DAMAGES IN SUPERALLOYS

Abstract: A method of repairing damages in a superalloy component is disclosed wherein existing brazed joints and protective coatings are not harmed. The method entails the use of a silicon-­ free metal mixture comprising (i) a low melting alloy hav­ ing a liquidus below the temperature to be used to deposit the metal mixture, (ii) an alloy melting above about 2100 o F, and (iii) optionally nickel. The resultant repair has a solidus temperature of at least 1950 o F, preferably at least 2000 o F.

Description: This invention relates generally to the use of silicon-free metal alloy powder mixtures for filling holes and slots and repairing and reforming damaged surface areas in high temperature engine components. In particular, the invention uses novel metal alloy mixtures which have the ability to repair many service damaged components which are presently considered non-repairable. Also, the present metal alloy powder mixtures can be used in new part fabrication and/or for the reformation of eroded or damaged surface areas, such as the tips of unshrouded blades. The alloy powder mixtures are used in a novel method for filling large holes, slots and widegap joints, or reforming extended surface areas, which method yields metal deposits with remelt temperatures (i.e., solidus temperatures) substantially greater than those produced by previous filling or repairing or brazing techniques. It has become increasingly important, especially in high temperature aircraft applications such as, for example, in turbine engine components, to use materials for structural applications that are capable of withstanding the combination of both high temperatures and corrosive attacks normally associated therewith. Stainless steels and the so-called superalloys, such as nickel-base superalloy, have been employed where possible to meet requirements of high strength to weight ratios, corrosion resistance, etc. at elevated temperatures. However, the greatest impediment to the efficient use of these materials has been the difficulty in repairing of service damaged components. Generally speaking, known brazing filler metal materials do not have the desired properties that are necessary for use in filling relatively large holes, slots and widegap joints and various other types of defects in high temperature superalloys such as those used in turbine engine high temperature components. In addition, known alloy powders and mixtures are completely unsatisfactory for rebuilding or reforming surface areas of high temperature superalloy bodies, such as blade tips, and therefore they are not intended for such use. As a result, superalloy bodies such as engines which develop these types of defects lose efficiency, and parts, many of which are very expensive, must be scrapped. In addition to these problems and disadvantages, conventional brazing filler metals do not simultaneously give good wetting, very limited flow, and the ability to bridge defects so that the defects are repaired without filler material flowing into internal passages in the components. This is as expected because brazing filler metals are designed to flow into spaces via capillary action, i.e., they liquify at the processing or use temperature and are drawn into the joint interfaces being united. Furthermore, known brazing filler compositions do not have the above desired properties along with the ability to provide both excellent high temperature and corrosion resistance and, when properly coated, survive in the harsh environment of a turbine engine. Thus, there is a great need for proper metal alloy mixtures that can be used to repair and/or rebuild surface areas of high temperature superalloy bodies and for techniques of using these mixtures for these purposes. Previously, repair of high temperature superalloys has been attempted with brazing filler metal compositions but these materials, some of which are disclosed in US-A-4,381,944, US-A-4,379,121, US-A-4,394,347, US-A-4,442,968, US-A-4,444,353, and US-A-4,478,638 have been found ineffective for the reasons stated above. US-A-4,285,459, US-A-4,381,944 and US-A-4,478,638 relate to alloy powder mixtures formulated to melt and flow into small cracks in superalloy bodies under vacuum conditions and at processing temperatures above about 2124°F and up to about 2250°F but below the remelt temperature of preexisting brazes. This is similar to conventional brazing or soldering, requires the use of high processing temperatures which can damage the superalloy body and/or superalloy coatings thereon, and does not permit the alloy powder composition to retain its shape and location on the superalloy body during processing so that surface reformtion, such as blade tip reformation, can be made and large cracks can be filled and bridged without run-off or run-in. EP-A-75497 discloses a process for assembling and repairing pieces of superalloys by brazing and diffusion whereby the powder mixture in one of the examples comprises 75 weight percent of a powder similar in composition to that of the superalloy and 25 weight percent of a lower melting powder consisting of 15 percent chromium, 3.5 percent boron and the rest nickel. A first aspect of the present invention provides a method for repairing damaged superalloy bodies which comprises (a) applying directly into holes or slots or widegap joint damages on such bodies or reconstructing damaged, missing or worn surface extensions of such bodies, such as blade tips, a semi-solid, form-retaining, silicon-free metal alloy powder mixture capable of being processed at a temperature of between about 1090°C and 1150°C (about 2000°F and 2100°F), said metal alloy mixture consisting of (i) from 55 to 90 per cent by weight of a first, lower melting, nickel-base superalloy powder composition consisting of from 14 to 16 weight percent chromium, from 2.5 to 3.2 weight percent boron and the balance nickel, said lower melting composition having a liquidus above about 980°C (1800°F) and below about 1090°C (2000°F): (ii) from 10 to 40 percent by weight of a second, higher melting, nickel-base superalloy powder composition consisting of from 38 to 67 weight percent nickel, from 11 to 15 weight percent chromium, from 8 to 12 weight percent cobalt, from 3 to 10 weight percent tungsten, from 3.5 to 10 weight percent tatanlum, amounts less than 5.0 weight percent each of titanium, aluminum, molybdenum and hafnium, amounts less than 0.5 weight percent each of carbon and zirconium, and from 0.0005 to 0.025 weight percent boron, said higher melting composition having a liquidus above about 1200°C (2200°F) but below about 1260°C (2300°F); and (iii) from 0 to 20 percent by weight, less than the amount of said higher melting composition (ii), of nickel powder, (b) heating said applied metal alloy powder mixture to a processing temperature between about 1090°C (2000°F) and 1150°C (2100°F) for a sufficient time to cause the lower melting power (i) to melt and alloy with the higher melting powder (ii), and with the nickel powder (iii), if present, for forming a semi-solid high viscosity, high surface-tension, form-retaining composition having a solidus temperature of at least about 1065°C (1950°F), and (c) cooling said processed composition to form a sound, non-porous deposit which fills and bridges the holes, slots and widegap joints and retains substantially the same shape on a superalloy body being repaired before and after processing. Other aspects and preferred features of the invention are set forth in the accompanying claims. After step (b) the assembly may be heated further at or below the processing temperature to allow chemical homogenization of the metal mixture to occur. Preferably step (b) is conducted under a vacuum or an inert or hydrogen atmosphere. The metal mixture preferably includes an organic binder. The powder composition has a processing temperature above about 1090°C (2000°F) but below about 1150°C (2100°F), preferably about 1120°C (2050°F), at which temperature the low melting alloy powder melts and wets the high temperature alloy to form a non-flowing, semi-solid, putty-like composition having a high viscosity and high surface tension. These critical properties enable the composition to be processed at a relatively low temperature of 1090°C (2000°F) to 1150°C (2100°F) which will not damage the superalloy body being repaired, or superalloy coatings thereon. Moreover, these critical properties enable the composition to retain its shape and location, as applied to the body prior to processing, without flowing onto adjacent surface areas during processing, so that the composition can bridge large surface holes or routed-open cracks and can substantially retain its applied shape when applied and processed to reconstruct a portion of the body which has been eroded, corroded or routed away or otherwise is no longer present on the superalloy body being repaired, such as the worn off tip of a turbine blade. For these reasons the present composition are not satisfactory for repairing or filling small unrouted cracks in superalloy bodies since the present compositions will not flow into such cracks during processing. The repair of such small cracks with the present compositions requires the routing of the small cracks to enable the composition to be applied directly to the areas to be repaired as a putty which substantially retains its shape and location during processing to fill and bridge the routed areas without any flow therefrom or thereinto. Techniques are being developed to repair gas turbine engine nickel-base alloy components, e.g., nozzels, that have thermal fatigue cracks and/or surface degradation both of which result from engine operation. The surface degradation can be the result of many reasons such as oxidation, hot-corrosion or erosion. In repairing the degradation, typically the damaged areas are first ground out to remove all of the undesirable material and leave a relatively clean surface after cleaning. The ground out areas are then directly filled with a filler metal slurry and then vacuum processed by a specific temperature cycle. The ground out areas are preferably nickel plated before vacuum processing if the base metal contains a high level of titanium and/or aluminum. To avoid damage to existing brazed joints and any protective surface coating, e.g., nickel-aluminide, of the component to be repaired, a filler metal with a relatively low liquidus temperature has been employed. In the prior use of the above-described technique for repair, the solidus or remelt temperature of the filler metal deposit was identical to the solidus of the original filler metal. For this reason, only those components with operating temperatures below the solidus temperature of the filler metal were repairable by prior methods. In order to overcome this problem, i.e., to raise the solidus temperature of the deposits while keeping the deposition temperature below that which would cause damage to existing brazed joints and any protective coating, a novel powder metal mixture and method of using that mixture has been developed and are described herein and form the basis for the present invention. Moreover, the present invention makes it possible, for the first time, to repair or reconstruct superalloy bodies or components which previously had to be discarded because extended surface portions thereof, such as unshrouded turbine blade tips, had been corroded, eroded or otherwise worn away. This is made possible by the alloy powder mixtures which can be formulated to a putty-like, semi-solid consistency which is moldable as an extension onto a superalloy body to form a replacement for the missing surface extension thereof, and which retains its molded shape during heat processing, without flowing or running, to form an integral superalloy body extension which can be machined to a final desired shape and coated if necessary to restore the superalloy body for reuse at service temperatures up to about 1090°C (2000°F). Any suitable superalloy metal body may be filled using the novel filler metal powder mixtures described herein. It is preferred that such filling be conducted by a vacuum processing technique. Suitable metal bodies include for example, nickel-base superalloys that are typically used in turbine engine components, among others. While any suitable temperature resistant superalloy body may be repaired using the filler metal mixture of this invention, particularly good results are obtained with nickel-base superalloys. The silicon-free metal powder mixture comprises a mixture of (i) the powdered relatively low melting nickel-base alloy discussed hereinbefore, which is silicon-free and contains 2.5 to 3.2 weight percent of boron as a melting point depressant, (ii) the powdered silicon-free nickel-based alloy melting above about 1200°C (2200°F) discussed hereinbefore, and optionally (iii) powdered nickel. The metal mixture will comprise 55 to 90 percent by weight low melting alloy, 10 to 40 percent by weight high melting alloy, and 0 to 20 percent by weight nickel. More preferably, the mixture will comprise 60 to 85 percent by weight low melting alloy, 15 to 40 percent by weight high melting alloy, and 0 to 15 percent by weight nickel. Still more preferably, the mixture will comprise 63 to above 82 percent by weight low melting alloy, 18 to 37 percent by weight high temperature alloy, and 0 to 12 percent by weight nickel. Most preferably, the mixture will comprise either (i) 68 to 72 percent by weight low melting alloy, 18 to 22 percent by weight high temperature alloy, and 8 to 12 percent by weight nickel or (ii) 63 to 67 percent by weight low melting alloy and 33 to 37 percent by weight high temperature alloy. The low melting alloys useful herein are those nickel-based alloys which have liquidus temperatures above about 980°C (1800°F) but below about 1090°C (2000°F) and below the processing temperature of about 1090°C-1150°C (2000°-2100°F) to be used. Preferably, the liquidus temperature will be in the range of about 1050°C (1925°F) to about 1080°C (1975°F). In addition, the alloy must be silicon-free. The alloy contains a critical amount of boron as the melting point depressant and comprises from 14 to 16 percent, most preferably 15 percent, by weight chromium, from 1.5 to 3.2 percent most preferably 2.8 percent by weight boron, and the balance nickel, most preferably 82.2 percent by weight. The preferred silicon-free high melting alloys useful herein are those nickel-based alloys disclosed in US-A-3,807,993, which melt above about 1200°C (2200°F). Such alloys have the composition disclosed hereinbefore and contain nickel, aluminum, boron, carbon, chromium, cobalt, hafnium, molybdenum, zirconium, tantalum, titanium and tungsten. Examples of such commercially-available alloys include C101 in a powder form. Most preferably, the high temperature alloy will comprise 12.2 to 13% chromium, 8.5 to 9.5% cobalt, 3.85 to 4.5 tantalum, 3.85 to 4.5% tungsten, 3.85 to 4.15% titanium, 3.2 to 3.6% aluminum, 1.7 to 2.1% molybdenum, 0.75 to 1.05% hafnium, 0.07 to 0.2% carbon 0.03 to 0.14% zirconium, 0.01 to 0.02% boron, and the balance nickel, all percents being by weight. The metal powder mixtures must, after processing, have a solidus temperature, as determined by differential thermal analysis, of at least 1065°C (1950°F), preferably at least 1090°C (2000°F). In addition, the mixtures must be capable of being processed at a temperature of about 1090°C (2000°F), preferably 1120°C (2050°F). Moreover, the mixture must not flow when heated to the processing temperature, i.e., it must have a sufficiently high viscosity and surface tension that it will not flow out of the shape or place in which it is deposited. The processing temperature is selected to be above the melting point of the low melting alloy but below the melting point of the high melting alloy as this allows the high melting alloy to form a homogenous mixture by the alloying action of the liquid low melting alloy coming in contact with the high melting alloy powder. In addition, the metal mixture should be prepared using similar size particles to minimize and preferably avoid segregation. preferably the particle size is -200 and +325 U.S. mesh. The processed metal mixtures may be coated with coating schemes that are typically used for high temperature superalloys. When properly coated, these metals survive in the harsh environment of a turbine engine. Depending upon the nature of the base metals to be repaired, a very thin layer of nickel may be plated onto the area needing repair or build-up prior to applying the metal mixture. When a nickel-base metal body being repaired contains higher concentrations of aluminum and titanium, for example, it is particularly advantageous to first apply this nickel coating. To utilize the metal mixture described above to repair and/or reform surface areas of a particular part, the following sequence of steps is preferably followed: 1. First, determine the maximum temperature which can be tolerated by the component to be repaired without damaging existing brazed joints, coatings, and materials. The deposition or processing temperature to be used will be this maximum temperature or close thereto. 2. Select a low melting alloy with a liquidus below the acceptable temperature to be used. 3. Select a high temperature alloy with a melting point above the acceptable temperature to be used. 4. Uniformly mix the selected alloys optionally with nickel powder in the desired proportions. 5. Uniformly mix the metal powder mixture of step 4 with an organic binder, such as those used in conventional brazing, to form a putty-like moldable composition. 6. Route out damaged areas, if necessary, to form holes or slots and clean surface areas for reconstruction. 7. Directly fill completely the hole, slot or area to be repaired and/or apply a molded mass as an extension on the surface areas to be reformed, using the semi-solid metal mixture of step 5. Based on the chemical composition of the component being repaired preplating with nickel may be required. In addition, the component must be properly cleaned prior to deposition, though unusual cleaning efforts with penetrating materials such as fluoride ions are not necessary. 8. Place the component in a vacuum furnace or an inert or hydrogen gas furnace. 9. Heat the component to the processing temperature and hold at this temperature for about 10 minutes. Then continue to heat either at this temperature or at a lower temperature until adequate chemical homogenization is achieved. This usually will take several hours or more depending on the specific metal mixture utilized. 10. Solution, precipitation heat treat, and recoat as required based on the heat treatment and coating requirements of the component. Both hot wall retort and cold wall radiant shield furnaces may be used while performing the deposition of the metal mixture compositions as defined by the present invention. However, because of some inherent advantages, cold wall furnaces are by far the more widely used. When employing a vacuum technique, the vacuum pumping system should be capable of evacuating a conditioned chamber to a moderate vacuum, such as, for example; about 10⁻³ torr, in about 1 hour. The temperature distribution within the work being repaired should be reasonably uniform (i.e., within about +5°C (10°F)). The present invention will be further illustrated by the following non-limiting examples in which all parts and percentages are by weight unless otherwise specified. EXAMPLE 1 Holes up to 5mm (0.20-in.) in diameter were drilled in 2.5mm (0.100-in.) thick nickel0base alloy specimens to simulate ground out cracks and eroded areas typically found in turbine airfoils damaged during engine operation. A filler metal powder mixture was mixed with an organic binder and applied to these holes. The filler metal mixture consisted nominally of 65% of a low melting alloy, 10% pure nickel and 25% of an alloy melting above 1150°C (2100°F). The low melting alloy had a nominal composition of 2.8% B, 15.0% Cr and 82.2% Ni. The high melting point alloy is C101 having a nominal composition of 0.09% C, 12.6% Cr, 9.0% Co, 1.9% Mo, 4.3% W, 4.3% Ta, 4.0% Ti, 3.4% Al, 0.9% Hf, 0.015% B, 0.06% Zr, and balance Ni. All of the specimens were subjected to the same deposition/homogenization treatment cycle: 1120°C (2050°F) for 10 minutes in a vacuum at 0.5 X 10⁻³ torr maximum pressure followed by 1050°C (1925°F) for 20 hours in a vacuum at 0.5 X 10⁻³ torr maximum pressure. Differential thermal analyses were conducted on the deposits. A solidus of 1084°C (1983°F) and a liquidus 1105°C (2020°F) were obtained for the deposits compared with 1055°C (1930°F) for both the solidus and liquidus of the original low melting alloy alone. Visual, fluorescent penetrant, radiographic and metallograhic examinations were conducted on the deposits. Excellent soundness and surface geometry were obtained. Results indicated that the filler metal had a high enough viscosity and surface tension during processing so that it did not flow out of the holes being repaired. COMPARATIVE EXAMPLES II AND III The basic procedure of Example 1 were repeated with two different formulations using low melting alloys consisting of 1.9% B, 15% Cr, and 83.1% Ni (Example II) and 3.5% B, 15% Cr and 81.5% Ni (Example III). The nominal compositions and the DTA results were: COMPOSITION EXAMPLE II III Low melting alloy 75 70 High melting alloy 25 20 Nickel 5 10 DTA Result, °C 1081 1077 (°F 1977 1970) The composition of Example II was processed at 1160°C (2125°F) for 10 minutes and then at 1052°C (1925°F) for 20 hours. The composition of Example III was processed at 1090°C (2000°F) for 6 hours and then at 1040°C (1900°F) for ten hours. EXAMPLE IV The basic procedure of Example I was repeated except that the metal mixture nominally comprised 35% of the high temperature alloy and 65% of the low melting alloy consisting of 2.8% B, 15% Cr, and 82.2% Ni. The sample was processed at 1120°C (2050°F) for ten hours. EXAMPLE V The basic procedure of Example I was repeated except that the metal mixture nominally comprised 35% of the high temperature alloy and 65% of the low melting alloy consisting of 2.8% B, 15% Cr, and 82.2% Ni. The sample was processed at 1120°C (2050°F) for 10 minutes followed by 20 hours at 1052°C (1925°F). The sample exhibited superior soundness and DTA yielded a solidus temperature of 1101°C (2014°F). COMPARATIVE EXAMPLE A The basic procedure of Examples I-IV was repeated for a variety of metal mixture formulations and thermal cycles as identified below in Table I. In each case a sound deposit was produced but DTA determined that the solidus of each was too low to be useful in the present invention. Results of Comparative Example A Composition Sample 1 2 3 4 Low melting alloy 100 75 70 70 High melting alloy -- 15 30 20 Nickel -- 10 -- 10 Thermal Cycle 10 min. at °C 1160 1090 1090 1090 (°F 2125 2000 2000 2000 ) followed by 20 hours at 552°C (1025°F) Solidus, °C 1063 1054 1055 1049 (°F 1946 1930 1931 1920 ) COMPARATIVE EXAMPLE B The basic procedure of Examples I-IV was repeated for various metal mixtures as identified in Table II below. each of the samples was processed at either 1090°C (2000°F)or 1120°C (2050°F) for 10 minutes and then allowed to cool. All of the samples were then visually evaluated and all were found to be unsound as specified in Table II. Thus no extended heating for homogenization was conducted. These results indicate that only the mixtures specified give the desired results. While specific components of the present system are defined in the working examples above, any of the other typical materials indicated above may be substituted in the working examples, if appropriate.

Claims: A method for repairing damaged superalloy bodies which comprises (a) applying directly into holes or slots or widegap joint damages on such bodies or reconstructing damaged, missing or worn surface extensions of such bodies, such as blade tips, a semi-solid, form-retaining, silicon-free metal alloy powder mixture capable of being processed at a temperature of between about 1090°C and 1150°C (about 2000°F and 2100°F), said metal alloy mixture consisting of (i) from 55 to 90 percent by weight of a first, lower melting, nickel-base superalloy powder composition consisting of from 14 to 16 weight percent chromium, from 2.5 to 3.2 weight percent boron and the balance nickel, said lower melting composition having a liquidus above about 980°C (1800°F) and below about 1090°C (2000°F): (ii) from 10 to 40 percent by weight of a second, higher melting, nickel-base superalloy powder composition consisting of from 38 to 67 weight percent nickel, from 11 to 15 weight percent chromium, from 8 to 12 weight percent cobalt, from 3 to 10 weight percent tungsten, from 3.5 to 10 weight percent tantalum, amounts less than 5.0 weight percent each of titanium, aluminum, molybdenum and hafnium, amounts less than 0.5 weight percent each of carbon and zirconium, and from 0.0005 to 0.025 weight percent boron, said higher melting composition having a liquidus above about 1200°C (2200°F) but below about 1260°C (2300°F); and (iii) from 0 to 20 percent by weight, less than the amount of said higher melting composition (ii), of nickel powder, (b) heating said applied metal alloy powder mixture to a processing temperature between about 1090°C (2000°F) and 1150°C (2100°F) for a sufficient time to cause the lower melting powder (i) to melt and alloy with the higher melting powder (ii), and with the nickel powder (iii), if present, for forming a semi-solid high viscosity, high surface-tension, form-retaining composition having a solidus temperature of at least about 1065°C (1950°F), and (c) cooling said processed composition to form a sound, non-porous deposit which fills and bridges the holes, slots and widegap joints and retains substantially the same shape on a superalloy body being repaired before and after processing. The method of claim 1, wherein after step (b) the assembly is continued to be heated at or below said processing temperature for a time to allow chemical homogenization of said metal mixture to occur. The method of claim 1, wherein step (b) is conducted under a vacuum. The method of claim 1, wherein step (b) is conducted under an inert or hydrogen atmosphere. The method of claim 1, wherein said metal mixture includes an organic binder. The method of claim 1, wherein the metal mixture consists of, by weight 60 to 85 percent low melting alloy, 10 to 40 percent higher melting alloy (ii), and 0 to 15 percent nickel. The method of claim 1, wherein the metal mixture consists of, by weight, 63 to 82 percent low melting alloy (i), 18 to 37 percent higher melting alloy (ii), and 0 to 12 percent nickel. The method of claim 1, wherein the low melting alloy comprises 2.8 weight boron. The method of claim 1, wherein the low melting alloy has a solidus temperature of about 1050°C (1925°F) to about 1080°C (1975°F). The method of claim 1 wherein the low melting alloy comprises, by weight, 15 percent chromium, 2.8 percent boron, and the balance nickel. The method of claim 10, wherein the higher melting alloy (ii) comprises, by weight, 12.2% to 13.0% chromium, from 8.5% to 9.5% cobalt, from 3.85% to 4.50% tungsten, from 3.85% to 4.50% tantalum, from 3.85% to 4.15% titanium, from 3.2% to 3.6% aluminum, from 1.70% to 2.10% molybdenum, from 0.75% to 1.05% hafnium, from 0.07% to 0.02% carbon, from 0.03% to 0.14% zirconium, from 0.01% to 0.02% boron and the remainder nickel. The method of claim 1, wherein the superalloy being repaired is nickel-based. The method of claim 12, which comprises first coating a thin layer of nickel onto the area of the body to be repaired. The method of claim 1, wherein the metal mixture comprises, by weight, 70% of the low melting alloy of claim 11, 20% of the higher melting alloy of claim 12, and 10% nickel. The method of claim 1, wherein the metal mixture comprises, by weight 65% of the low melting alloy of claim 10, 25% of the higher melting of claim 11, and 10% nickel. The method of claim 1, wherein the metal mixture comprises, by weight 75% of the low melting of claim 11, 20% of the higher melting of claim 11, and 5% nickel. The method of claim 1, wherein the metal mixture comprises, by weight, 80% of the low melting alloy of claim 10 and 20% of the higher melting alloy of claim 11. The method of claim 17, wherein the metal mixture comprises, by weight, 65% of the low melting alloy of claim 10 and 35% of the higher melting alloy of claim 11. The method of claim 1, wherein the solidus temperature of the deposited mixture is at least 1090°C (2000°F) and the deposition temperature is at least 1120°C (2050°F). A method of repairing a damage in a high temperature superalloy component while not causing damage to existing brazed joints and coatings thereon, which comprises: (a) determining the maximum temperature which can be tolerated by the component without damaging existing brazed joints and coatings; (b) selecting a powdered nickel-based silicon-free low melting alloy which has a liquidus temperature above 980°C (1800°F) and below about 1090°C (2000°F) and consisting of a powder (i) as defined in claim 1; (c) selecting a powdered nickel-based silicon-free higher melting alloy having a melting point above 1150°C (2100°F) and consisting of a powder (ii), as defined in claim 1; (d) uniformly mixing the alloy powders (i) and (ii), optionally with nickel powder (iii), in the proportions, as defined in claim 1; (e) uniformly mixing the metal powder mixture of (d) with an organic binder to form a semi-solid, farm-retaining composition; (f) routing out the damage, if necessary, to form a hole, slot or widegap joint or receptive surface; (g) directly filling or reconstructing the damage to be repaired with the mixture of (e); (h) placing the component in a furnace; (i) heating the component to a temperature of about 1090°C (2000°F) for about 10 minutes and then continuing to apply heat until chemical homogenization is achieved. The method of claim 20, wherein the repaired damage will withstand a temperature of at least 1065°C (1950°F) in subsequent use. The method of claim 20, wherein the heating in (i) is to at least 1120°C (2050°F) and the repaired damage will withstand a temperature of at least 1090°C (2000°F) in subsequent use. The method of claim 14, wherein the low melting alloy comprises eight percent chromium, 2.8 weight percent boron, and the balance nickel. The method of claim 20, wherein the higher melting alloy of step (c) is as defined in claim 11. The method of claim 20, wherein the furnace is a vacuum furnace. The method of claim 20, wherein the superalloy being repaired is nickel-based and a thin layer of nickel is plated onto the area to be repaired before step (f).

Inventors: IOVENE MICHAEL A, LEE JACK W, MILLER JULE A, IOVENE, MICHAEL, A., LEE, JACK, W., MILLER, JULE, A.
Applicants: AVCO CORP, AVCO CORPORATION
Application year: 1988
Main classification: B22F7
IPC codes: B23K35, B22F5, F01D5, B23P6, B22F1, C22C1, B23K1, B22F7