|Publication number||US3544348 A|
|Publication date||Dec 1, 1970|
|Filing date||Oct 25, 1968|
|Priority date||Oct 25, 1968|
|Also published as||DE1952370A1, DE1952370B2|
|Publication number||US 3544348 A, US 3544348A, US-A-3544348, US3544348 A, US3544348A|
|Inventors||Boone Donald H, Goward George W|
|Original Assignee||United Aircraft Corp|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (7), Referenced by (57), Classifications (18)|
|External Links: USPTO, USPTO Assignment, Espacenet|
United States Patent Office 3,544,348 Patented Dec. 1, 1970 3,544 348 OVERHAUL PROCESS FOR ALUMINIDE COATED GAS TURBINE ENGINE COMPONENTS Donald H. Boone and George W. Goward, North Haven, Conn., assignors to United Aircraft Corporation, East Hartford, Conn., a corporation of Delaware No Drawing. Filed Oct. 25, 1968, Ser. No. 770,853 Int. Cl. B23p 7/00; C23c 9/02 US. Cl. 117-2 4 Claims ABSTRACT OF THE DISCLOSURE An overhaul process for coated gas turbine engine components is described wherein the components are: removed from the engine at or prior to the onset of significant coating penetration as evidenced by the loss of one or more substrate components; recoated in a pack cementation process of high aluminum activity without stripping of the old coating; and are subsequently heat treated to promote the formation of aluminides having an aluminum content less than that corresponding to Ni Al BACKGROUND OF THE INVENTION The present invention relates in general to the generation of oxidation-resistant aluminide coatings on the nickel-base superalloys, particularly in the overhaul and repair of coated gas turbine engine components.
It is the standard practice in the gas turbine engine industry to establish inspection, repair and overhaul cycles for the various engine models on a statistical basis which is related to the projected lifetimes of selected engine components. While a number of factors are involved in determining the length of such cycles and in the past the factors have involved various mechanical properties such as fatigue or creep of the substrate alloy, at the higher operating temperatures of a number of the advanced engines the components are very often coatinglimited which means that in many cases it is deterioration of the coating rather than accumulated mechanical stress on the part which determines the duration of the overhaul cycle. It also means that, if the coating can be restored, the part can be salvaged and reused, possibly several times. This is of particular advantage in the case of certain advanced thin-walled hardware incorporating air cooling where the expense involved in the initial production of the component makes salvage almost mandatory, if feasible.
The present practice with salvageable parts following a coating deterioration or breakdown is to: remove all of the original coating; rework the part as necessary; and then recoat utilizing one of the standard techniques such as slurry-diffusion. These current salvage operations are not without drawback however. Most aluminide coatings are produced by or involve a diffusion mechanism whereby the coating is formed by reaction of the coating material with the substrate elements. Therefore, the formation of the usual 3 mil coating involves consumption of at least 2 mils of the substrate alloy. Thus, the removal of the old coating, even from areas where a coating failure has not occurred, necessarily results in the loss of some substrate material and a reduction in the thickness of the part. While the loss of substrate material is of some, although often lesser, concern in the case of thick walled components, the loss of 2 mils or more of thickness on the more advanced hardware, some sections being but 15-20 mils thick, is intolerable. Furthermore, there are the additional problems involving the time and expense related to the stripping operation, not to mention the difiiculty of a uniform or controlled material removal. Because of these factors, there is an unacceptably high scrap rate associated with the utilization of the current overhaul and repair techniques.
SUMMARY OF THE INVENTION It is a primary object of the present invention to provide an improved overhaul and repair procedure for aluminide-coated superalloy components which have been exposed to a high temperature oxidizing environment.
The above and other objects and advantages of the invention are provided by processing the part involved prior to excessive coating degradation or failure, in a pack cementation aluminizing process utilizing a pack mix of high aluminum activity at the coating temperature, without stripping the prior coating therefrom.
A particularly preferred process comprises the steps of: removing the part to be processed from its oxidizing environment prior to the onset of any substantial oxidative attack on the superalloy substrate elements; superficially cleaning the oxide layer therefrom; recoating the part in a pack aluminizing process utliizing a pack mix of sulficiently high aluminum activity at the coating temperature to preferentially form the nickel aluminides having an aluminum content equal to or greater than that corresponding to Ni Al and subsequently heat treating the coated components to cause further diffusion thereby converting at least a portion of the aluminides to those having an aluminum content less than that of the Ni Al phase.
DESCRIPTION OF THE PREFERRED EMBODIMENTS Diffused aluminum coatings for the protection of various metals from high temperature oxidation have been in use for over fifty years. Two major processes are generally used for the application of such coatings to nickelbase gas turbine hardware. The first involves covering the surface of the metal to be protected with a slurry of aluminum in a liquid vehicle, followed by drying and firing at an elevated temperature. The second process comprises the steps of embedding the article in a dry powder mix of aluminum, an inert filler such as powdered alumina, and an activator such as ammonium chloride, and heating the pack to some elevated temperature for a period of time suflicient to form a coating of the desired thickness. This latter process is typically referred to as pack aluminizing or pack cementation aluminizing. While various other elements may be added to the pack mix either as rate-controllers or to impart some additional specific property to the coating, nevertheless all such coatings consist primarily of intermetallic compounds, such as nickel aluminides derived from the aluminum in the pack and elements from the substrate and from which the basic oxidation resistance is derived.
In general, the thickness, composition and structure of a pack cementation coating are determined by the follow; ing controllable variables: (a) pack mix composition; (b) processing temperatures; (c) time at temperature; and (d), any subsequent heat treatment of the coated component. Historically, the pack cementation processes have been performed in large retorts necessitating the use of long times at temperature to obtain thermal equilibrium To prevent large differences in coating thicknesses as a result of different thermal histories in such large containers, a pack mix of low time-sensitivity is generally employed, such a mix being characterized by a low aluminum activity.
It has now been discovered that, if the aluminum activity of the pack mix is such that the equilibrium coating phase is NiAl or other phases lower in aluminum content, then the coating will form only by outward diffusion of nickel from the substrate and the phases will form on top of the substrate alloy. Virtually no aluminum motion is 3 involved in the formation of sucha coating. While this is an unusual diffusion phenomenon, it has nevertheless been experimentally established. On the other hand, if the aluminum activity of the pack mix is such that the equilibrium coating phase is Ni Al or phases higher in aluminum content, then the coating will form only byan inward diffusion of aluminum and virtually no nickel motion is involved in the formation of such a coating. Again, this is an unusual and unexpected diffusion phenomenon, but nevertheless experimentally established.
For mechanical property reasons, the coating comprising the Ni Al phase generated-in a pack of high aluminum activity cannot be practically employed in many cases because of its brittleness. Therefore, the coated alloy is normally subsequently heat treated to cause further diffusion to occur which promotes the formation of the more ductile NiAl phase. Because the driving force of high aluminum activity is no longer present, nickel diffusion from the substrate now occurs in combination with diffusion of the aluminum from the Ni Al phase to form a layer of NiAl beneath the original Ni Al coating.
The aluminide coatings derive their protectivity from the intermetallic compounds of aluminum which in turn are protected by a thin layer of aluminum oxide formed by high temperature oxidation of the coating. Gradually, however, the oxide is lost by a process of erosive spalling, but a reoxidation occurs and the protective function is reestablished. Accordingly, the substrate remains protected as long as sufiicient aluminum is retained in the coating to provide for the preferential oxidation to aluminum oxide, and a coating failure or rapid degradation occurs when one or more of the substrate metals commences to oxidize. The protective function of the coating is, hence, a direct function of its aluminum content.
A major factor contributing to the success of the present invention involves recognition of the fact that aluminide coatings may be formed on the superalloys by an inward diffusion of aluminum provided the aluminum activity of the pack mix is sufiiciently high to form equilibrium aluminide phases of high aluminum content as previously described. For such a pack aluminizing process there is a parabolic relationship between coating thickness and time. Thus, a part with no coating in an eroded zone and a retained coating of 3 mils in a cooler zone will, during such a recoating process, form a new coating of Ni Al or phases of higher aluminum content, of the required thickness in all zones but in so doing will absorb considerably less aluminum in the undegraded zones than in the degraded or eroded zone. This occurs because in the undegraded zones the aluminum content, before recoating amounts to about 30%, corresponding to the ,3 (NiAl) phase, whereas in the degraded zone the aluminum content may be as low as 5%. That is to say, that in being transformed to the Ni A1 phase, which contains 40% aluminum, the undegraded zones absorb the equivalent of about aluminum while the degraded zone absorbs as much as the equivalent of 35% aluminum. Upon subsequent heat treatment to form the desired ductile fl (NiAl) phase, as previously described, the coating on the previously undegraded zones exhibits minimal new growth because these zones have absorbed relatively small amounts of aluminum during the recoating process, whereas a completely new coating has formed on the previously degraded zone because this zone has absorbed a relatively large amount of aluminum. The net result is that new coating of the required thickness has been formed on the previously eroded area of the part with insignificant increase in coating thickness in the cooler, undegraded zones thereby eliminating the necessity of performing the expensive and otherwise undesirable stripping operation of the current processes wherein the old coating is totally removed.
While a number of gas turbine engine components can be satisfactorily recoated as herein described even in those instances where there has been substantial corrosive attack on the substrate metal, maximum usefulness of the present process occurs if the overhaul period selected allows recoating of the components prior to a substantial loss of substrate components by oxidation-erosion. This substrate loss occurs when the aluminum con tent of the coating fall below that level at which the oxidation mechanism is preferentially toward the formation of aluminum oxide as evidenced, in the nickel-base systems, by the occurrence of macroscopic amounts of the blue-green, nickel-rich oxide.
The particular pack aluminizing process preferred in the present overhaul and repair process is one selected to provide for the incorporation of the desirable substrate alloying elements in the coating while minimizing the formation of deleterious phases. In the process, the article to be coated is embedded in a pack mix containing 5-20 Weight percent aluminum, 0.5-3 percent ammonium chloride, balance alumina. The pack is then heated to a relatively low temperature 1200-1600 F. in an inert atmosphere and coating growth is allowed to proceed for 1-4 hours. In the recoating process a minimum coating thickness of 0.003 inch is effected. Subsequenfly, the recoated article is subjected to a ductilizing heat treatment in the temperature range of l900-2200 F. usually matched to the strengthening heattreatments specified for the superalloy substrate.
The exact pack composition and coating parameters employed in a given case are, of course, dependent upon the particular component being processed and the particular end result desired. In each case, however, the pack of the present invention will be characterized by a high aluminum activity, and will tend to yield coatings high in aluminum content for a given time at temperature. Those skilled in the art will readily recognize the variety of alternative techniques and compositions adapted to provide the requisite high aluminum activity.
As used herein, the term nickel-base superalloys will be understood to have reference to those multiphase alloys of the 'y'y' type which are characterized by high strengths at temperatures of 1500" F. and higher. Several represeriative alloys of this type are listed in the following ta e.
In one test an erosion bar formed of the B-1900 alloy was coated by slurry techniques to a thickness of about 3 mils and run in an oxidation-erosion environment at 2100 F. for hours. The bar was removed from test at the first sign of coating penetration and substrate oxidation as evidenced by the appearance of the blue-green, nickel-rich oxide. The specimen was sectioned through the eroded zone and one half was examined metallographically as a control specimen while the other half was recoated in a pack of high aluminum activity for 1 /2 hours at 1400 F., followed by a heat treatment of 4 hours at 2000 F. This specimen was then examined metallographically to determine coating uniformity, thickness and structure.
Examination of the control specimen revealed pitting through the coating at the eroded zone which resulted in the formation of the blue-green oxide. The uneroded portion of the coating in the hot zone of bar contained no ,0 (NiAl) aluminide and a thin layer of carbides was observed to be in the process of resolutioning in the 'y (nickel solid solution)-'y (Ni Al) phases of the coating layer. The recoating process uniformly covered the defect area and the remaining 'y'y' phase layer with but a slight depression in the coating surface at the eroded zone, but otherwise little difference was noted in the coating structure or thickness after recoating. The cooler zones of specimen before recoating showed some effects of aluminum depletion with the presence of the 7' phase of the aluminide at the grain boundaries of the ,9 (NiAl) aluminide. The recoated structure after diffusion heat treatment was all aluminide with a slightly different carbide morphology than in the original specimen, but no unusual or detrimental phases were present. As indicated by the absence of a hyper-stoichiometric aluminum rich ,6 phase layer, the recoated structure was not excessive high in aluminum content.
A second B-1900 alloy erosion bar was coated in a process similar to that used with the first specimen and was run in an oxidation-erosion test at 2100 F. Although the specimen failed at about 50 hours by pitting through the coating to the substrate, the test was run to 100 hours. As a result, some excessive substrate damage in hot zone on the trailing surface was noted because of the excessive time in test. However, the specimen was lightly cleaned with a vapor blast and recoated by a pack aluminizing process of high aluminum activity. This recoated specimen was then retested for an additional 60 hours at 2100 F. until coating failure again occurred.
The specimen was again cleaned and recoated, this time to produce a coating of 3 /2 mils thickness. A third oxidation erosion cycle at 2100 F. was run and coating failure did not occur for an additional 80 hours.
After these tests the following observations were made with respect to the specimen: (1) the specimen surface was still smooth and free from any indication of defects; (2) a slight depression of 3-5 mils on the surface of the hot zone was present, the result, however, of testing of the specimen beyond the limit of the coating protection in the initial oxidation-erosion test which resulted in some substrate attack; (3) the lfetime of the nickelbase substrate was successfully extended to 3 or more times its normal useful level; (4) no excessive buildup of the coating occurred in the previously undegraded areas and no masking was required; (5) the problems associated with the stripping of the coating were eliminated.
It is evident that aluminide-coated alloy systems can be recoated several times by the disclosed pack cementation process without the necessity of prior coating stripping. The principal considerations are the removal of the specimen from its oxidizing environment prior to coating breakthrough and significant substrate attack, and the use of a pack aluminizing process utilizing a pack mix of high aluminum activity.
'In view of the continuing upward trend in engine operating conditions, the increased use of thin-walled components is anticipated with the consequent increased component cost resultant from the added complexity. Furthermore, the trend toward higher temperatures clearly forecasts that a number of engine components will continue to be coating-limited. Thus, the salvage of these expensive components will continue to be mandatory and the overhaul and repair procedure described herein should find wide utility in such salvage operations.
While the present invention has been described in connection with certain examples and preferred process compositions and parameters, these will be understood to be illustrative only and numerous modifications will be 6 evident to those skilled in the art from the detailed description. The invention in its broader aspects is not limited to the specific details shown and described but departures may be made from such details without departing from the principles of the invention and Without sacrificing its chief advantages.
What is claimed is:
1. An overhaul and repair procedure for aluminidecoated gas turbine engine components formed from the nickel-base superalloys which comprises:
removing the oxidized components from the engine prior to the onset of substantial oxidative attack on the superalloy substrate;
superficially cleaning the surface of the coated components to remove the accumulated oxide layer therefrom; recoating the components in a pack aluminizing process utilizing a pack mix having an aluminum activity at the coating temperature sufiicient to preferentially form equilibrium aluminides having an aluminum content not less than that corresponding to Ni A1 and diffusion heat treating the recoated components to convert the aluminides formed in the aluminizing process to aluminides having an aluminum content substantially corresponding to NiAl.
2. An overhaul and repair procedure for aluminide coated gas turbine engine components formed from the nickel-base superalloys which comprises:
removing the oxidized components from the engine prior to the first appearance of macroscopic amounts of blue-green nickel-rich oxide;
superficially cleaning the surface of the coated components to remove the accumulated oxide layer therefrom;
recoating the components in a pack aluminizing process utilizing a pack mix having an aluminum activity at the coating temperature sufficiently high to promote formation of the coating by an inward diffusion of aluminum toward the superalloy substrate;
and, after removal from the pack, diffusion heat treating the recoated components to preferentially form aluminides having an aluminum content substantially corresponding to NiAl.
3. The procedure according to claim 2 wherein the final diffusion heat treatment is conducted in the temperature range of l900-2200 F.
4. The procedure according to claim 3 wherein in the recoating process a minimum coating thickness of 0.003 inch is effected.
References Cited UNITED STATES PATENTS 3,079,276 2/1963 Puyear et al. 117 107.2 (P) 3,129,069 4/1964 Hanink et al. 29-197 X 3,141,744 7/1964 Couch et a1 29 197 X 3,257,230 6/1966 Wachtelletal. 117 107.2 (P) 3,345,197 10/1967 Martini et al. 117-1072 (P)X 3,436,249 4/1969 Lambert et al. 117-1072 (P) 3,450,512 6/1969 Maxwell 29-197 X ALFRED L. LEAVITT, Primary Examiner I. R. BATTEN, 111., Assistant Examiner U.S. Cl. X.R.
29197; ll77l, 107.2
|Cited Patent||Filing date||Publication date||Applicant||Title|
|US3079276 *||Oct 14, 1960||Feb 26, 1963||Union Carbide Corp||Vapor diffusion coating process|
|US3129069 *||Dec 17, 1959||Apr 14, 1964||Gen Motors Corp||Oxidation-resistant turbine blades|
|US3141744 *||Jun 19, 1961||Jul 21, 1964||Dwight E Couch||Wear-resistant nickel-aluminum coatings|
|US3257230 *||Mar 24, 1964||Jun 21, 1966||Chromalloy American Corp||Diffusion coating for metals|
|US3345197 *||Aug 9, 1963||Oct 3, 1967||Howmet Corp||Aluminizing process and composition|
|US3436249 *||Feb 23, 1966||Apr 1, 1969||Rolls Royce||Aluminising powder|
|US3450512 *||Jul 5, 1966||Jun 17, 1969||United Aircraft Corp||Coated nickel base engine alloys|
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US3647517 *||Jun 22, 1970||Mar 7, 1972||Chromalloy American Corp||Impact resistant coatings for cobalt-base superalloys and the like|
|US3716398 *||Aug 19, 1970||Feb 13, 1973||Chromalloy American Corp||Impact resistant coatings for nickel-base and cobalt-base superalloys and the like|
|US3837901 *||Aug 21, 1970||Sep 24, 1974||Gen Electric||Diffusion-coating of nickel-base superalloy articles|
|US3839898 *||Nov 22, 1972||Oct 8, 1974||United Aircraft Corp||Determination of thermal profile history of high temperature parts|
|US3887731 *||Apr 23, 1973||Jun 3, 1975||Chromalloy American Corp||Corrosion resistant coating system for ferrous metal articles having brazed joints|
|US3922474 *||Nov 29, 1973||Nov 25, 1975||United States Borax Chem||Cold-pressed refractory materials|
|US3953647 *||Oct 5, 1973||Apr 27, 1976||United Technologies Corporation||Graphite fiber reinforced metal matrix composite|
|US4128522 *||Jul 30, 1976||Dec 5, 1978||Gulf & Western Industries, Inc.||Method and maskant composition for preventing the deposition of a coating on a substrate|
|US4181758 *||Feb 6, 1978||Jan 1, 1980||Gulf & Western Industries, Inc.||Method for preventing the deposition of a coating on a substrate|
|US4729799 *||Jun 30, 1986||Mar 8, 1988||United Technologies Corporation||Stress relief of single crystal superalloy articles|
|US4944858 *||Dec 8, 1988||Jul 31, 1990||United Technologies Corporation||Method for applying diffusion aluminide coating|
|US5161898 *||Jul 5, 1991||Nov 10, 1992||Camco International Inc.||Aluminide coated bearing elements for roller cutter drill bits|
|US5538796 *||Oct 13, 1992||Jul 23, 1996||General Electric Company||Thermal barrier coating system having no bond coat|
|US5650235 *||Feb 28, 1994||Jul 22, 1997||Sermatech International, Inc.||Platinum enriched, silicon-modified corrosion resistant aluminide coating|
|US5813118 *||Jun 23, 1997||Sep 29, 1998||General Electric Company||Method for repairing an air cooled turbine engine airfoil|
|US5897966 *||Feb 26, 1996||Apr 27, 1999||General Electric Company||High temperature alloy article with a discrete protective coating and method for making|
|US6042880 *||Dec 22, 1998||Mar 28, 2000||General Electric Company||Renewing a thermal barrier coating system|
|US6071622 *||Oct 30, 1998||Jun 6, 2000||Beesabathina; Durga Prasad||Stabilized two-phase-glass diffusion barrier|
|US6110262 *||Aug 31, 1998||Aug 29, 2000||Sermatech International, Inc.||Slurry compositions for diffusion coatings|
|US6203847||Dec 22, 1998||Mar 20, 2001||General Electric Company||Coating of a discrete selective surface of an article|
|US6228510||Dec 22, 1998||May 8, 2001||General Electric Company||Coating and method for minimizing consumption of base material during high temperature service|
|US6274193||Apr 28, 2000||Aug 14, 2001||General Electric Company||Repair of a discrete selective surface of an article|
|US6444054||Jun 21, 2000||Sep 3, 2002||Sermatech International, Inc.||Slurry compositions for diffusion coatings|
|US6465040||Feb 6, 2001||Oct 15, 2002||General Electric Company||Method for refurbishing a coating including a thermally grown oxide|
|US6482470||Jul 18, 2000||Nov 19, 2002||General Electric Company||Diffusion aluminide coated metallic substrate including a thin diffusion portion of controlled thickness|
|US6605364||Jul 18, 2000||Aug 12, 2003||General Electric Company||Coating article and method for repairing a coated surface|
|US6689422||Feb 16, 1994||Feb 10, 2004||Howmet Research Corporation||CVD codeposition of A1 and one or more reactive (gettering) elements to form protective aluminide coating|
|US6849132||Aug 20, 2003||Feb 1, 2005||Howmet Research Corporation||CVD codeposition of A1 and one or more reactive (gettering) elements to form protective aluminide coating|
|US6969558||Nov 18, 2003||Nov 29, 2005||General Electric Company||Low sulfur article having a platinum-aluminide protective layer, and its preparation|
|US7093335||Jul 3, 2002||Aug 22, 2006||General Electric Company||Coated article and method for repairing a coated surface|
|US7138065||May 17, 2002||Nov 21, 2006||Siemens Aktiengesellschaft||Method for removing at least one area of a layer of a component consisting of metal or a metal compound|
|US7163718||Oct 15, 2003||Jan 16, 2007||General Electric Company||Method of selective region vapor phase aluminizing|
|US7429337||Sep 29, 2006||Sep 30, 2008||Siemens Aktiengesellschaft||Method for removing at least one area of a layer of a component consisting of metal or a metal compound|
|US7510779||Sep 17, 2004||Mar 31, 2009||General Electric Company||Low-sulfur article having a platinum aluminide protective layer and its preparation|
|US7901788||Mar 8, 2011||Howmet Corporation||CVD condeposition of A1 and one or more reactive (gettering) elements to form protective aluminide coating|
|US8038894 *||Nov 29, 2006||Oct 18, 2011||General Electric Company||Method of selectively stripping an engine-run ceramic coating|
|US20030021892 *||Jul 3, 2002||Jan 30, 2003||Conner Jeffrey Allen||Coated article and method for repairing a coated surface|
|US20030054191 *||Oct 10, 2002||Mar 20, 2003||Reeves Jim Dean||Diffusion aluminide coated metallic substrate including a thin diffusion portion of controlled thickness|
|US20040037958 *||Aug 20, 2003||Feb 26, 2004||Howmet Research Corporation||CVD condeposition of A1 and one or more reactive (gettering) elements to form protective aluminide coating|
|US20040038069 *||Aug 20, 2003||Feb 26, 2004||Howmet Research Corporation||CVD codeposition of Al and one or more reactive (gettering) elements to form protective aluminide coating|
|US20040123923 *||Nov 18, 2003||Jul 1, 2004||Walston William S.||Low sulfur article having a platinum-aluminide protective layer, and its preparation|
|US20040180232 *||Feb 5, 2004||Sep 16, 2004||General Electric Company||Selective region vapor phase aluminided superalloy articles|
|US20040244817 *||May 17, 2002||Dec 9, 2004||Norbert Czech||Method for removing at least one area of a layer of a component consisting of metal or a metal compound|
|US20050084706 *||Oct 15, 2003||Apr 21, 2005||General Electric Company||Method of selective region vapor phase aluminizing|
|US20050121116 *||Sep 17, 2004||Jun 9, 2005||General Electric Company||Low-sulfur article having a platinum aluminide protective layer and its preparation|
|US20070023392 *||Sep 29, 2006||Feb 1, 2007||Siemens Aktiengesellschaft And Diffusion Alloys Ltd.|
|US20080121623 *||Nov 29, 2006||May 29, 2008||General Electric Company||Method of selectively stripping an engine-run ceramic coating|
|US20090232975 *||Dec 7, 2005||Sep 17, 2009||Mtu Aero Engines Gmbh||Method for repairing turbine vanes|
|US20090293447 *||Apr 16, 2009||Dec 3, 2009||Dan Roth-Fagaraseanu||Method for the provision of fire protection for titanium components of an aircraft gas turbine and titanium components for an aircraft gas turbine|
|DE102012010602A1||May 30, 2012||Dec 5, 2013||Dechema-Forschungsinstitut||Verfahren zum Beschichten eines kobalt-, nickel- und/oder eisenhaltigenSubstrats mit einer korrosionsbeständigen Schicht|
|EP0496935A1 *||Aug 27, 1991||Aug 5, 1992||General Electric Company||Aluminide processing of articles protected by a thermal barrier coating system|
|EP0837153A2 *||Oct 9, 1997||Apr 22, 1998||United Technologies Corporation||Low activity localized aluminide coating|
|EP1013786A1 *||Dec 10, 1999||Jun 28, 2000||GE Aviation Services Operation (Pte) Ltd.||Method for repairing a superalloy turbine component|
|EP1123987A1 *||Feb 7, 2001||Aug 16, 2001||General Electric Company||Repairable diffusion aluminide coatings|
|WO1994007004A1 *||Sep 7, 1993||Mar 31, 1994||Rolls-Royce Plc||Aluminide-silicide coatings, coating compositions, process for coating and improved coated products|
|WO2006063561A1 *||Dec 7, 2005||Jun 22, 2006||Mtu Aero Engines Gmbh||Method for repairing turbine vanes|
|WO2013178216A1||May 29, 2013||Dec 5, 2013||Dechema-Forschungsinstitut||Method for coating a substrate containing cobalt, nickel and/or iron with a corrosion-resistant layer|
|U.S. Classification||427/142, 428/653, 427/226, 427/327, 428/679|
|International Classification||F01D5/00, F01D5/28, C23C10/48, C23C10/60, C23C10/00|
|Cooperative Classification||C23C10/60, C23C10/48, F01D5/005, F01D5/288|
|European Classification||C23C10/60, C23C10/48, F01D5/00B, F01D5/28F|