|Publication number||US3754903 A|
|Publication date||Aug 28, 1973|
|Filing date||Sep 15, 1970|
|Priority date||Sep 15, 1970|
|Publication number||US 3754903 A, US 3754903A, US-A-3754903, US3754903 A, US3754903A|
|Inventors||G Goward, D Boone, F Pettit|
|Original Assignee||United Aircraft Corp|
|Export Citation||BiBTeX, EndNote, RefMan|
|Referenced by (113), Classifications (18)|
|External Links: USPTO, USPTO Assignment, Espacenet|
United States Patent [1 1 Goward et a1.
[ Aug. 28, 1973 1 1 HIGH-TEMPERATURE OXIDATION-RESISTANT COATING ALLOY [75} Inventors: George W. Goward; Donald H.
Boone; Frederick S. Pettit, all of North Haven, Conn.
 Assignee: United Aircraft Corporation, East Hartford, Conn.
221 Filed: Sept. 15, 1970 21 Appl. No.: 72,512
Related U.S. Application Data  Division of Ser. No. 734,740, June 5, 1968  U.S. Cl. 75/171, 29/194  Int. Cl. C22c 19/08  Field of Search 75/138, 171
 References Cited UNITED STATES PATENTS 3,228,095 [/1966 Bird 75/171 3,399,058 8/1968 Roush 75/171 3,536,542 10/1970 Murphy 75/171 3,615,375 10/1971 Beltran 75/171 3,620,693 11/1971 Sama 75/171 Primary Examinerl-lyland Bizot Attorney-Richard N. James  ABSTRACT A coating alloy for the gas turbine engine super-alloys is described which consists primarily of nickel, aluminum and a reactive metal such as yttrium, particularly at the composition, by weight, 14-30 percent aluminum, 0.0l-0.5 percent reactive metal balance nickel. A preferred embodiment also includes 15-45 weight percent chromium.
2 Claims, 1 Drawing Figure l 1 l l HIGH-TEMPERATURE OXIDATION-RESISTANT COATING ALLOY This is a division of Application Ser. No. 734,740, filed June 5, 1968.
BACKGROUND OF THE INVENTION the present invention is directed to oxidationresistant alloys, particularly alloy compositions having application as coatings on the superalloys utilized in the gas turbine engine industry.
A nickel-base superalloy is typically a nickelchromium solid solution, hardened by the additions of aluminum and titanium to precipitate the intermetallic compound or gamma prime phase Ni (Al,Ti). The contemporary superalloys also usually contain cobalt to raise the solvus temperature of the gamma prime phase, refractory metals such as tungsten or tantalum for solution strengthening, and carbon, boron and zirconium to promote ductility and fabricability.
A limiting factor in the application of the current superalloys to jet engine hardware is their susceptibility to oxidation at very high temperatures with a consequent progressive loss of substrate material. For this reason, the nickel-base superalloys are generally coated with a composition different from and more oxidation-resistant than the structural alloy. In most instances the requisite layer of icnreased oxidation resistance is provided by reacting aluminum with the surface of the alloy to form an aluminide which in turn oxidizes to provide a surface oxide layer through which the transport rates of the reacting species are low. Typical of the processes of this type is that described in the U.S. Pat. to Joseph No. 3,102,044.
Although the aluminide coatings as currently provided significantly enhance the lifetimes of superalloy hardware, the theoretically expected behavior of the nickel aluminide intermetallic compound is not in fact realized in dynamic oxidizing environments. This is the result of thermal shock spalling. In the dynamic environment of a gas turbine engine, for example, temperature fluctuations caused by the mixing of the hot combustion gases with cooler secondary air or those associated with varying power-levels give rise to thermallyinduced strains at the metal-oxide interface which are sufficiently large to eventually spall the oxide layer. This layer then reforms by the consumption of more aluminum from the interrnetallic coating phase. In general, this is a rapidly recurring process and the aluminum is more rapidly depleted from the coating phase than would be the case in a truly isothermal environment wherein no thermal shock spalling would occur. In a copending application of the same assignee, Ser. No. 734,706, filed June 5, 1968, entitled NICKEL BASE SUPERALLOY RESISTANT T OXIDA- TION-EROSION, by D. H. Boone et al., there is described a nickel-base superalloy system having an oxidation-erosion resistance significantly superior to the conventional super-alloys. While the utilization of this alloy obviates the need for coatings for satisfactory oxidation resistance, such coatings may be advantageous in some circumstances, perhaps for economic reasons. In such instances the coating herein described will be seen to have particularly advantageous properties.
SUMMARY OF THE INVENTION This invention relates to coating alloys of the type generaly identified as the nickel-aluminum interrnetallics. It contemplates a basic nickel-aluminum alloy of relatively specific chemistry containing as an essential ingredient one or more of the reactive metals.
It has been found that two factors contribute to the improved oxidation-erosion resistance of the alloys of the presentinvention. First, the chemistry of the alloy is formulated such that, upon oxidation, essentially a single oxide, specifically alumina, is formed rather than other oxides or mixtures of oxides. This is done through maintenance of a particular aluminum level in the alloy. Secondly, the alloy is provided with at least a minor amount of retained reactive metal such as yttrium, scandium, thorium, or lanthanum and the other rare earth elements.
In terms of their composition, the alloys of the present invention consist of, by weight, 14-30 percent aluminum, 0.0l-l percent reactive metal, balance nickel together with, on an optional basis, one or more of alloying ingredients compatible with the basic alloy chemistry. Specifically, the compatability of the optional ingredients must be such that they do not interfere with the basic oxidation mechanism of the alloy.
A preferred embodiment of the invention comprises an alloy consisting essentially of, by weight, about 14-25 percent aluminum, 0.0l-0.5 percent reactive metal, 15-45 percent chromium, balance nickel. This alloy possesses both oxidation-erosion and sulfidation resistance.
The most preferred coating alloy consists essentially of, by weight, 15-20 percent aluminum, 20-35 percent chromium, 0.05-0.3 percent reactive metal, balance nickel.
BRIEF DESCRIPTION OF THE DRAWING The drawing is a graph depicting the oxidationerosion behavior of an alloy of the present invention as compared to certain representative contemporary materials.
DESCRIPTION OF THE PREFERRED EMBODIMENTS Although not so confined, the alloys of the present invnetion find particular utility in imparting long-term, oxidation-erosion resistance to the gas turbine superalloys, when utilized as coatings thereon, in the dynamic oxidizing environments of gas turbine engines. Representative of the centemporary superalloys requiring such oxidation protection is the alloy identified in the industry as B-l900, the nominal composition of which, by weight, is as follows: 8 percent Cr, 10 percent Co, 1 percent Ti, 6 percent Al, 6 percent M0, 4.3 percent Ta, 0.11 percent C, 0.015 percent B, 0.07 percent Zr, balance Ni.
As previously mentioned, the prior art coatings are, in general, most commonly provided by reacting aluminum with the deoxidized surface of the article to be protected and an aluminide layer is formed with consumption of the substrate components. This aluminide layer in turn oxidizes to form the desired inert barrier oxide. However, because of the complex nature of most of the contemporary alloys, and because the coating composition thereon is derived in part from the components of the substrate alloys, it is difficult to control the coating composition so as to cause the formation of a suitable barrier oxide resistant to thermal shock spalling. This is particularly true in the case of the contemporary coatings after exposure to an oxidizing environment for an extended period of time, because in the reformation of the oxide barrier at this point the oxides reform as mixtures of many oxides due to the preferential depletion of certain species with time. Such mixtures are more prone to thermal shock spalling than the single oxide.
The alloys of the present invention are in themselves oxidation resistant and do not depend for their protective effect upon a reaction with the substrate material. Their particular formulation is such that the most desirable barrier oxide is preferentially formed in a high temperature oxidizing environment and this oxice is significantly more resistant to thermal shock spalling than that formed on competitive coatings.
The desired results in this case are achieved with a basic alloy containing, by weight, 14-30 percent aluminum, 0.01-1 percent reactive metal, balance nickel. Of course, whatever oxidation-erosion does occur with this coating, or with other coatings for that matter, results in the loss of aluminum from the system. A relatively high aluminum content is, accordingly, preferred from a durability standpoint. In addition, below about 14 percent, or possibly in some instances as low as about 12 weight percent aluminum, complete surface coverage by the desired protective oxide is not formed. The upper limit of the aluminum content, on the other hand, is established primarily by mechanical considerations. Aluminum contents in excess of about 31.5 weight percent result in the development of a brittle hyperstoichiometric beta phase of the aluminide which, while satisfactory in terms of its oxidation resistance, is in terms of its suitability to the dynamic conditions associated with jet engine operation generally unsatisfactory because of its poor mechanical properties.
Those' materials which promote adherence of the oxide to the underlying substrate will include those having an affinity for oxygen approximating or exceeding that of aluminum. As used herein, however, the term reactive metal has reference to the elements yttrium, scandium, thorium, and lanthanum and the other rare earths, including mixtures of the same.
In those environments where not only oxidation but sulfidation may also be a problem, as is the case with many if not most gas turbine engine systems, 15-45 weight percent chromium is advantageously included in the coating composition. With the chromium addition, the aluminum content of the alloy is preferably reduced and limited to a maximum of about 25 weight percent to forestall the formation of a brittle phase or phases as previously mentioned. Experimentation has also revealed that, as a general rule, the higher chromium contents are to be preferred, about 30 percent chromium representing about the optimum amount from a sulfidation standpoint.
As the best balance between chemical and physical properties, the most preferred alloy composition corre-, sponds to, by weight, l5-20 percent aluminum, -35 percent chromium, 0.05-0.3 percent reactive metal, balance nickel.
Those skilled in the art will recognize that certain other elements are known to be compatible with the basic chemistry of the present alloys. Accordingly,
. other elements such as cobalt, iron or tantalum may be advantageously added to the alloy as required in certain applications for modification of the mechanical, diffusional or hot corrosion characteristics of the coatings.
The alloys are relatively easily prepared by the conventional arc melt-drop cast technique. Among the compositions so prepared and tested were the following, by weight:
Ni 16% Al .5%Y
Ni 25% Al .5% Y
Ni 30% Al .5% Y
Ni 16% Al .1% Sc Ni 30% Al .25% Sc Ni 12% Al .85% Y Ni 12% Al .6% Nd Ni 20% Cr 14.5% Al .5% Y
Ni 30% Cr 15% Al .1% Sc Ni 15% Cr 15% Al .l% Sc Ni 15% Cr 12% Al 4% Ta .25% Sc With respect to the processes whereby the alloy is applied as a coating to the surface'to be protected, the necessary presence in the alloy of the reactive metals precludes synthesis of these alloys in coating form by the widely. used slurry or simple pack cementation techniques. It appears, however, that various of the other methods discussed in the literature including vapor deposition, plasma spraying, mechanical bonding, electrolysis, electrophoresis, gaseous ion plating and sputtering may be adapted to applying the specific compositions herein discussed. Several of these techniques have been utilized in connection with this invention as discussed in the following examples:
Example 1 A sputtering target of, by weight, Ni-26 percent Al- 0.12 percent Y was prepared by a standard arc melting process. -A 2.5 mil coating of this composition was deposited on a'specimen of 8-1900 alloy by a sputtering process. Basically this method consists of bombarding the target of correct coating composition with high energy argon ions which causes sublimation of the target material. The sublimed atoms are then condensed on the substrate alloy to form a coating of essentially the same composition as the original target material. The whole process is carried out in a vacuum of a few microns of argon.
The coated specimen of this example was tested in a hot, high velocity gas stream generated by the combustion of propane in air. The coating protected the specimen from oxidation damage for hours at 2,000 F and for a subsequent period of 37 hours at 2.100" F at which time the test was terminated to permit metallographic examination of the specimen.
Example 2 A sputtering target of, by weight; Ni-30 percent Cr 12 percent Al 0.5 percent Sc was prepared as above. A one mil coating of this composition was deposited on a 8-1900 specimen by the sputtering technique described above.
Testing of this specimen was conducted in a hot high velocity propane exhaust stream contaminated with 0.4 percent sulfur (sulfur/fuel ratio) and 3.5 ppm sea salt (salt/air ratio) to simulated gas turbine hot corrosion (sulfidation) conditions. At a specimen temperature of l,650 F, the test article survived for a total of 330 hours. Uncoated 8-1900 is catastrophically attacked under these test conditions.
Example 3 An ingot of the composition, by weight, Ni 28 percent Cr 14 percent Al 0.4 percent Y was prepared by a standard melting method. A B-l900 erosion bar was coated to a thickness of 4.5 mils of this composition by electron beam evaporation. Subjected to dynamic oxidation-erosion in J PSR fuel exhaust at 2,00() F the erosion bar was protected from oxidavention, some of which are discussed herein, will be evident to those skilled in the art from the teachings herein and will, in the true spirit of the invention, be embraced within the scope of the appended claims.
1. An oxidation-erosion resistant coating alloy which consists essentially of, by weight, 14-25 percent aluminum, l5-45 percent chromium, 0.01-0.5 percent yttrium, up to 10 percent of an alloying ingredient selected from the group consisting of cobalt, iron and the refractory metals, balance essentially nickel.
2. An oxidation-erosion resistant coating alloy which consists essentially of, by weight, 15-20 percent aluminum, 20-35 percent chromium, 0.05-0.33 percent yttrium, balance essentially nickel.
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US3869779 *||Jan 24, 1974||Mar 11, 1975||Nasa||Duplex aluminized coatings|
|US3890456 *||Aug 6, 1973||Jun 17, 1975||United Aircraft Corp||Process of coating a gas turbine engine alloy substrate|
|US3918139 *||Jul 10, 1974||Nov 11, 1975||United Technologies Corp||MCrAlY type coating alloy|
|US3928026 *||May 13, 1974||Dec 23, 1975||United Technologies Corp||High temperature nicocraly coatings|
|US3964877 *||Aug 22, 1975||Jun 22, 1976||General Electric Company||Porous high temperature seal abradable member|
|US3993454 *||Jun 23, 1975||Nov 23, 1976||United Technologies Corporation||Alumina forming coatings containing hafnium for high temperature applications|
|US4005989 *||Jan 13, 1976||Feb 1, 1977||United Technologies Corporation||Coated superalloy article|
|US4013424 *||Dec 12, 1974||Mar 22, 1977||Rolls-Royce (1971) Limited||Composite articles|
|US4022587 *||Sep 8, 1975||May 10, 1977||Cabot Corporation||Protective nickel base alloy coatings|
|US4029477 *||Oct 29, 1975||Jun 14, 1977||General Electric Company||Coated Ni-Cr base dispersion-modified alloy article|
|US4080486 *||Sep 24, 1974||Mar 21, 1978||General Electric Company||Coating system for superalloys|
|US4094673 *||Nov 2, 1976||Jun 13, 1978||Brunswick Corporation||Abradable seal material and composition thereof|
|US4101713 *||Jan 14, 1977||Jul 18, 1978||General Electric Company||Flame spray oxidation and corrosion resistant superalloys|
|US4139376 *||Nov 2, 1976||Feb 13, 1979||Brunswick Corporation||Abradable seal material and composition thereof|
|US4246323 *||Sep 11, 1979||Jan 20, 1981||United Technologies Corporation||Plasma sprayed MCrAlY coating|
|US4248940 *||Jun 30, 1977||Feb 3, 1981||United Technologies Corporation||Thermal barrier coating for nickel and cobalt base super alloys|
|US4275090 *||Oct 15, 1979||Jun 23, 1981||United Technologies Corporation||Process for carbon bearing MCrAlY coating|
|US4275124 *||Oct 15, 1979||Jun 23, 1981||United Technologies Corporation||Carbon bearing MCrAlY coating|
|US4346137 *||Dec 19, 1979||Aug 24, 1982||United Technologies Corporation||High temperature fatigue oxidation resistant coating on superalloy substrate|
|US4518406 *||Dec 6, 1983||May 21, 1985||Owens-Corning Fiberglas Corporation||Drain bushing|
|US4536202 *||Dec 6, 1983||Aug 20, 1985||Owens-Corning Fiberglas Corporation||Drain bushing|
|US4615865 *||Jul 12, 1983||Oct 7, 1986||United Technologies Corporation||Overlay coatings with high yttrium contents|
|US4711665 *||Jul 26, 1985||Dec 8, 1987||Pennsylvania Research Corporation||Oxidation resistant alloy|
|US4889589 *||Apr 11, 1988||Dec 26, 1989||United Technologies Corporation||Gaseous removal of ceramic coatings|
|US5015502 *||Nov 8, 1989||May 14, 1991||Allied-Signal Inc.||Ceramic thermal barrier coating with alumina interlayer|
|US5126213 *||May 17, 1988||Jun 30, 1992||The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland||Coated near-alpha titanium articles|
|US5277936 *||Nov 19, 1987||Jan 11, 1994||United Technologies Corporation||Oxide containing MCrAlY-type overlay coatings|
|US5352540 *||Aug 26, 1992||Oct 4, 1994||Alliedsignal Inc.||Strain-tolerant ceramic coated seal|
|US5397649 *||Aug 26, 1992||Mar 14, 1995||Alliedsignal Inc.||Intermediate coating layer for high temperature rubbing seals for rotary regenerators|
|US5455119 *||Nov 8, 1993||Oct 3, 1995||Praxair S.T. Technology, Inc.||Coating composition having good corrosion and oxidation resistance|
|US5716720 *||Mar 21, 1995||Feb 10, 1998||Howmet Corporation||Thermal barrier coating system with intermediate phase bondcoat|
|US5824423 *||Feb 7, 1996||Oct 20, 1998||N.V. Interturbine||Thermal barrier coating system and methods|
|US5856027 *||Mar 31, 1997||Jan 5, 1999||Howmet Research Corporation||Thermal barrier coating system with intermediate phase bondcoat|
|US6132890 *||Mar 23, 1998||Oct 17, 2000||Tocalo Co., Ltd.||High-temperature spray coated member and method of production thereof|
|US6180259 *||Mar 23, 1998||Jan 30, 2001||Tocalo Co., Ltd.||Spray coated member resistant to high temperature environment and method of production thereof|
|US6532657 *||Sep 21, 2001||Mar 18, 2003||General Electric Co.,||Pre-service oxidation of gas turbine disks and seals|
|US6607789||Apr 26, 2001||Aug 19, 2003||General Electric Company||Plasma sprayed thermal bond coat system|
|US6696176||Mar 6, 2002||Feb 24, 2004||Siemens Westinghouse Power Corporation||Superalloy material with improved weldability|
|US6924045||May 3, 2002||Aug 2, 2005||Alstom Technology Ltd||Bond or overlay MCrAIY-coating|
|US6942929 *||Jan 8, 2002||Sep 13, 2005||Nianci Han||Process chamber having component with yttrium-aluminum coating|
|US7014923||Sep 6, 2002||Mar 21, 2006||Alstom Technology Ltd||Method of growing a MCrAlY-coating and an article coated with the MCrAlY-coating|
|US7052782||Jul 19, 2004||May 30, 2006||Alstom Technology Ltd.||High-temperature protection layer|
|US7094475||Sep 6, 2002||Aug 22, 2006||Alstom Technology Ltd||MCrAlY-coating|
|US7150798||Dec 4, 2003||Dec 19, 2006||Alstom Technology Ltd.||Non-destructive testing method of determining the service metal temperature of a component|
|US7175720||Dec 4, 2003||Feb 13, 2007||Alstom Technology Ltd||Non-destructive testing method of determining the depletion of a coating|
|US7264887||Jul 8, 2004||Sep 4, 2007||Alstom Technology Ltd.||MCrAlY bond coating and method of depositing said MCrAlY bond coating|
|US7371467 *||Apr 13, 2004||May 13, 2008||Applied Materials, Inc.||Process chamber component having electroplated yttrium containing coating|
|US7455913||Jan 10, 2006||Nov 25, 2008||United Technologies Corporation||Thermal barrier coating compositions, processes for applying same and articles coated with same|
|US7579087||Jan 10, 2006||Aug 25, 2009||United Technologies Corporation||Thermal barrier coating compositions, processes for applying same and articles coated with same|
|US7622195||Jan 10, 2006||Nov 24, 2009||United Technologies Corporation||Thermal barrier coating compositions, processes for applying same and articles coated with same|
|US7833401||Nov 16, 2010||Applied Materials, Inc.||Electroplating an yttrium-containing coating on a chamber component|
|US7879457 *||Feb 1, 2011||Praxair S. T. Technology, Inc.||Thermal spray coatings and applications therefor|
|US7883784 *||Feb 8, 2011||Praxair S. T. Technology, Inc.||Thermal spray coatings and applications therefor|
|US7910225||Mar 22, 2011||Praxair S.T. Technology, Inc.||Low thermal expansion bondcoats for thermal barrier coatings|
|US8007899||Aug 30, 2011||United Technologies Corporation||Segmented abradable coatings and process(es) for applying the same|
|US8110086||Oct 31, 2007||Feb 7, 2012||Applied Materials, Inc.||Method of manufacturing a process chamber component having yttrium-aluminum coating|
|US8114525||May 8, 2008||Feb 14, 2012||Applied Materials, Inc.||Process chamber component having electroplated yttrium containing coating|
|US8182881||Dec 24, 2008||May 22, 2012||United Technologies Corporation||Methods for reducing stress when applying coatings, processes for applying the same and their coated articles|
|US8529999||Aug 24, 2009||Sep 10, 2013||United Technologies Corporation||Thermal barrier coating application processes|
|US8802199||Dec 31, 2009||Aug 12, 2014||United Technologies Corporation||Method for microstructure control of ceramic thermal spray coating|
|US8808852||Jul 11, 2007||Aug 19, 2014||United Technologies Corporation||Process for controlling fatigue debit of a coated article|
|US9012030||Feb 7, 2012||Apr 21, 2015||Applied Materials, Inc.||Process chamber component having yttrium—aluminum coating|
|US20040079648 *||Oct 15, 2003||Apr 29, 2004||Alstom (Switzerland) Ltd.||Method of depositing an oxidation and fatigue resistant MCrAIY-coating|
|US20040108019 *||Dec 4, 2003||Jun 10, 2004||Alstom Technology Ltd.||Non-destructive testing method of determining the depletion of a coating|
|US20040159376 *||Dec 4, 2003||Aug 19, 2004||Alstom Technology Ltd||Non-destructive testing method of determining the service metal temperature of a component|
|US20040159552 *||Dec 4, 2003||Aug 19, 2004||Alstom Technology Ltd.||Method of depositing a local MCrAIY-coating|
|US20040163583 *||Dec 4, 2003||Aug 26, 2004||Alstom Technology Ltd.||Method of depositing a local MCrAIY-coating|
|US20040191545 *||Apr 13, 2004||Sep 30, 2004||Applied Materials, Inc.||Process chamber component having electroplated yttrium containing coating|
|US20040234808 *||Sep 6, 2002||Nov 25, 2004||Alexander Schnell||Mcraly-coating|
|US20040244676 *||Sep 6, 2002||Dec 9, 2004||Alexander Schnell||Method of growing a mcraly-coating and an article coated with the mcraly-coating|
|US20050003227 *||Jul 8, 2004||Jan 6, 2005||Alstom Technology Ltd||MCrAIY bond coating and method of depositing said MCrAIY bond coating|
|US20050042474 *||Jul 19, 2004||Feb 24, 2005||Hans-Peter Bossmann||High-temperature protection layer|
|US20070160873 *||Jan 10, 2006||Jul 12, 2007||United Technologies Corporation||Thermal barrier coating compositions, processes for applying same and articles coated with same|
|US20070187005 *||Feb 7, 2007||Aug 16, 2007||Taylor Thomas A||Alloy powders and coating compositions containing same|
|US20070190354 *||Feb 7, 2007||Aug 16, 2007||Taylor Thomas A||Low thermal expansion bondcoats for thermal barrier coatings|
|US20070207328 *||Mar 1, 2006||Sep 6, 2007||United Technologies Corporation||High density thermal barrier coating|
|US20070231589 *||Apr 4, 2006||Oct 4, 2007||United Technologies Corporation||Thermal barrier coatings and processes for applying same|
|US20070281103 *||Aug 1, 2007||Dec 6, 2007||Alstom Technology Ltd||MCrAIY BOND COATING AND METHOD OF DEPOSITING SAID MCrAIY BOND COATING|
|US20080017516 *||Jun 21, 2007||Jan 24, 2008||Applied Materials, Inc.||Forming a chamber component having a yttrium-containing coating|
|US20080032105 *||Feb 7, 2007||Feb 7, 2008||Taylor Thomas A||Low thermal expansion bondcoats for thermal barrier coatings|
|US20080113217 *||Jan 10, 2006||May 15, 2008||United Technologies Corporation||Thermal barrier coating compositions, processes for applying same and articles coated with same|
|US20080113218 *||Jan 10, 2006||May 15, 2008||United Technologies Corporation||Thermal barrier coating compositions, processes for applying same and articles coated with same|
|US20080166489 *||Aug 4, 2005||Jul 10, 2008||United Technologies Corporation||Method for microstructure control of ceramic thermal spray coating|
|US20080199684 *||Feb 7, 2008||Aug 21, 2008||Prasad Shrikrisnna Apte||Thermal spray coatings and applications therefor|
|US20080199722 *||Feb 7, 2008||Aug 21, 2008||Prasad Shrikrishna Apte||Thermal spray coatings and applications therefor|
|US20080223725 *||May 8, 2008||Sep 18, 2008||Applied Materials, Inc.||Process chamber component having electroplated yttrium containing coating|
|US20090308733 *||Dec 17, 2009||United Technologies Corporation||Thermal Barrier Coating Compositions, Processes for Applying Same and Articles Coated with Same|
|US20100047075 *||Nov 2, 2009||Feb 25, 2010||United Technologies Corporation||Thermal Barrier Coating Compositions, Processes for Applying Same and Articles Coated with Same|
|US20100098923 *||Oct 5, 2006||Apr 22, 2010||United Technologies Corporation||Segmented abradable coatings and process (ES) for applying the same|
|US20100151230 *||Jul 11, 2007||Jun 17, 2010||United Technologies Corporation||Process for controlling fatigue debit of a coated article|
|US20100159149 *||Dec 24, 2008||Jun 24, 2010||United Technologies Corporation||Apparatus for reducing stress when applying coatings, processes for applying the same and their coated articles|
|US20100196663 *||Apr 9, 2010||Aug 5, 2010||United Technologies Corporation||Segmented Abradable Coatings and Process(es) for Applying the Same|
|US20100260613 *||Dec 22, 2006||Oct 14, 2010||United Technologies Corporation||Process for preventing the formation of secondary reaction zone in susceptible articles, and articles manufactured using same|
|US20120156054 *||Dec 15, 2010||Jun 21, 2012||General Electric Company||Turbine component with near-surface cooling passage and process therefor|
|USRE31339 *||Sep 24, 1979||Aug 9, 1983||Howmet Turbine Components Corporation||Process for producing elevated temperature corrosion resistant metal articles|
|USRE33876 *||Oct 10, 1989||Apr 7, 1992||United Technologies Corporation||Thermal barrier coating for nickel and cobalt base super alloys|
|CN103911581A *||Mar 24, 2014||Jul 9, 2014||燕山大学||Preparation method of zirconia thermal barrier coating based on roller|
|CN103911581B *||Mar 24, 2014||Mar 2, 2016||燕山大学||一种基于轧辊的氧化锆热障涂层的制备方法|
|DE2520192A1 *||May 6, 1975||Nov 27, 1975||United Technologies Corp||Hitzbestaendige nicocraly-beschichtungen|
|DE2530197A1 *||Jul 5, 1975||Jan 29, 1976||United Technologies Corp||Ueberzugslegierungen des mcraly typs|
|DE2640829A1 *||Sep 10, 1976||Mar 17, 1977||United Technologies Corp||Waermesperrueberzug fuer superlegierungen auf nickelbasis|
|DE2842848A1 *||Oct 2, 1978||Apr 19, 1979||United Technologies Corp||Ueberzogener gegenstand, insbesondere superlegierungsgasturbinenschaufel|
|DE3229293A1 *||Aug 5, 1982||Mar 24, 1983||United Technologies Corp||Deckbelaege fuer superlegierungen|
|EP0061322A2 *||Mar 19, 1982||Sep 29, 1982||Hitachi, Ltd.||Alloy coated metal structure having excellent resistance to high-temperature corrosion and thermal shock|
|EP0780484A1||Dec 13, 1996||Jun 25, 1997||General Electric Company||Thermal barrier coated articles and method for coating|
|EP1342803A2 *||Jan 22, 2003||Sep 10, 2003||Siemens Westinghouse Power Corporation||Superalloy material with improved weldability|
|EP1752553A2||Aug 4, 2006||Feb 14, 2007||United Technologies Corporation||Method for microstructure control of ceramic thermal spray coating|
|EP1798300A1 *||Dec 16, 2005||Jun 20, 2007||Siemens Aktiengesellschaft||Alloy, protective coating to protect a part against corrosion and/or oxidation at high temperatures and component|
|EP1829984A1||Mar 1, 2007||Sep 5, 2007||United Technologies Corporation||High Density Thermal Barrier Coating|
|EP1939326A2||Dec 11, 2007||Jul 2, 2008||United Technologies Corporation||Process for preventing the formation of secondary reaction zone in susceptible articles, and articles manufactured using same|
|EP2014786A1||Jul 9, 2008||Jan 14, 2009||United Technologies Corporation||Process for controlling fatigue debit of a coated article|
|EP2204465A2||Sep 21, 2009||Jul 7, 2010||United Technologies Corporation||Apparatus for reducing stress when applying coatings, processes for applying the same and their coated articles|
|WO1988009397A1 *||May 17, 1988||Dec 1, 1988||The Secretary Of State For Defence In Her Britanni||COATED NEAR -alpha TITANIUM ARTICLES|
|U.S. Classification||420/443, 428/938, 428/680, 420/452, 428/667|
|International Classification||C23C14/16, C23C4/08, C22C19/05, C22C19/00|
|Cooperative Classification||C23C4/085, C23C14/16, C22C19/007, Y10S428/938, C22C19/052|
|European Classification||C23C4/08B, C23C14/16, C22C19/00D, C22C19/05P2|