Patent Application
20130316086
The present invention generally relates to the field of wear resistant coatings. In particular, the present invention relates to wear resistant coatings for carbon seals.
Successful operation and performance of gas turbine engine bearing compartment carbon seals is strongly dependent on having a hard, chemically stable, and thermal-shock resistant counterface material system. The most common arrangement involves a static carbon seal, spring and air loaded axially against a shaft co-rotating ring, known as a seal plate or seal seat. The counterface is defined as the region of the seal seat contacting the axial and/or radial face of the carbon seal.
Historically, the counterface material system has consisted of a low alloy steel protected with hard chromium plating (HCP) or by a chromium carbide-nickel chromium coating applied by a Detonation Gun (D-Gun), available from Praxair Surface Technologies, Inc. Seal applications using HCP are typically limited to lower speed applications, and the plating process generates a heavily regulated hexavalent-chromium waste stream. While a superior counterface to hard chromium plating, the chromium carbide-nickel chromium coating applied by the D-Gun can exhibit localized surface distress in the form of radial or craze-type cracks due to thermal-mechanical stresses during operation. The cracks occasionally propagate to the extent that the coating material is liberated from the coated surface, either as discrete pull-out or gross spallation.
Attempts have been made to either complement or improve upon the D-Gun technology by depositing coatings using the continuous combustion high velocity oxygen fuel (HVOF) method. These attempts have been generally unsuccessful for application to a seal seat coating running against gas turbine engine carbon seals. Potential reasons include: the coatings were developed for other types of wear applications involving different mating materials and operating environments; carbide type and chemistry not thermo-chemically stable for operation against carbon seals at high power; and microstructures, primarily phase morphology and size, were not optimized to resist the propagation of surface thermal cracks into the thickness of the coating, often resulting in a rapid and catastrophic breakdown of the coating and unacceptable levels of carbon seal wear. It would be beneficial to develop a coating applied by HVOF for use with carbon seals.
The present disclosure is directed to a method of applying a wear-resistant coating. The method comprises mixing about 75% to about 85% by weight chromium carbide and about 15% to about 25% by weight nickel chromium to form a chromium carbide-nickel chromium mixture, and simultaneously heating the chromium carbide-nickel chromium mixture to about 1371 degrees Celsius to about 2204 degrees Celsius and applying the chromium carbide-nickel chromium mixture at a velocity in a range of about 305 meters feet per second to about 915 meters per second by high velocity oxygen fuel (HVOF) spraying.
Coating 12 is applied onto surface 14 of rotating counterface 10. Surface 14 faces stationary mating surface 16. Coating 12 may be applied onto surface 14 as a dense single phase layer or as a composite. Coating 12 is formed of a chromium carbide-nickel chromium composition and may be either a blended powder or an alloyed powder. In an exemplary embodiment, coating 12 constitutes between approximately 75% and approximately 85% by weight chromium carbide and between approximately 15% and approximately 25% by weight nickel chromium. The composition preferably constitutes approximately 80% by weight chromium carbide and approximately 20% by weight nickel chromium. In an exemplary embodiment, the particle size of the chromium carbide and the nickel chromium is between approximately 16 microns and approximately 45 microns. The particle size of the chromium carbide and the nickel chromium is preferably approximately 30 microns.
Mating surface 16 is typically formed of a carbon source, such as amorphous carbon or crystalline graphite. In an exemplary embodiment, mating surface 16 is a stationary, solid graphite ring.
Prior to applying coating 12 onto counterface 10, counterface 10 is cleaned and the areas of counterface 10 that are not to be coated are masked. Surface 14 of counterface 10 is then grit-blasted to provide a roughened surface for improved coating adhesion. Coating 12 is applied onto surface 14 of counterface 10 as a clad or alloyed powder by high velocity oxy-fuel (HVOF) thermal spray process. In the HVOF thermal spray process, a high velocity gas stream is formed by continuously combusting oxygen and a gaseous or liquid fuel. A powdered form of the coating to be deposited is injected into the high velocity gas stream and the coating is heated proximate its melting point, accelerated, and directed at the substrate to be coated. The HVOF process imparts substantially more kinetic energy to the powder being deposited than many existing thermal spray coating processes. As a result, an HVOF applied coating exhibits considerably less residual tensile stresses than other types of thermally sprayed coatings. Oftentimes, the residual stresses in the coating are compressive rather than tensile. These compressive stresses also contribute to the increased coating density and higher coating thickness capability of this process compared to other coating application methods.
The particular HVOF thermal spray parameters will vary depending on numerous factors, including, but not limited to: the type of spray gun or system used, the type and size of powder employed, the fuel gas type, and the configuration of counterface 10. In an exemplary embodiment, coating 12 is sprayed onto surface 14 using a Sulzer Metco Diamond Jet Hybrid HVOF spray system with hydrogen as the fuel gas and a standard nozzle designed for hydrogen-oxygen combustion. Although hydrogen is described as the fuel gas used, kerosene or propylene may also be used as the fuel gas in other HVOF systems. In other alternate embodiments, the parameters may be modified for use with other HVOF systems and techniques using other fuels. A cooling gas, or shroud gas, may also used to in the HVOF process to help maintain the temperature of the process. In an exemplary embodiment, the flow rate of hydrogen fuel gas is between approximately 661 liters per minute (1400 cubic feet per hour at standard conditions (scfh)) and approximately 755 liters per minute (1600 scfh) and the flow rate of oxygen fuel gas is between approximately 189 liters per minute (400 scfh) and approximately 283 liters per minute (600 scfh). In an exemplary embodiment, the cooling/shroud gas is air and has a flow rate of between approximately 283 liters per minute (600 scfh) and approximately 425 liters per minute (900 scfh). Standard conditions are defined as approximately 25 degrees Celsius and approximately 1 atmosphere of pressure.
The composition of coating 12 in powder form is fed into the spray gun at a rate of between approximately 45 grams per minute and approximately 90 grams per minute. A nitrogen carrier gas in the spray gun has a flow rate of between approximately 11.8 liters per minute (25 scfh) and approximately 16.5 liters per minute (35 scfh) to provide adequate particle injection of the powder or powder alloy into the plume centerline of the HVOF system. The powder composition of coating 12 that is fed into the spray gun is heated to a temperature of between approximately 1371 degrees Celsius (2500 degrees Fahrenheit) and approximately 2204 degrees Celsius (4000 degrees Fahrenheit) and at a velocity of between approximately 305 meters per second (1000 feet per second) and approximately 915 meters per second (3000 feet per second) in the HVOF jet.
During spray deposition of coating 12, counterface 10 is rotated to produce surface speeds of between approximately 61 meters per minute (200 surface feet per minute (sfpm)) and approximately 122 meters per minute (400 sfpm). The spray gun is typically located at an outer diameter of counterface 10 and traverses in a horizontal plane across surface 14 of counterface 10 at a speed of between approximately 20.3 centimeters per minute (8 inches per minute) and approximately 101.6 centimeters per minute (40 inches per minute) and at an angle of between approximately 45 degrees and approximately 90 degrees from surface 14. In an exemplary embodiment, the spray gun is oriented at approximately 90 degrees from surface 14. While spraying coating 12 onto surface 14, the spray gun is positioned between approximately 23 centimeters (9 inches) and approximately 30.5 centimeters (12 inches) from surface 14 of counterface 10. Generally, the temperature of counterface 10 when coating 12 is being sprayed onto surface 14 is affected by factors including, but not limited to: the rotation speed of counterface 10, the surface speed, the gun traverse rate, and the size of counterface 10. To help control the temperature of counterface 10, external gas may be utilized to cool counterface 10.
Upon impact with surface 10, the composition solidifies, shrinks, and flattens against surface 10 to form coating 12. Depositing the composition in this manner allows a repeatable coating 12 with an optimized lamellar microstructure. In an exemplary embodiment, coating 12 has a predominantly lamellar splat structure with isolated regions of cuboidal carbide phases such that coating 12 is a discrete mixture of (1) cuboidal Cr3C2 carbides; (2) precipitated matrix carbides, predominately lamellar, of the form CrxCy, where x=7 to 23 and y=3 to 6; (3) fine lamellar nickel oxides; and (4) a fine lamellar Ni—Cr binder. Coating 12 has a maximum porosity of approximately 3%, a nominal oxide level of between approximately 10% and approximately 20%, and a microhardness of between approximately 850 Vickers Hardness (HV) and approximately 1150 HV. In an exemplary embodiment, coating 12 is applied onto surface 10 to a thickness of between approximately 203 microns (0.008 inches) and approximately 762 microns (0.03 inches). Preferably, coating 12 is applied onto surface 10 to a thickness of between approximately 254 microns (0.01 inches) and approximately 508 microns (0.02 inches). Coating 12 is then finished to a thickness of between approximately 76 microns (0.003 inches) and approximately 380 microns (0.015 inches).
The wear-resistant coating of the present invention has many uses, such as being used in conjunction with carbon seals, rotating shaft journal surfaces, brush seal land surfaces, and other such similar surfaces as are typically found in gas turbine engines and other rotating turbo-machinery. In other embodiments, the present invention is, however, applicable to other surfaces subject to sliding, abrasive, erosive or fretting wear, particularly for surfaces operating continuously in environments above 900° F. (˜482.2° C.). The coating is typically sprayed by high velocity oxygen fuel onto a counterface that is positioned adjacent a mating surface formed of a carbon source. The coating has a composition consisting essentially of chromium carbide and nickel chromium. Proper manipulation of the spray parameters results in the coating exhibiting particular phase distribution, morphology, oxide level, porosity, and micro-hardness. These properties enhance carbon seal or other wear system, performance by reducing thermally-induced cracking or spallation, reducing wear in mating surface, improving limits in coating build-up, and increasing repair applicability.
Although the present invention has been described with reference to preferred embodiments, workers skilled in the art will recognize that changes may be made in form and detail without departing from the spirit and scope of the invention.
This application claims priority as a divisional application under 35 U.S.C. §121 of earlier filed application Ser. No. 11/805,160 entitled “WEAR RESISTANT COATING” by Eli N. Ross and Paul H. Zajchowski and filed May 22, 2007.
This invention was made with government support under Contract Number F33657-99-D-2051 awarded by the United States Air Force. The government may have certain rights in the invention.
| Number | Date | Country | |
|---|---|---|---|
| Parent | 11805160 | May 2007 | US |
| Child | 13962477 | US |
