Abstract: A seal system, for an apparatus that includes a rotatable portion with airfoils coupled thereto and a stationary portion with an inner surface, includes an abradable portion including at least one abradable layer of an abradable material formed over the inner surface. The seal system also includes an abrading portion disposed over at least a portion of a substrate of the airfoil. The abrading portion includes at least one abrading layer formed on at least a portion of the substrate and a plurality of abrasive particles embedded within the abrading layer. The plurality of abrasive particles includes at least one of substantially all of one of tantalum carbide (TaC), aluminum oxide (Al2O3), and ziconia (ZrO2), cubic boron nitride (cBN) and Al2O3 in predetermined ratios, cBN, Al2O3 and ZrO2 in predetermined ratios, Al2O3 and ZrO2 fused together in predetermined ratios, and TaC and Al2O3 in predetermined ratios.

Abstract: A compressor blade generally used in turbine engines is presented. The compressor blade includes a protective covering bonded to a tip portion of the blade with a braze material. The braze material includes from about 1 weight percent to about 10 weight percent of an active metal element, based on the total amount of the braze material. A compressor rotor is also provided that includes a plurality of the compressor blades. A method for joining a protective covering to a tip portion of a compressor blade, and a method for repair of a compressor blade, are also provided.

Abstract: A compressor blade and process for inhibiting rub encounters between a blade tip of the blade and an interior surface of a case that surrounds the rotating hardware within a compressor section of a turbomachine. The compressor blade includes a cap that defines the blade tip at a radially outermost end of the blade, and a plurality of flexible elements extending from a surface of the cap that defines the blade tip. The flexible elements extend from the surface in a span-wise direction of the blade, and are operable to become rigid due to centrifugal stiffening at compressor operating speeds and, optionally, cut a groove the interior surface of the case.

Abstract: A coated article, a process of coating an article, and a process of using an article are disclosed. The coated article includes a substrate, a porous coating material, and a thermal barrier coating material. The porous coating material includes a porosity between about 1 percent and about 20 percent, by volume. The thermal barrier coating material has a thermal conductivity that is lower than a thermal conductivity of the substrate. The porous coating material differs in one or both of composition and microstructure from the thermal barrier coating material. Additionally or alternatively, the porous coating material resists at least one of sintering, densification, and phase destabilization for a predetermined period at a predetermined temperature. The process of coating an article includes applying a coating to form the coated article.

Abstract: A seal system, for an apparatus that includes a rotatable portion with airfoils coupled thereto and a stationary portion with an inner surface, includes an abradable portion including at least one abradable layer of an abradable material formed over the inner surface. The seal system also includes an abrading portion disposed over at least a portion of a substrate of the airfoil. The abrading portion includes at least one abrading layer formed on at least a portion of the substrate and a plurality of abrasive particles embedded within the abrading layer. The plurality of abrasive particles includes at least one of substantially all of one of tantalum carbide (TaC), aluminum oxide (Al2O3), and ziconia (ZrO2), cubic boron nitride (cBN) and Al2O3 in predetermined ratios, cBN, Al2O3 and ZrO2 in predetermined ratios, Al2O3 and ZrO2 fused together in predetermined ratios, and TaC and Al2O3 in predetermined ratios.

Abstract: A method of machining a profile pattern in a ceramic coating of a turbine shroud is provided and includes applying the ceramic coating substantially uniformly onto the turbine shroud, positioning a machining tool proximate the ceramic coating, and removing material from the ceramic coating by activating the machining tool to machine the ceramic coating and by moving the machining tool across the ceramic coating in a movement pattern that generally corresponds to the profile pattern.

Abstract: A coated article and a coating application process are disclosed. The coated article includes a metallic surface, a first layer positioned proximal to the metallic surface, the first layer having a first ductility, and a second layer positioned distal from the metallic surface, the second layer having a second ductility. The first ductility is at least about 20% greater than the second ductility. The process includes providing an article, the article comprising a metallic surface, applying a first layer proximal to the metallic surface, the first layer having a first ductility, and applying a second layer distal from the metallic surface, the second layer having a second ductility.

Abstract: Disclosed is a coating, a turbine component, and a process of fabricating a turbine component. The coating includes a ceramic phase formed by ceramic particles and a ductile matrix having a ductility greater than the ceramic phase. The ceramic phase includes substantially the same microstructure as the ceramic particles. The turbine component includes a surface having the coating. The process includes applying the coating to the surface of the turbine component.

Abstract: A compressor blade and process for inhibiting rub encounters between a blade tip of the blade and an interior surface of a case that surrounds the rotating hardware within a compressor section of a turbomachine. The compressor blade includes a cap that defines the blade tip at a radially outermost end of the blade, and a plurality of flexible elements extending from a surface of the cap that defines the blade tip. The flexible elements extend from the surface in a span-wise direction of the blade, and are operable to become rigid due to centrifugal stiffening at compressor operating speeds and, optionally, cut a groove the interior surface of the case.

Abstract: In one embodiment, an abradable seal includes a soft material that may be worn away and a hard material that may provide mechanical strength for the abradable seal. The soft material and the hard material may include different compositions of a base material.

Abstract: A process for erosion testing of a specimen article includes securing a test specimen in a test rig; measuring physical characteristics of the test specimen article; using a thermal spray coating apparatus, flowing incident particles at the test specimen; and re-measuring the physical characteristics of the test specimen.

Abstract: In one embodiment, an abradable seal includes a soft material that may be worn away and a hard material that may provide mechanical strength for the abradable seal. The soft material and the hard material may include different compositions of a base material.

Abstract: A process for erosion testing of a specimen article includes securing a test specimen in a test rig; measuring physical characteristics of the test specimen article; using a thermal spray coating apparatus, flowing incident particles at the test specimen; and re-measuring the physical characteristics of the test specimen.

Abstract: Methods and systems of applying a liquid precursor for a calcium-magnesium-aluminosilicate (CMAS) resistant coating to a turbine engine component are provided. In one embodiment, a method of manufacturing a turbine engine includes spraying a liquid compound, wherein the liquid component is stored with a carrier gas, applying the compound to a component of a turbine engine, such that the compound is disposed on a thermal barrier coating of the component, and forming an oxide layer on the thermal barrier coating of the component. In another embodiment, a system includes a turbine engine component and a sprayer containing a compound and a carrier gas, wherein the sprayer is configured to apply the compound to a thermal barrier coating of the component such that the compound forms an oxide on the thermal barrier coating.

Abstract: A method of machining a profile pattern in a ceramic coating of a turbine shroud is provided and includes applying the ceramic coating substantially uniformly onto the turbine shroud, positioning a machining tool proximate the ceramic coating, and removing material from the ceramic coating by activating the machining tool to machine the ceramic coating and by moving the machining tool across the ceramic coating in a movement pattern that generally corresponds to the profile pattern.

Abstract: A pattern for improving aerodynamic performance of a turbine includes a material disposed in a pattern at a base surface of a turbine shroud such that the material is capable of abradable contact with a tip portion of a turbine bucket. The pattern includes a first plurality of ridges disposed at the base surface such that a first portion of the first plurality of ridges corresponding to a back portion of the turbine bucket is oriented at a first angle with respect to an axis of rotation of the turbine bucket. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.

Abstract: An article of manufacture pattern for improving aerodynamic performance of a turbine including an abradable material capable of abradable contact. The abradable material is disposed in a pattern. The pattern includes a first plurality of ridges disposed at a base surface of the turbine. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.

Abstract: A system and method for performing laser plasma spectroscopy on a surface of a component, particularly to detect, analyze, and determine the extent of deposit build up on turbomachine components protected by coatings that are susceptible to damage from infiltration of deposits. The system includes a laser energy source and a probe interconnected with the laser energy source to receive a laser beam therefrom and then direct the laser beam onto the surface of the component and scan an area of the surface while the component remains stationary. The probe is further configured to collect radiation emitted from a laser-induced plasma generated by the laser beam at the surface of the component. The system is further equipped to transmit the radiation from the probe and spectrally analyze the radiation.

Abstract: Erosion resistant coating processes and material improvements for line-of-sight applications. The erosion resistant coating composition includes nanostructured grains of tungsten carbide (WC) and/or submicron sized grains of WC embedded into a cobalt chromium (CoCr) binder matrix. A high velocity air fuel thermal spray process (HVAF) is used to create thick coatings in excess of about 500 microns with high percentages of primary carbide for longer life better erosion resistant coatings. These materials and processes are especially suited for hydroelectric turbine components.

Abstract: A bi-layer bond coating for use on metal alloy components exposed to hostile thermal and chemical environment, such as a gas turbine engine, and the method for applying such coatings. The preferred coatings include a bi-layer bond coat applied to the metal substrate using high velocity oxy-fuel (HVOF) thermal spraying. Bi-layer bond coatings in accordance with the invention consist of a dense first inner layer (such as iron, nickel or cobalt-based alloys) that provides oxidation protection to the metal substrate, and a second outer layer having controlled porosity that tends to promote roughness, mechanical compliance, and promotes adherence of the thermal barrier coating (TBC). Preferably, the outer, less dense layer of the bi-layer bond coat is formed from a mixture of metallic powder and polyester to adjust and control the porosity, but without sacrificing mechanical compliance.