Abstract:
In an embodiment, a bearing assembly includes superhard bearing elements distributed circumferentially about an axis. At least one of the superhard bearing elements may include a first arcuate end portion, a second arcuate end portion, a first substantially planar face, a second substantially planar face, and a bearing surface. The first and second arcuate end portions may be generally opposite each other. The first substantially planar face may extend between the first and second arcuate end portions. The second substantially planar face may be generally opposite the first substantially planar face. The first substantially planar face may have a length greater than a length of the second substantially planar face. The bearing surface may extend between the first arcuate end portion, the second arcuate end portion, the first substantially planar face, and the second substantially planar face. The bearing assembly includes a support ring that carries the superhard bearing elements.
Abstract:
Ein Verfahren zum Reparieren eines Bauteils (406), insbesondere eines Gasturbinenbauteils, welches aus einem Basismaterial mit einer gerichteten Mikrostruktur hergestellt ist, umfasst die Schritte: Reinigen der Reparaturstelle (420), Füllen der Reparaturstelle (420) mit einem der Zusammensetzung des Basiswerkstoffes entsprechenden Füllmaterial, Durchführen einer Wärmebehandlung im Bereich der gefüllten Reparaturstelle (420), wobei das Füllmaterial mikro- und/oder nanoskalige Partikel (425a, 425b) aufweist, beim Füllen der Reparaturstelle (420) Maßnahmen getroffen sind, welche die Oxidation des Füllmaterials verhindern, und die Temperaturen und Haltezeiten der Wärmebehandlung derart auf die Zusammensetzung des Füllmaterials und des Basismaterials des Bauteils (406) abgestimmt sind, dass eine epitaktische Anbindung des Füllmaterials an das umgebende Basismaterial erfolgt.
Abstract:
An airfoil includes an airfoil body that extends at least between leading and trailing edges, first and second sides, and radially inner and outer ends. The airfoil body includes an aluminum alloy that has a controlled crystallographic texture with respect to a predefined three-dimensional coordinate system. The airfoil can be used in the fan of a gas turbine engine.
Abstract:
Embodiments of the invention are directed to compact bearing assemblies configured to operate in small spaces and/or in harsh environments, bearing apparatuses including such bearing assemblies, and method of operating such bearing assemblies and apparatuses. For instance, one or more compact bearing assemblies may at least partially rotatably secure a shaft of a power generation unit to a housing thereof. Also, a first compact bearing assembly (100) may connect or couple to the shaft and may rotatably engage a second compact bearing assembly (200), which may be connected or otherwise secured to the housing.
Abstract:
An article includes a body that has a coating thereon. The coating has a first portion disposed on a first section of the body and a second portion disposed on a second, different section of the body. The first portion has a first microstructure and the second portion has a second, different microstructure.
Abstract:
The invention relates to a turbo-machine (1), comprising a flow channel (5) for a working fluid (A). Said flow channel is delimited by a channel wall (15) with a surface structure (47) that is resistant to wetting by the working fluid (A).The invention also relates to a turbine blade comprising a blade surface (39) which can be subjected to the action of a working fluid (A). Said blade surface has a surface structure which specifically uses the Lotus effect and is resistant to wetting by the working fluid (A); at least in parts.
Abstract:
Es wird ein Verfahren zum Wideraufbereiten eines betriebsbedingt lokal geschädigten Bauteils (120) mit einer ursprünglich kubischen γ/γ' -Mikrostruktur, wobei die betriebsbedingte lokale Schädigung in einer entlang einer Ausdehnungsrichtung gerichteten Vergröberung der γ/γ' -Mikrostruktur besteht, zur Verfügung gestellt. In dem Verfahren wird die Ausdehnungsrichtung der gerichtet vergröberten γ/γ' -Mikrostruktur durch lokales Erwärmen und Einbringen einer Zug- und oder Druckspannung (503, 505), insbesondere im Bereich einer lokalen Schädigung des Bauteils, in ihrer Orientierung gedreht.
Abstract:
Diamond surfaces for electric submersible pump (ESP) components are provided. A layer of diamond is deposited, adhered, or sintered directly or indirectly to component surfaces subject to wear, erosion, or abrasion to form at least a partial coating. The diamond surfaces increase longevity and reliability of the ESP by reducing friction, wear, and operating temperature. The diamond surfaces may take several forms, such as an amorphous diamond layer, a polycrystalline diamond (PCD) layer, or a thermally stable polycrystalline (TSP) diamond layer. Diamond surfaces may be used to protect bearings, thrust washers, shafts, sliding surfaces, wet areas, hydraulic flow surfaces in cavities, fluid intake ports, downthrust and upthrust pads, bearing runners, shaft seals, face-seals, hydraulic seals, clearance seals, and other surfaces susceptible to erosion or abrasion in the ESP.
Abstract:
Durch die gezielte Auswahl von Verfahrensparametern bei Laserschweißen, Vorschub, Laserleistungsstrahldurchmesser und Pulvermassenstrom kann der Temperaturgradient gezielt eingestellt werden, der wesentlich entscheidend ist zum einkristallinen Wachstum beim Laserauftragsschweißen.
Abstract:
A gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature dwell capabilities, including creep and dwell fatigue crack growth behavior. The superalloy contains, by weight, 10.00 to 22.0% cobalt, 10.0 to 14.0% chromium, 4.0 to 6.0% tantalum, 2.0 to 4.0% aluminum, 2.0 to 6.0%) titanium, 1.5 to 5.0% tungsten, 1.5 to 5.0% molybdenum, 1.0 to 3.5% niobium, 0.05 to 0.6% hafnium, 0.02 to 0.10% carbon, 0.01 to 0.40 % boron, 0.02 to 0.10% zirconium, the balance essentially nickel and impurities, wherein the titanium: aluminum weight ratio is 0.7 to 1.5. The superalloy is hot worked and heat treated to contain cellular gamma prime precipitates that distort grain boundaries, creating tortuous grain boundary fracture paths that are believed to promote the fatigue crack growth resistance of the superalloy.