A turbomachine component having a main body and a multilayer coating, which is applied directly to the main body is provided. The multilayer coating is at least 5 μm and at most 35 μm thick and has a plurality of layers applied directly one on top of the other, wherein the layer applied directly to the main body is an adhesion promoting layer, which comprises chromium nitride, and at least one of the remaining layers comprises a hard material.

A gas turbine arrangement, including a gas generator section (A), a power turbine section (B), and a generator section (C) coupled on a common shaft (10). The power turbine has its bearing block (12) provided with a copper cooling cup (9), which possesses a high thermal conductivity and conveys heat flux away from the side and block of the bearing and which has a design that enables the effect of a penetrating airflow.

A composite component comprising a plurality of plies. A first set of pins extend in a direction transverse to the plies and a second set of pins extend in a direction transverse to the plies. The pins of the first set are made of a different material to the pins of the second set.

A method for treating a composite part including a metal protective duct fixed to a core by a binder, so as to be able to separate the duct from the core, including the steps of: subjecting the metal duct to compressive stresses tending to lengthen same, and b) if necessary, heating or cooling the part in order to soften or weaken the binder.

A gas turbine engine includes: a turbine section including a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating. At least one turbine blade has sides and a tip and at least one seal member is located adjacent to the tip of the at least one turbine blade. The tip of the at least one turbine blade has a wear resistant layer and an abrasive coating disposed on the wear resistant layer. The wear resistant layer has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

A gas turbine engine includes an engine static structure extending circumferentially about an engine centerline axis; a compressor section, a combustor section, and a turbine section within the engine static structure. At least one of the compressor section and the turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil. A tip of the at least one airfoil is metal having a wear resistant coating and the at least one seal member is coated with an abradable coating. The wear resistant coating is formed as a layer in a base metal surface of the airfoil, has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

A turbocharger contains a turbine housing having an accommodating region for a turbine rotor disk of the turbocharger, which accommodating region is arranged centrally with respect to a turbine housing axis, and a turbine spiral channel, which tapers helically toward the accommodating region. A wastegate valve, having a spindle arm and a valve plate arranged on the spindle arm, or a variable exhaust-gas guiding device, having bearing disks and guide vanes, is arranged in the turbine housing. At least one of the: turbine housing, spindle arm and valve plate, or bearing disks and guide vanes, has a steel material for high-temperature applications. The material composition of which contains, in addition to iron, Fe, at least the following alloying constituents in amounts within the specified limits in weight percent: carbon: 0.4-0.5%; silicon: 1.25-1.75%; manganese: 3.0-12.0%; chromium: 19.5-20.5%; nickel: 5.0-6.0%; niobium: 1.00-1.5%. The material composition ensures sufficient temperature resistance of the components.

A bearing pad for a tilting-pad bearing includes a first member having a bearing surface and a second member disposed on a back surface side of the first member. At least one of a back surface of the first member or a front surface of the second member facing the back surface of the first member has a recess for forming a cavity between the first member and the second member. Preferably, the bearing pad further includes a support member disposed on a back surface side of the second member and tiltably supporting the first member and the second member, and the recess is formed over at least a part of an installation range of the support member in a plan view of the bearing pad.

To provide a vacuum pump which separates and constructs an inlet port flange and a casing (outer cylinder) as two components to reduce weight while retaining required strength and which is consequently capable of reducing manufacturing cost. In a vacuum pump, an inlet port flange and a casing (outer cylinder) are separated from each other and constructed as different members. The inlet port flange uses stainless steel as a material thereof and the casing (outer cylinder) use aluminum as a material thereof. The components are fastened to each other by bolts and sealed by an O-ring in order to maintain a vacuum property during assembly of the vacuum pump. Accordingly, a weight of the vacuum pump can be reduced while maintaining strength of the inlet port flange.

A coated article includes a substrate and an MCrAlY coating supported on the substrate. The M includes at least one of nickel, cobalt, and iron, Cr is chromium, Al is aluminum, and Y is yttrium. The composition of the MCrAlY coating varies in an amount of at least one of Cr, Al, and Y by location on the substrate with respect to localized property requirements. In one example, the coated article is an article of a gas turbine engine.