An ammonia plant synthesis gas compressor train includes a steam turbine; and a compression unit that compresses a synthesis gas by being rotationally driven by the steam turbine. The compression unit includes a rotary shaft that rotates around an axis, and a plurality of impellers that are provided on the rotary shaft at intervals in a direction of the axis and are rotated integrally with the rotary shaft to pump a gas outward in a radial direction to compress the gas. In at least one of the impellers, a maximum operating peripheral speed at a radially outermost position of the impeller is within a range of 290 m/s to 390 m/s, a yield strength is 827 MPa or less, and a Vickers hardness is 311 or less.

One exemplary embodiment of this disclosure relates to a method of forming an engine component. The method includes forming an engine component having an internal passageway, the internal passageway formed with an initial dimension. The method further includes establishing a flow of machining fluid within the internal passageway, the machining fluid changing the initial dimension.

Embodiments of the invention are directed to a rotor for use in molten metal and devices including the rotor. The rotor has a rotor body and blades, wherein each blade includes a tip that is at least twice as hard as the rotor body.

A turbocharger, has a turbine for expanding a first medium and a compressor for compressing a second medium. The turbine includes a turbine housing and a turbine rotor. The compressor includes a compressor housing and a compressor rotor coupled to the turbine rotor via a shaft. A bearing housing is arranged between the compressor and turbine housings in which the shaft is mounted. The turbine and bearing housings are connected via a fastening device mounted on a flange of the turbine housing with a first section and a second section that covers a flange of the bearing housing at least in sections. The fastening device is contoured curved on a surface of the second section facing the flange of the bearing housing.

A composite blade includes a composite blade body including reinforced fibers and resin; a metal layer provided on an outer side of a leading edge section including a leading edge that is a part of the composite blade body on an upstream side of an air stream, the metal layer having a thickness of equal to or larger than 5 micrometers and equal to or smaller than 100 micrometers; an adhesive layer provided between the composite blade body and the metal layer to bond the metal layer to the composite blade body; and an electric insulating layer provided in contact with a surface of the leading edge section of the composite blade body, the surface being on the side on which the metal layer is provided, the electric insulating layer having an electric insulating property.

The present invention discloses a turbine engine with at least a high pressure and a low pressure turbine section comprising a casing and at least one turbine blade rotatably mounted within the casing wherein at least part of the inner surface of the casing is covered with shrouds as abradables to provide clearance control between the inner surface and the tip of the at least one blade and wherein the tip of the blade is coated with a hard PVD coating, characterized in that the shroud material of at least the high pressure and/or the low pressure section comprises a porous ceramic based material and the hard PVD coating on the tip of the blade essentially consists of a droplet free nitride coating.

A sliding part with a wear resistant coating includes a sliding part, and a wear resistant coating provided on a sliding surface of the sliding part, and made of a cobalt alloy containing chromium and silicon. In the wear resistant coating, oxide particles are dispersed which include an oxide containing chromium and silicon, and have a particle size of 100 m or less when a cross section of the wear resistant coating is observed using an optical microscope with a magnification of 100 times.

An article has a cavity defined by an inner surface, the cavity having a size such that a largest sphere placeable in the cavity has a diameter of less than 7 cm and a smallest sphere placeable in the cavity has a diameter of 0.5 mm; and a hard coating on the inner surface, the hard coating having a hardness between 18 to 100 GPa, the hard coating distributed on the inner surface such that a ratio of a coating thickness at a first region of the hard coating to that at a second region of the hard coating ranges from 0.75 to 1.33.

A journal bearing including a plurality of bearing pads having pad surfaces which configured to slidably come into contact with an outer circumferential surface of a rotating shaft and disposed at intervals, a key member provided a part of a pad rear surface which faces radially outward in the bearing pad, having a curved surface which is curved around an axis parallel to the central axis, configured to extend to have the same cross-sectional shape, and formed of a material having a hardness higher than that of a material forming the pad rear surface of the bearing pad, and a housing having a support surface in contact with a part of the curved surface of the key member in the circumferential direction and configured to support the key member and the bearing pad to be swingable from an outer side in a radial direction.

A hydrostatic seal assembly includes a seal support, a seal shoe integral to the seal support and radially movable relative to the seal support. A plurality of seal teeth are located at a radially inboard surface of the seal shoe. The seal shoe is formed from a first material and the radially inboard surface is formed from a second material softer than the first material such that the radially inboard surface is abradable in the event of a rub between the radially inboard surface and an adjacent rotating component.