A terrific stainless steel alloy and turbocharger kinematic components are provided. A ferritic stainless steel alloy includes or consists of, by weight, about 20% to about 35% chromium, less than about 2% nickel (i.e., from 0% to about 2%), about 1% to about 4% carbon, about 1.5% to about 1.9% silicon, less than about 0.4% nitrogen (i.e., from 0% to about 0.4%), about 0.5% to about 15% molybdenum, less than about 1% niobium (i.e., from 0% to about 1%) and a balance of iron, and other inevitable/unavoidable impurities that are present in trace amounts. The turbocharger kinematic components are made at least in part using this stainless steel alloy.

The austenitic heat resistant steel of the embodiment contains: 24 to 50% by mass of Ni, 5 to 13% by mass of Cr, 0.1 to 12% by mass of Co, 0.1 to 5% by mass of Nb, 0.1 to 0.5% by mass of V, 1.90 to 2.35% by mass of Ti, 0.01 to 0.30% by mass of Al, 0.001 to 0.01% by mass of B, 0.001 to 0.1% by mass of C, and the balance being Fe and inevitable impurities.

A method for manufacturing a shaft body by welding a plurality of shaft members together and forming the shaft body, the method including: a primary tempering step of subjecting a range in at least one of the shaft members, which is in the vicinity of an end of another shaft member side adjacent thereto, to tempering before the shaft members are welded together so that a strength of an end side of a region thereof is lower than a strength at a side which is opposite to the end of the region thereof; a welding step of welding the shaft members together after the primary tempering step; and a secondary tempering step of tempering the vicinity of a weld part between the shaft members after the welding step.

An anti-bird strike protection net for aircraft jet engine, comprising fixed circular truncated cone, conical protection net body, connection section, and double helix electrical heating wire, wherein the fixed circular truncated cone is secured on the cowl inlet's outside of the aircraft jet engine via which the conical protection net body is connected to the jet engine with the connection section: hinge, catches, and gas springs; The conical protection net body comprises the base of the conical protection net body, the conical support frame, the net which covers the outside of the conical support frame; the double helix electrical heating wire spirally surrounding the surface of the net is used as deicing device.

This invention is an aftermarket add-on device and can be an original integration part as jet engine manufacturing. It's simple and easy to be secured on the cowl inlet without changing the structure of the aircraft jet engine.

This disclosure describes new high temperature, radiation-resistant, ferritic-martensitic steel compositions. The new steels generally contain 9.0-12.0 wt. % Cr, 0.001-1.0 wt. % Mn, 0.001-2.0 wt. % Mo, 0.001-2.5 wt. % W, and 0.1-0.3 wt. % C, with the balance being primarily Fe. More specifically, steels having from 10.0-12.0 wt. % Cr are considered particularly advantageous. Small amounts of N, Nb, V, Ta, Ti, Zr, and B may or may not also be present, depending on the particular embodiment. Impurities may be present in any embodiment, in particular impurities of less than 0.01 wt. % S, less than 0.04 wt. % P, less than 0.04 wt. % Cu, less than 0.05 wt. % Co, and less than 0.03 wt. % As are contemplated. Examples of these steels exhibit improved fracture toughness and reduced thermal creep and swelling.

It is an objective of the invention to provide a steam turbine rotor that is capable of both reducing SCC susceptibility and improving LCF life thereof. There is provided a steam turbine rotor, comprising a rotor disk in a low pressure final stage L-0, and another rotor disk in a plurality of stages including a stage L-1 positioned closer to a high pressure side than the low pressure final stage L-0, the rotor disk in the low pressure final stage L-0 and the rotor disk in a plurality of stages including the stage L-1 being joined by welding, wherein a material of both the rotor disk in the low pressure final stage L-0 and the rotor disk in a plurality of stages including the stage L-1 is a 12Cr steel and has a tensile strength of 900 to 1200 MPa.

The present invention relates to a relief valve (1) for a turbocharger, in which the crank arm (3) is made of a first material and the shaft (4) is made of a second material different from the first material used for manufacturing the crank arm (3), each of the materials containing a composition that provides the necessary properties according to the application of each component of the relief valve (1). The present invention also relates to a process for manufacturing the relief valve (1), which allows the crank arm (3) and the shaft (4) to be manufactured separately, using different materials for the manufacture of each component.

A nanocrystalline bainitic steel consisting of, by weight percentage: 0.3% to 0.6% carbon; 9.0% to 20.0% nickel; up to 10% cobalt; 1.0% to 4.5% aluminium; up to 0.5% molybdenum; up to 0.5% manganese; up to 0.5% tungsten; up to 3.0% chromium; and the balance being iron and impurities.

A labyrinth seal for sealing a sealing region between a rotor and stator of a rotary machine includes, a base, and a plurality of sealing rings. The sealing rings are formed on the base, project into the sealing region and form, between them labyrinth valleys bounded, laterally, by the sealing rings and, in the floor of the valleys, by the base. The sealing rings, in at least one region, include at least one material which is different from that of the base.

There is provided a turbocharger which can reduce whirl vibration. The turbocharger includes a shaft connecting a turbine and a compressor, a bearing housing having a bearing portion turnably supporting the shaft, and a sliding bearing interposed between the shaft and the bearing portion. The bearing portion is formed of an aluminum-based material, the shaft is formed of a steel material, and the sliding bearing is formed of a copper-based material.