Various implementations described herein are directed to a method of performing a land seismic survey operation. The method may include receiving a first information from a central recording system by a computer system on a seismic truck. The first information describes time and locations of seismic shots being performed in the seismic survey operation. The method may include using a set of rules and the first information to determine a start time for a seismic shot at a next shot location. The method may also include transmitting a second information that describes the next shot location and the start time to the central recording system.

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 slidable component including a wear-resistant coating includes a slidable component, and a wear-resistant coating provided on a slide surface of the slidable component. The wear-resistant coating includes metal particles deposited on the side surface of the slidable component, and containing Ni, Co and Cr, and a first oxide layer covering surfaces of the metal particles, containing an Al oxide as its main component, and containing a Y oxide.

Disclosed is an austenitic stainless steel alloy that includes, by weight, about 22% to about 28% chromium, about 3.5% to about 6.5% nickel, about 1% to about 6% manganese, about 0.5% to about 2.5% silicon, about 0.3% to about 0.6% carbon, about 0.2% to about 0.8% nitrogen, and a balance of iron. Molybdenum, niobium, and tungsten are excluded. The alloy is suitable for use in turbocharger turbine housing applications for temperature up to about 980 C.

A clearance control system for a gas turbine engine includes a full hoop blade outer air seal carrier ring, a full hoop thermal control ring at least partially contained within the full hoop blade outer air seal blade outer air seal carrier ring to form an interference fit therebetween, and a multiple of blade outer air seals mounted to the full hoop blade outer air seal carrier ring.

An object of the invention is to provide an alloy article that exhibits even better mechanical properties and/or even higher corrosion resistance than conventional high entropy articles without sacrificing the attractive properties thereof, a product formed of the alloy article, and a fluid machine having the product. An alloy article according to the invention has a predetermined chemical composition consisting of Co, Cr, Fe, Ni and Ti, Mo within a range of 1 atomic % or more and 5 atomic % or less, an element with a larger atomic radius than the atomic radiuses of Co, Cr, Fe and Ni within a range of more than 0 atomic % and 4 atomic % or less, and a balance of inevitable impurities.

A clearance control system for a gas turbine engine includes a full hoop blade outer air seal carrier ring, a full hoop thermal control ring at least partially contained within the full hoop blade outer air seal blade outer air seal carrier ring to form an interference fit therebetween, and a multiple of blade outer air seals mounted to the full hoop blade outer air seal carrier ring.

A coated article (22) comprises a substrate (100) and a coating system (102) atop the substrate. The coating system has a nickel-based first layer (104) and a chromium-based second layer (108) atop the first layer.

It is an objective of the invention to provide a steam turbine rotor of which a rotor shaft is made of a low-cost heat resistant ferritic steel and that can withstand high main steam temperatures of about 650 C. There is provided a steam turbine rotor comprising: a rotor shaft made of a heat resistant ferritic steel such as a 12-Cr steel; and a rotor blade made of a TiAl alloy, wherein the TiAl alloy includes: from 38 to 45 atomic % of Al; from 0.5 to 2 atomic % of V; from 2 to 6 atomic % of Cr and/or Mo; and the balance being Ti and incidental impurities.

Methods of forming a coating system on a surface of a cobalt-based superalloy component are provided. The method includes forming a nickel-based primer layer on the surface of the cobalt-based superalloy component; forming an intermediate nickel-containing layer on the nickel-based primer layer; and heat treating the cobalt-based superalloy component to form a diffusion coating on the surface of the cobalt-based superalloy component. The intermediate nickel-containing layer includes nickel, chromium, and aluminum. Coated cobalt-based superalloy components formed from such a method are also provided.