The turbocharger according to the invention has a rotor with a compressor wheel as well as a turbine wheel that is connected in a rotationally-fixed manner to the compressor wheel by means of a common shaft. The compressor wheel and the shaft are form-fittingly tensioned with one another, wherein respectively at least one or two torque-transmitting contact surfaces, which lie one atop the other, between components force-fittingly tensioned with one another, is provided with a friction-increasing coating.

A method for coating a surface of a substrate is provided. The method includes providing a suspension or a precursor comprising feedstock material suspended in a liquid medium. Further, the method includes spraying the suspension or the precursor onto the surface at a spray angle less than about 75 degrees to a tangent of the surface.

In one aspect, the present disclosure is directed to a gas turbine sealing assembly that includes a first static gas turbine wall and a second static gas turbine wall. A seal is disposed between the first static gas turbine wall and the second static gas turbine wall. The seal includes a shield wall constructed from a first material that includes a first shield wall portion and a second shield wall portion. A spring constructed from a second material includes a first spring portion and a second spring portion. The first shield wall portion is adjacent to the first spring portion, and the second shield wall portion is adjacent to the second spring portion.

A flow-conditioning system includes a pump, process tubing coupling the pump to a source of multiple component process fluid, and an in-line flow-mixing device positioned in the process tubing upstream of the pump. A system includes a well disposed below a body of water and providing a source of multiple component fluid, a pump disposed in and exposed to the water, process tubing coupling the pump to the well, and an in-line flow-mixing device positioned in the process tubing upstream of the pump.

A ring-shaped thermomechanical part for a turbine engine, comprising at least one coating including a polymeric matrix and fillers in non-deflagrating carbon exclusively comprising the chemical element C. A turbine engine comprising such a part.

A method applies one or more films of polynuclear aluminum oxide hydroxide and polynuclear chromium hydroxide to a metal substrate. A method thermally treats the metal substrate with the one or more films at a temperature of at least 250 C., the thermal treatment reducing the polynuclear aluminum oxide hydroxides and the polynuclear chromium hydroxides to at least one layer of aluminum-chromium oxide.

A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, a damper block disposed between the inner shroud and the outer shroud, a first biasing apparatus, and a second biasing apparatus. The first biasing apparatus provides a first biasing force to the inner shroud, biasing the inner shroud a first deflection distance in a direction toward the hot gas path and away from the outer shroud. The second biasing apparatus provides a second biasing force to the damper block, biasing the damper block a second deflection distance in a direction toward the hot gas path and away from the outer shroud. The second deflection distance is greater than the first deflection distance.

The invention relates to a method for repairing a thermal barrier of a component comprising a substrate coated with such a thermal barrier, said substrate being made of a high-performance alloy, said thermal barrier being adhered to the alloy and having lower thermal conductivity than the alloy, the thermal barrier including at least one ceramic, one region of the thermal barrier being a region to be repaired, wherein said method includes the following steps: a) defining the region to be repaired, using a mask which protects the other regions of the thermal barrier; b) injecting a carrier gas loaded with droplets of ceramic precursor into a plasma discharge inside a plasma chamber of a plasma reactor containing the component to be repaired, while making the concentration of ceramic precursor in the carrier gas dependent on at least one parameter of the reactor selected from among: the pressure of the plasma chamber, the power of the plasma generator and the diameter of the precursor droplets, in order to control the stateliquid, gel or solidof the ceramic precursor having an effect on the region to be repaired; c) injecting a gas not loaded with ceramic precursor into a plasma discharge within the plasma chamber, steps b) and c) being repeated.

A coating comprising a first surface and a second surface is provided. The coating includes a plurality of growth domains. An orientation of at least one growth domain of the plurality of growth domains is non-vertical with respect to the first surface of the coating. One or more growth domains of the plurality of growth domains comprise a plurality of at least partially melted and solidified particles.

A fan containment case includes a barrel that includes a case structure and a nanocrystalline metal coating overlying the case structure. The case structure includes a plurality of carbon fiber bands, in which at least an outermost carbon fiber band and an innermost carbon fiber band include a fire resistant polymer matrix. The case structure also includes at least one cut resistant polymer band between the outermost and the innermost carbon fiber bands.