A turbomachine includes a shroud and a rotor, which includes first and second blades. A first blade tip and a second blade tip respectively include a base and a first layer. The second blade tip also includes an abrasive second layer layered over the respective first layer. The first layer has a lower material hardness than the shroud. The second layer has a lower thermal stability than the shroud and the first layer. The rotor performs a grind operation and, subsequently, a post-grind operation. The second layer, in the grind operation, contacts and removes material from the shroud, and wears away, thereby revealing the first layer of the second blade tip for the post-grind operation. The first layer of the first blade tip is spaced apart with at least some radial clearance from the shroud in the grind and post-grind operations.

The present disclosure relates generally to blades used in gas turbine engines. More specifically designs in accordance with the present disclosure include turbine blades comprising ceramic matrix composite materials with abrasive tips coupled thereto.

In one aspect, a calcium-magnesium alumino-silicate (CMAS)-resistant coating includes an outer coating having a plurality of columnar structures formed during material deposition due to preferential material accumulation and a plurality of generally vertically-oriented gaps separating adjacent columnar structures. The columnar structures include a plurality of randomly-oriented particle splats and a CMAS-reactive material and have a total porosity of less than five percent. The plurality of generally vertically-oriented gaps extend from an outermost surface of the outer coating to a first depth of the outer coating equal to or less than a total thickness of the outer coating. The vertically-oriented gaps have a median gap width of less than five micrometers.

A rotor assembly for a gas turbine engine includes a rotor defining an outer periphery; and a plurality of blades attached to the outer periphery. The plurality of blades includes a material property different than the other of the plurality of blades to provide mistuning of the rotor.

Methods for creating a cast component, along with the resulting cast components, are provided. The method may include heating a mold having a cavity therein; supplying a first molten metal material into the cavity of the mold such that the first molten metal material is directed to a first portion of the cavity of the mold; supplying a second molten metal material into the cavity of the mold such that the second molten metal material is directed to a second portion of the cavity of the mold, wherein the first molten metal material is compositionally different than the second molten metal material; and thereafter, allowing the first molten metal material and the second molten metal material to form the cast component.

A gas turbine engine includes a rotor that has a rim, blades extending radially outwards from the rim, a hub extending radially inwards from the rim, an arm extending axially from the rim, the arm having a radially outer surface, and a coating disposed on the radially outer surface. The coating is zirconia-toughened alumina in which the alumina is a matrix with grains of the zirconia dispersed there through. The grains of zirconia are predominantly a tetragonal crystal structure.

The present invention relates to a method for producing a component of a turbomachine from a metal alloy as well as a correspondingly produced component, wherein the method includes defining at least one first component region that will have a first property profile, and at least one second component region that will have a second property profile which is different from the first property profile; providing at least one powder of the metal alloy or several different powders of constituents of the metal alloy; additive manufacture of the component from the at least one powder, wherein the powder is melted for cohesive joining of the powder particles to each other and to a substrate or to an already produced part of the component.

A method for welding a first powder metallurgical (PM) part to a second powder metallurgical (PM) part includes: working a first face of the first PM part; working a first face of the second PM part; and friction welding the first face of the first part to the first face of the second part.

Disclosed herein is an article comprising a substrate; an abrasive coating disposed on the substrate; where the abrasive coating comprises a matrix having abrasive grit particles dispersed therein; and a layer of material disposed on the abrasive coating; where the layer of material is a titanium nitride (TiN), boron nitride (BN), titanium-aluminum-nitrides [(TiAl)N], titanium-aluminum-silicon-nitrides [(TiAlSi)N], chromium nitrides (CrN), aluminum oxide (Al.sub.2O.sub.3), titanium oxide (TiO.sub.2), silicon carbo-nitride (SiCN), titanium carbo-nitride (TiCN), or a combination thereof.

A method of manufacturing a component includes additively manufacturing a crucible; directionally solidifying a metal material within the crucible; and removing the crucible to reveal the component. A component for a gas turbine engine includes a directionally solidified metal material component, the directionally solidified metal material component having been additively manufactured of a metal material concurrently with a core, the metal material having been remelted and directionally solidified.