A method of fabricating an abradable coating of varying density, and an abradable coating of varying density. The method comprises the following steps: providing a substrate having a first portion and a second portion; depositing a first precursor material on the first portion of the substrate compressing the first precursor material between the substrate and a first bearing surface; sintering the first precursor material as compressed in this way in order to obtain a first abradable coating portion on the first portion of the substrate, and possessing a first density; depositing a second precursor material on the second portion of the substrate; and compressing the second precursor material between the substrate and a second bearing surface.

An integrally bladed rotor in which a hub and a web are formed from a fine grain microstructure using an investment casting process or from metal powder with a HIP process, and a plurality of rotor blades formed from a coarse grain microstructure using a metal additive manufacturing process, where the hub and the web and the rotor blades are formed as a single piece and from the same material.

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.

A method for implementing an abradable coating comprising: a pattern-forming step in which, using a slurry containing ceramic particles and solvent, a slurry pattern is formed on the surface of a thermal barrier coating layer; and a firing step in which the slurry pattern formed on the surface of the thermal barrier coating layer is fired to form an abradable coating layer. A ceramic material included in the thermal barrier coating layer and ceramic particles included in the abradable coating layer are of the same type.

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.

A blade has an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The blade has a compositional variation along the airfoil.

A gas turbine engine assembly comprising a rotor, a gas path component, and a carrier. The rotor includes a shaft adapted to rotate about an axis and a gas-path component that extends from the shaft for rotation therewith about the axis. The carrier extends around the gas-path component to block gasses from passing over the gas-path component during rotation of the rotor.

Provided are a nickel-base alloy having high high-temperature strength, a turbine blade using same, and a method for producing an injection molded article of the nickel-base alloy. The nickel-base alloy contains: at least one metal element from among chrome, molybdenum, and niobium; nickel; aluminum; and carbon. The nickel-base alloy comprises a plurality of crystal grains and a plurality of precipitates. The areas between the individual crystal grains in the nickel-base alloy, i.e., the boundaries of the individual crystal grains serve as crystal grain boundaries. The crystal grains are crystals in which nickel is the primary component. The precipitates are precipitated on the crystal grain boundaries. The precipitates are carbides comprising: at least one metal element from among chrome, molybdenum, and niobium; and carbon. The carbides have a diameter of 0.1-10 m and an aspect ratio of 3 or more.

An inner band used on a turbine engine is disclosed herein. The inner band may include a core comprising polymeric materials and a shell comprising nanocrystalline metallic materials applied to the core to cover at least a portion of the core.

An erosion resistant material has a continuous portion and discontinuous portions. The continuous portion has a continuous structure. The discontinuous portions are arranged inside the continuous portion to have a discontinuous structure. The discontinuous portions are formed of particles having an average particle diameter of 1 m or less. Further, the discontinuous portions are formed of a material having a surface hardness and a Young's modulus higher than those of the continuous portion.