A method for joining engine components includes positioning a first plurality of thermal protection structures across a thermal protection space between a first thermal protection surface and a second thermal protection surface. The first and second engine components are locally joined by forming a first plurality of transient liquid phase (TLP) or partial transient liquid phase (PTLP) bonds along corresponding ones of the first plurality of thermal protection structures between the first thermal protection surface and the second thermal protection surface. The second thermal protection surface is formed from a second surface material different from a first surface material of the first thermal protection surface.

A method for joining engine components includes positioning a first plurality of thermal protection structures across a thermal protection space between a first thermal protection surface and a second thermal protection surface. The first and second engine components are locally joined by forming a first plurality of transient liquid phase (TLP) or partial transient liquid phase (PTLP) bonds along corresponding ones of the first plurality of thermal protection structures between the first thermal protection surface and the second thermal protection surface. The second thermal protection surface is formed from a second surface material different from a first surface material of the first thermal protection surface.

An erosion and corrosion resistant protective coating for turbomachinery application includes at least one ceramic or metal-ceramic coating segment deposited on surface of a conductive metal substrate subjected to a pre-deposition treatment by at least blasting to provide the surface with texture. The erosion and corrosion resistant coating has a plurality of dome-like structures with dome width between in range from about 0.01 m to about 30 m. The at least one coating segment is formed by condensation of ion bombardment from a metal-gaseous plasma flow, wherein, at least during deposition of first micron of the coating segment, deposition rate of metal ions is at least 3 m/hr and kinetic energy of deposited metal ions exceeds 5 eV.

A compressor blade for a gas turbine is provided. The compressor blade has a blade substrate that consists of a metal alloy and has an aluminum diffusion zone on a surface of the blade substrate. In addition, the compressor blade has a hard material coating provided on the surface of the blade substrate. A compressor that has a compressor blade and a method of producing such a compressor blade is also provided.