Abstract: A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.

Abstract: An airfoil for a turbofan engine includes a first contoured sidewall, a second contoured sidewall, a leading edge, and a trailing edge with each extending in a spanwise direction defined between a root and a tip portion of the airfoil. The first contoured sidewall and the second contoured sidewall define an outer surface of the airfoil. The airfoil further includes a plurality of protrusions where each protrusion of the plurality of protrusions has a curvilinear shape and extends outwardly from the outer surface along at least one of the first contoured sidewall or the second contoured sidewall. The plurality of protrusions is defined downstream from a mid-point of a chord length of the airfoil and terminates upstream of the trailing edge.

Abstract: A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.

Abstract: An airfoil for a gas turbine engine includes an exterior skin layer having a pressure side surface, a suction side surface, a leading edge, and a trailing edge. The exterior skin layer defines an interior volume. The airfoil further includes a primary structure within the interior volume between the pressure and suction side surfaces. The primary structure includes one or more primary meta-structures. The airfoil further includes a secondary structure within the interior volume adjacent to the primary structure between the pressure and suction side surfaces. The secondary structure includes at least one isogrid structure. Further, one or more of the plurality of primary meta-structures of the primary structure is connected to at least a portion of the at least one isogrid structure of the secondary structure.

Abstract: Methods of manufacturing airfoil assemblies include forming an airfoil core comprising a foam to define an airfoil shape extending in a first direction and having a pressure side and a suction side extending in a second direction, the second direction being perpendicular to the first direction, between a leading edge and a trailing edge; and electroforming a metal alloy onto an exterior surface of the airfoil core to define an external airfoil shell.

Abstract: Nickel-cobalt materials, methods of forming a nickel-cobalt material, and methods of thermally stabilizing a nickel-cobalt material are provided. A nickel-cobalt material may include a metal matrix composite with amorphous regions and crystalline regions substantially encompassed by a nanocrystalline grain structure with a grain size distribution of about 50 nanometers to about 800 nanometers, and the nanocrystalline grain structure may include widespread intragranular twinning. The metal matrix composite may have a chemical makeup that includes nickel, cobalt, and a dopant such as phosphorus and/or boron. A nickel-cobalt material may be heat treated within a first temperature zone below the onset temperature for grain growth and then within a second temperature zone above the onset temperature for grain growth in the material. Chemical composition and heat treatment may yield a thermally stabilized nickel-cobalt material.

Abstract: Nickel-cobalt materials, methods of forming a nickel-cobalt material, and methods of thermally stabilizing a nickel-cobalt material are provided. A nickel-cobalt material may include a metal matrix composite with amorphous regions and crystalline regions substantially encompassed by a nanocrystalline grain structure with a grain size distribution of about 50 nanometers to about 800 nanometers, and the nanocrystalline grain structure may include widespread intragranular twinning. The metal matrix composite may have a chemical makeup that includes nickel, cobalt, and a dopant such as phosphorus and/or boron. A nickel-cobalt material may be heat treated within a first temperature zone below the onset temperature for grain growth and then within a second temperature zone above the onset temperature for grain growth in the material. Chemical composition and heat treatment may yield a thermally stabilized nickel-cobalt material.