General Electric Company

Unison Industries, Inc.

Guru Venkata Dattu Jonnalagadda

Ravindra Shankar Ganiger

David Raju Yamarthi

Steven Douglas Johnson

Deepak Trivedi

Gordon Tajiri

Sandeep Kumar

Vidyashankar Ramasastry Buravalla

Narendra Anand Hardikar

Emily Marie Phelps

Joseph Richard Schmitt

Prateek Jalan

Vamshi Krishna Reddy Kommareddy

Lakshmi Krishnan

Shalini Thimmegowda

Grant Robert Portune

Amit Goyal

Srinivasan Swaminathan

Nuthi Srinivas

Chandrashekhar Kandukuri

Himanshu Gupta

Ashley Rose Dvorak

Gary Stephen Shipley

Shalabh Saxena

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.

Seal support assembly for a turbine engine

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.

Airfoil for a gas turbine engine having an inner core structure formed of meta-structures and isogrids

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.

Thermally stabilized nickel-cobalt materials and methods of thermally stabilizing the same

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Ponnur, India

Guru Venkata Dattu Jonnalagadda