Abstract: This disclosure is directed to seal assemblies for a turbomachine. The seal assemblies include stationary and rotating components and at least one interface between the stationary and rotating components. The seal assembly further includes a self-lubricating lattice element made of carbon or a carbon-based material. The self-lubricating lattice element may have a porous and compressible microstructure capable of retaining a liquid substance. During engine operation, the self-lubricating lattice element can compress and expel some portion of the liquid substance to form a liquid-containing layer between the rotating and stationary components of the seal assembly. Also described herein are self-lubricating wear sleeves for use in other portions of the turbomachine.

Abstract: Method of repairing a Ni-based alloy component are provided, along with the resulting repaired coated component. The method may include: spraying a plurality of particles onto a surface of the Ni-based alloy component to form a coating thereon. The plurality of particles comprises a mixture of Ni-based superalloy particles and Co-based superalloy particles. The particles are sprayed at a spray temperature that is less than a melting point of both the Ni-based superalloy particles and the Co-based superalloy particles. A repaired coated component may include: a Ni-based alloy component having a surface and a coating on the surface of the Ni-based alloy component. The coating comprises a plurality of deformed particles therein, with the plurality of deformed particles comprises 5% by weight to 80% by weight of a Ni-based superalloy and 20% by weight to 95% by weight of a Co-based superalloy.

Abstract: Methods of protecting a surface of a Ni-based alloy component are provided, along with the wear strip utilized and the repaired Ni-based alloy component. The method may include: spraying a plurality of particles to form a wear strip. The plurality of particles includes a mixture of Ni-based superalloy particles and Co-based superalloy particles. The plurality of particles is sprayed at a spray temperature that is less than a melting point of the Ni-based superalloy particles and less than a melting point of the Co-based superalloy particles. The wear strip may be attached onto a surface of the Ni-based alloy component, either during the spraying of the particles (when wear strip formed on the surface of the Ni-based alloy component) or after a standalone wear strip is formed.

Abstract: There is provided markers, systems, and methods for creating and utilizing a marker containing identification information. The embodiments include an identifying marker comprised of high temperature material for tracking a component in a high temperature environment. The marker may be disposed on the component such that the marker is subject to high temperatures while affixed to the component. The marker may provide the ability to track a history of the component the marker is attached to for maintenance.

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: There is provided markers, systems, and methods for creating and utilizing a marker containing identification information. The embodiments include an identifying marker comprised of high temperature material for tracking a component in a high temperature environment. The marker may be disposed on the component such that the marker is subject to high temperatures while affixed to the component. The marker may provide the ability to track a history of the component the marker is attached to for maintenance.

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: This disclosure is directed to seal assemblies for a turbomachine. The seal assemblies include stationary and rotating components and at least one interface between the stationary and rotating components. The seal assembly further includes a self-lubricating lattice element made of carbon or a carbon-based material. The self-lubricating lattice element may have a porous and compressible microstructure capable of retaining a liquid substance. During engine operation, the self-lubricating lattice element can compress and expel some portion of the liquid substance to form a liquid-containing layer between the rotating and stationary components of the seal assembly. Also described herein are self-lubricating wear sleeves for use in other portions of the turbomachine.

Abstract: A high entropy alloy-based composition is provided that has the formula: (M1aM2bM3cM4dM5eM6f)CrAlY1-x-zZrxMoz where: each of M1, M2, M3, M4, M5, and M6 is a different alloying element selected from the group consisting of Ni, Co, Fe, Si, Mn, and Cu such that none of M1, M2, M3, M4, M5, and M6 are the same alloying element; 0.05?a?0.35; 0.05?b?0.35; 0.05?c?0.35; 0.05?d?0.35; 0.05?e?0.35; 0?f?0.35; a+b+c+d+e+f=1; 0?x?1; 0?z?1; and 0?x+z?1.

Abstract: A corrosion resistant coating including a matrix, corrosion resistant particles dispersed throughout the matrix, and a glass-forming additive is disclosed. The glass-forming additive and one or more materials in the matrix form a glassy-phase when cured. Coated gas turbine engine components and methods for coating components are also disclosed.

Abstract: Systems and methods for measuring the clearance gaps between rotating and stationary components of a turbomachine are provided. In one exemplary aspect, flexible and degradable sensing arrays that include a plurality of microwave sensors are utilized to sense the clearance gaps between rotating and stationary components of the turbomachine. Microwaves generated by a microwave generator are transmitted to the sensors. Upon rotation of the rotating components, the rotating components reflect the microwaves transmitted thereto. The microwave sensors capture the transmitted signal and also capture a reflected signal indicative of the transmitted signal reflected by the rotating components. The signals are then forwarded to a computing device for processing. The amplitude difference at the interference fringes between the superimposed signals is representative of the clearance gaps between the rotating and stationary components.

Abstract: The present disclosure discloses a method of manufacturing a structure with a wall, comprising manufacturing a structure with a wall by using additive manufacturing technology, and dissolving a surface of the wall for reducing thickness of the wall.

Abstract: An electrical machine and method of forming includes electroforming a first set of metal laminates having a first predetermined geometry. The method also includes arranging an insulating layer between each in the first set of metal laminates in a stack to define a layered component having the first predetermined geometry.

Abstract: Systems and methods for measuring the clearance gaps between rotating and stationary components of a turbomachine are provided. In one exemplary aspect, flexible and degradable sensing arrays that include a plurality of microwave sensors are utilized to sense the clearance gaps between rotating and stationary components of the turbomachine. Microwaves generated by a microwave generator are transmitted to the sensors. Upon rotation of the rotating components, the rotating components reflect the microwaves transmitted thereto. The microwave sensors capture the transmitted signal and also capture a reflected signal indicative of the transmitted signal reflected by the rotating components. The signals are then forwarded to a computing device for processing. The amplitude difference at the interference fringes between the superimposed signals is representative of the clearance gaps between the rotating and stationary components.

Abstract: The present disclosure discloses a method of manufacturing a structure with a wall, comprising manufacturing a structure with a wall by using additive manufacturing technology, and dissolving a surface of the wall for reducing thickness of the wall.