Abstract: Containerized software discover and identification can include discovering a plurality of container remnants by electronically scanning portions of computer memory of at least one computer system of one or more of computing nodes, the portions of computer memory being allocated to persistent storage of computer data, and each container remnant containing computer data providing a record of system-generated execution attributes generated in response to execution of one or more containerized applications. One or more inactive container remnants unutilized by a currently running containerized application can be identified among the plurality of container remnants. Each inactive container remnant can be categorized, the categorizing being based on system-generated execution attributes contained in each inactive container remnant.

Abstract: Containerized software discover and identification can include discovering a plurality of container remnants by electronically scanning portions of computer memory of at least one computer system of one or more of computing nodes, the portions of computer memory being allocated to persistent storage of computer data, and each container remnant containing computer data providing a record of system-generated execution attributes generated in response to execution of one or more containerized applications. One or more inactive container remnants unutilized by a currently running containerized application can be identified among the plurality of container remnants. Each inactive container remnant can be categorized, the categorizing being based on system-generated execution attributes contained in each inactive container remnant.

Abstract: A turbomachine diaphragm including a sealing section having a first end portion that extends to a second end portion through an intermediate portion; and at least one rail member including a first end section that extends from the first end portion of the sealing section to a second end section through an intermediate section having an inner surface section and an outer surface section, the second end section including multiple weld passes disposed on opposed sides of the second end section for mitigation of thermal tensions on the diaphragm, the multiple weld passes forming a cladding welded to the diaphragm, wherein the cladding includes a stainless austenitic steel.

Abstract: An inner band assembly for at turbine nozzle of a rotary machine that includes a centerline axis, the inner band assembly comprising a platform portion, a first flange portion coupled to the platform portion and obliquely oriented with respect to the centerline axis, and a second flange coupled to the first flange and obliquely oriented with respect to the first flange. Wherein the platform portion and the first flange intersect.

Abstract: A turbomachine diaphragm including a sealing section having a first end portion that extends to a second end portion through an intermediate portion; and at least one rail member including a first end section that extends from the first end portion of the sealing section to a second end section through an intermediate section having an inner surface section and an outer surface section, the second end section including multiple weld passes disposed on opposed sides of the second end section for mitigation of thermal tensions on the diaphragm, the multiple weld passes forming a cladding welded to the diaphragm, wherein the cladding includes a stainless austenitic steel.

Abstract: A method of refurbishing worn diaphragm rails for turbo machines. This method comprises machining the worn part of the diaphragm rails such that a clean and geometrically exact machined surface is achieved. Welding one or more layers on these machined surfaces builds up a cladding that overtops the nominal dimensions of new diaphragm. The method further comprises machining the cladding such that it has the nominal dimensions of a new diaphragm.

Abstract: An inner band assembly for at turbine nozzle of a rotary machine that includes a centerline axis, the inner band assembly comprising a platform portion, a first flange portion coupled to the platform portion and obliquely oriented with respect to the centerline axis, and a second flange coupled to the first flange and obliquely oriented with respect to the first flange. Wherein the platform portion and the first flange intersect.

Abstract: A masking fixture includes a flexible cover and a rigid cover. The flexible cover is received within a cavity of the rigid cover. An air connector provides for a purge flow supply to be connected to the masking fixture via a port in fluid communication with an enclosure of the flexible cover. A method of treating a workpiece includes directing a pressurized fluid jet comprising an abrasive media entrained therein against an exterior surface of the workpiece and directing a purge flow through the workpiece while directing the pressurized fluid jet against the exterior surface.

Abstract: A turbine nozzle for a rotary machine including a centerline axis includes an airfoil including a leading edge and a trailing edge. The airfoil defines a throat location proximate the trailing edge. The turbine nozzle also includes an inner band assembly including a platform portion coupled to the airfoil, and a first flange coupled to the platform portion. The first flange is obliquely oriented with respect to the platform portion, and the platform portion and the first flange intersect at a point axially aligned with the throat location.

Abstract: A system includes a stand having a first axis, a first arm, and a second arm. The first arm and the second arm extend from the axis. The first arm is configured to rotate about the axis and the second arm is configured to rotate about the axis. The system includes a first can coupled to the first arm. The first can is configured to be disposed around a first tip of a first airfoil, the first can is configured to receive a first gas flow, and the first can is configured to distribute the first gas flow to a first work cavity around the first tip of the first airfoil. The system further includes a second can coupled to the second arm. The second can is configured to be disposed around a second tip of a second airfoil, the second can is configured to receive a second gas flow, and the second can is configured to distribute the second gas flow to a second work cavity of the second airfoil.

Abstract: A method of refurbishing worn diaphragm rails for turbo machines. This method comprises machining the worn part of the diaphragm rails such that a clean and geometrically exact machined surface is achieved. Welding one or more layers on these machined surfaces builds up a cladding that overtops the nominal dimensions of new diaphragm. The method further comprises machining the cladding such that it has the nominal dimensions of a new diaphragm.

Abstract: A system includes a stand having a first axis, a first arm, and a second arm. The first arm and the second arm extend from the axis. The first arm is configured to rotate about the axis and the second arm is configured to rotate about the axis. The system includes a first can coupled to the first arm. The first can is configured to be disposed around a first tip of a first airfoil, the first can is configured to receive a first gas flow, and the first can is configured to distribute the first gas flow to a first work cavity around the first tip of the first airfoil. The system further includes a second can coupled to the second arm. The second can is configured to be disposed around a second tip of a second airfoil, the second can is configured to receive a second gas flow, and the second can is configured to distribute the second gas flow to a second work cavity of the second airfoil.

Abstract: A turbine nozzle for a rotary machine including a centerline axis includes an airfoil including a leading edge and a trailing edge. The airfoil defines a throat location proximate the trailing edge. The turbine nozzle also includes an inner band assembly including a platform portion coupled to the airfoil, and a first flange coupled to the platform portion. The first flange is obliquely oriented with respect to the platform portion, and the platform portion and the first flange intersect at a point axially aligned with the throat location.

Abstract: Various aspects include a composite turbomachine component and related methods. In some cases, a method includes: identifying a location of potential or actual structural weakness in a body of a turbomachine component, the body including a first material having a first thermal expansion coefficient; forming a slot in the location of the body, the slot extending at least partially through a wall of the turbomachine component; and bonding an insert to the body at the slot to form a composite component, the insert including a second material having a second thermal expansion coefficient differing from the first thermal expansion coefficient by up to approximately ten percent, the second material consisting of a nickel-chromium-molybdenum alloy, wherein after the bonding the insert is configured to reduce the potential or actual structural weakness in the body.

Abstract: A masking fixture includes a flexible cover and a rigid cover. The flexible cover is received within a cavity of the rigid cover. An air connector provides for a purge flow supply to be connected to the masking fixture via a port in fluid communication with an enclosure of the flexible cover. A method of treating a workpiece includes directing a pressurized fluid jet comprising an abrasive media entrained therein against an exterior surface of the workpiece and directing a purge flow through the workpiece while directing the pressurized fluid jet against the exterior surface.

Abstract: A method and system for use in facilitating relative movement between first and second components is provided. A first component engagement assembly is inserted into an opening in the first component. The first component engagement assembly is threadably coupled adjacent to a thrust member such that the thrust member extends through the first component opening. An end of the thrust member extends toward the second component. The first component engagement assembly couples in frictional engagement with an inner surface of the first component opening. When torque is exerted on the thrust member, the thrust member moves relative to the first component engagement assembly to exert, via the end of the thrust member, one of a thrust force and a traction force against the second component to move the second component relative to the first component.