Abstract: According to some embodiments, an industrial asset item definition data store may contain at least one electronic record defining the industrial asset item. An automated support structure creation platform may include a support structure optimization computer processor. The automated support structure optimization computer processor may, for example, be adapted to automatically create support structure geometry data associated with an additive printing process for the industrial asset item. The creation may be performed, according to some embodiments, via an iterative loop between a build process simulation engine and a topology optimization engine.

Abstract: A component has a first structural configuration and a second structural configuration. The component includes a sensor assembly including a plurality of interconnected structural members defining a plurality of load paths. A first structural member and a second structural member define a first load path when the component is in the first structural configuration. The first structural member and a third structural member define a second load path when the component is in the second structural configuration. The second load path is configured to bypass the second structural member. The sensor assembly is configured to detect a characteristic of the component that changes when the component switches between the first structural configuration and the second structural configuration.

Abstract: The turbomachine includes a rotatable member defining an axis of rotation and an inner annular casing extending circumferentially over at least a portion of the rotatable member. The inner annular casing includes a radially outer surface. The turbomachine further includes an outer annular casing extending over at least a portion of the inner annular casing. The inner annular casing and the outer annular casing define a plurality of cavities therebetween. The clearance control system includes a manifold system including a plurality of conduits extending circumferentially about the inner annular casing and disposed within the cavities. The clearance control system also includes an impingement system extending circumferentially about the inner annular casing and disposed within the cavities. The conduits are configured to channel a flow of cooling fluid to the impingement system which is configured to channel the cooling fluid to the radially outer surface of the inner annular casing.

Abstract: A planet gear includes a pin and an annular planet gear rim. The pin has a pin radius. The pin includes a pin outer surface. The annular planet gear rim has an inner radius and an outer radius. The annular planet gear rim includes an inner surface and an outer surface. The inner surface and the pin outer surface define a clearance therebetween. The clearance is greater than 0 when a radial force is applied to the planet gear.

Abstract: Coating systems for components of a gas turbine engine, such as a compressor casing, are provided. The coating system can include a ceramic material disposed along the compressor casing on a surface to be adjacent to a rotating compressor blade. The coating system is harder than the compressor blade and can reduce the rub ratio between the casing and blade. The coating system can thereby increase the lifetime of the compressor casing and blades. Methods are also provided for applying the coating system onto a compressor casing.

Abstract: Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include an abradable material disposed along the compressor blade tip and may be used with a bare compressor casing. The abradable coating is softer than the compressor casing and can reduce the overall rub ratio thereby increasing the lifetime of the compressor blade and casing. Methods are also provided for applying the coating system onto a compressor blade.

Abstract: Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include a ceramic material disposed along the compressor blade tip and may be used with a bare compressor casing. The ceramic coating is harder than the bare compressor casing and can reduce the rub ratio thereby increasing the lifetime of the compressor blades. Methods are also provided for applying the coating system onto a compressor blade.

Abstract: An airfoil for use in a turbomachine includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and a trailing edge, the leading edge and the trailing edge define a chord distance. The airfoil includes a tip portion extending between the pressure sidewall and the suction sidewall. The tip portion includes a planar section and a recessed section. The recessed section extends adjacent to the planar section such that a thickness of the planar section is less than a thickness of the airfoil. The recessed section is offset a predetermined distance from the leading edge and the trailing edge along the chord distance.

Abstract: An airfoil for use in a turbomachine includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and an opposite trailing edge. The leading edge and the trailing edge define a chord distance. The airfoil further includes a root portion, and a tip portion. The tip portion extends between the pressure sidewall and the suction sidewall such that the tip portion is substantially perpendicular to each sidewall. The tip portion includes at least one planar section and at least one oblique section that forms a recess within the tip portion. The at least one oblique section extends from the at least one planar section towards the root portion along the chord distance. The tip portion is configured to reduce airfoil wear during contact with a surrounding casing.

Abstract: The turbomachine includes a rotatable member defining an axis of rotation and an inner annular casing extending circumferentially over at least a portion of the rotatable member. The inner annular casing includes a radially outer surface. The turbomachine further includes an outer annular casing extending over at least a portion of the inner annular casing. The inner annular casing and the outer annular casing define a plurality of cavities therebetween. The clearance control system includes a manifold system including a plurality of conduits extending circumferentially about the inner annular casing and disposed within the cavities. The clearance control system also includes an impingement system extending circumferentially about the inner annular casing and disposed within the cavities. The conduits are configured to channel a flow of cooling fluid to the impingement system which is configured to channel the cooling fluid to the radially outer surface of the inner annular casing.

Abstract: The present disclosure is directed to a shroud assembly for a gas turbine. The shroud assembly includes a casing and a shroud. The shroud includes a radially outer wall engaged with the casing. A radially inner wall integrally couples to the radially outer wall. The radially inner wall and the radially outer wall collectively define a pair of axially opposed cavities. The radially inner wall moves radially outward toward the casing when one or more gas turbine blades contact the radially inner wall.

Abstract: A method implemented using at least one processor includes receiving a plurality of measured operational parameters of a turbo machine having a rotor and a stator. The plurality of measured operational parameters includes a plurality of real-time operational parameters and a plurality of stored operational parameters. The method further includes generating a finite element model of the turbo machine and generating a plurality of snapshots based on the finite element model and the plurality of stored operational parameters. The method further includes generating a reduced order model based on the plurality of snapshots. The method also includes determining an estimated clearance between the rotor and the stator during operation of the turbo machine, based on the reduced order model and the plurality of real-time operational parameters.

Abstract: A journal bearing for use in an epicyclical gearbox including a non-circular shaped journal pin and a journal bearing body into which the non-circular shaped journal pin is disposed. The non-circular shaped journal pin configured to mimic the shape of the non-cylindrical shaped journal bearing body at least at a high pressure point exerted upon the non-cylindrical shaped journal bearing body during a high pressure event, thereby permitting a free flow of a lubricating fluid there between the non-circular shaped journal pin and the journal bearing body during the high pressure event. An epicyclical gearbox including the journal bearing and method of facilitating a hydrodynamic oil flow in the planet gear journal bearing.

Abstract: A journal bearing for use in an epicyclical gearbox including a non-circular shaped journal pin and a journal bearing body into which the non-circular shaped journal pin is disposed. The non-circular shaped journal pin configured to mimic the shape of the non-cylindrical shaped journal bearing body at least at a high pressure point exerted upon the non-cylindrical shaped journal bearing body during a high pressure event, thereby permitting a free flow of a lubricating fluid there between the non-circular shaped journal pin and the journal bearing body during the high pressure event. An epicyclical gearbox including the journal bearing and method of facilitating a hydrodynamic oil flow in the planet gear journal bearing.