Abstract: A system and method for monitoring and diagnosis of engine health are provided. In one aspect, a system receives continuous operating data (COD) associated with an asset. The COD includes parameter values for one or more parameters over a collection time period. The system generates synthetic snapshot data based at least in part on the COD. The synthetic snapshot data includes one or more synthetic snapshots each containing the parameter values for the one or more parameters for a given timepoint within the collection time period. The system also receives snapshot data associated with the asset. The snapshot data includes one or more snapshots each containing parameter values for the one or more parameters for a given timepoint. The system generates an output indicating a health status of the asset or one or more components thereof based at least in part on the snapshot data and the synthetic snapshot data.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to generate a predictive asset health quantifier of a turbine engine. An example apparatus includes a performance model analyzer to determine a fleet behavior parameter by generating a reference performance model using historical information for a fleet of operators using turbine engines, generate a residual performance model based on calculating a difference between the fleet behavior parameter and a plurality of operator behavior parameters, identify an operator as a candidate improvement target based on comparing the operator behavior parameters corresponding to the operator to the fleet in the residual performance model, and determine an adjusted operator behavior parameter for the candidate improvement target.

Abstract: An apparatus and method for predicting distress on a physical component. The method can include obtaining distress data. The distress data can be used to determine a distress rank. The distress rank can be compared to a distress output provided by a kernel that use parameters related to the physical component. The comparison can result in a prediction model for the physical component.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to generate a predictive asset health quantifier of a turbine engine. An example apparatus includes a performance model analyzer to determine a fleet behavior parameter by generating a reference performance model using historical information for a fleet of operators using turbine engines, generate a residual performance model based on calculating a difference between the fleet behavior parameter and a plurality of operator behavior parameters, identify an operator as a candidate improvement target based on comparing the operator behavior parameters corresponding to the operator to the fleet in the residual performance model, and determine an adjusted operator behavior parameter for the candidate improvement target.

Abstract: An apparatus and method for predicting distress on a physical component. The method can include obtaining distress data. The distress data can be used to determine a distress rank. The distress rank can be compared to a distress output provided by a kernel that use parameters related to the physical component. The comparison can result in a prediction model for the physical component.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to generate a predictive asset health quantifier of a turbine engine. An example apparatus includes a performance model analyzer to determine a fleet behavior parameter by generating a reference performance model using historical information for a fleet of operators using turbine engines, generate a residual performance model based on calculating a difference between the fleet behavior parameter and a plurality of operator behavior parameters, identify an operator as a candidate improvement target based on comparing the operator behavior parameters corresponding to the operator to the fleet in the residual performance model, and determine an adjusted operator behavior parameter for the candidate improvement target.

Abstract: Systems for thermally regulating portions of a steam turbine are disclosed. In one embodiment, a thermal control system for a rotor bearing support includes: a housing fluidly connected to an inlet and adapted to substantially enclose the rotor bearing support, the housing defining a first annular cavity adapted to receive a fluid from the inlet; and an outlet fluidly connected to the housing, the outlet adapted to receive the fluid from the annular cavity.

Abstract: A turbomachine rotor includes: a rotor body having an outer surface; and a patterned abrasive or abradable coating formed over the outer surface of the rotor body, the patterned abrasive or abradable coating for directing a flow of a working fluid across the turbomachine rotor.

Abstract: Systems for thermally regulating portions of a steam turbine are disclosed. In one embodiment, a thermal control system for a rotor bearing support includes: a housing fluidly connected to an inlet and adapted to substantially enclose the rotor bearing support, the housing defining a first annular cavity adapted to receive a fluid from the inlet; and an outlet fluidly connected to the housing, the outlet adapted to receive the fluid from the annular cavity.

Abstract: A turbomachine rotor includes: a rotor body having an outer surface; and a patterned abrasive or abradable coating formed over the outer surface of the rotor body, the patterned abrasive or abradable coating for directing a flow of a working fluid across the turbomachine rotor.

Abstract: A pattern-abradable seal assembly is provided for a stationary steam turbine component. The seal assembly, in use, is oriented in opposition to at least one seal tooth on a rotatable turbine component so as to inhibit leakage flow across the seal assembly in one direction, the seal assembly may include an annular seal carrier having at least one axially-oriented surface; a pattern-abradable/abrasive seal coating or insert at least partially covering the at least one axially-oriented surface, the pattern-abradable/abrasive seal coating having a pattern formed thereon adapted to face and be at least partially penetrated by the at least one seal tooth. A plurality of anti-swirl elements project radially beyond the pattern and are arranged to provide at least an axial component of flow across the abradable seal assembly. The coating or insert may also be used on other stationary turbine component surfaces to direct flow in a predetermined direction.

Abstract: In an embodiment, a seal assembly for a rotating element is disclosed. The seal assembly includes: a plurality of arcuate packing rings configured to form an annulus proximately surrounding the rotating element; and a plurality of radially and circumferentially extending seal teeth coupled to each of the plurality of arcuate packing rings, wherein at least one of the plurality of seal teeth includes a plurality of axially extending protrusions.

Abstract: A rotor of a turbomachine includes a rotor drum located at a central axis and a plurality of buckets secured to the rotor drum. A first reaction stage includes axial entry dovetailed buckets. An axial passage for cooling flow is provided along a mating surface between the bucket dovetail and the dovetail slot in the rotor drum. Cool steam at taken between a first stage bucket and a second stage nozzle and passed through the axial passage to a low pressure sink at an upstream end of the rotor.

Abstract: A method to determine eccentricity of a rotor in a turbine including: collecting sensor data of rotor eccentricity for a plurality of startup operations; establishing a baseline eccentricity value using the sensor data corresponding to a selected startup operation; determining an eccentricity value using the filtered sensor data for each of a plurality of startup operations subsequent to the selected startup operation; determining a rotor eccentricity difference between the baseline eccentricity value and each of the eccentricity values for the plurality of startup operations subsequent to the selected startup operation, and reporting a rotor eccentricity condition based on the rotor eccentricity difference.

Abstract: A method to determine eccentricity of a rotor in a turbine including: collecting sensor data of rotor eccentricity for a plurality of startup operations; establishing a baseline eccentricity value using the sensor data corresponding to a selected startup operation; determining an eccentricity value using the filtered sensor data for each of a plurality of startup operations subsequent to the selected startup operation; determining a rotor eccentricity difference between the baseline eccentricity value and each of the eccentricity values for the plurality of startup operations subsequent to the selected startup operation, and reporting a rotor eccentricity condition based on the rotor eccentricity difference.