Abstract: A method for determining a potential cause of pre-identified conditions occurring in components of a plurality of rotary machines is provided. The method includes associating each rotary machine with a respective machine data set and identifying, in a component database, a first set of the components each having a first pre-identified condition. The method also includes identifying at least one common parameter from the machine data sets of the rotary machines associated with the first set of components, and identifying, in the component database, a second set of the components for which the machine data set of the associated rotary machine includes the at least one common parameter. The method further includes reporting the at least one common parameter as the potential cause of the first pre-identified condition, and as the potential cause of at least a second of the pre-identified conditions associated with the second set of components.

Abstract: An imaging and analysis system for a component of a rotary machine includes an image capture device operable to capture image data from at least one selected type of electromagnetic radiation that is at least one of reflected from and transmitted through the component. The system also includes an image processor configured to generate processed data from the captured image data. The system further includes a control system configured to automatically identify a condition of the component by comparing the processed data to stored reference data. The reference data is stored in a format that enables direct comparison to the processed data.

Abstract: A method, system and program product for contemporaneous data recording and/or reliability modeling with a turbomachine service outage is provided. A database including impairment data for the turbomachine is provided. An impairment mode is recorded in the database for at least one of a part or an event from a plurality of predetermined impairment modes contemporaneously with a service outage of the turbomachine. The method also includes modeling a reliability of at least one of the part and the event based on the database contemporaneously with the service outage. Embodiments may also include using the reliability modeling to control operation of the turbomachine after the service outage.

Abstract: An imaging and analysis system for a component of a rotary machine includes an image capture device operable to capture image data from at least one selected type of electromagnetic radiation that is at least one of reflected from and transmitted through the component. The system also includes an image processor configured to generate processed data from the captured image data. The system further includes a control system configured to automatically identify a condition of the component by comparing the processed data to stored reference data. The reference data is stored in a format that enables direct comparison to the processed data.

Abstract: A method for determining a potential cause of pre-identified conditions occurring in components of a plurality of rotary machines is provided. The method includes associating each rotary machine with a respective machine data set and identifying, in a component database, a first set of the components each having a first pre-identified condition. The method also includes identifying at least one common parameter from the machine data sets of the rotary machines associated with the first set of components, and identifying, in the component database, a second set of the components for which the machine data set of the associated rotary machine includes the at least one common parameter. The method further includes reporting the at least one common parameter as the potential cause of the first pre-identified condition, and as the potential cause of at least a second of the pre-identified conditions associated with the second set of components.

Abstract: A configuration of cooling channels through the interior of a turbine rotor blade, the turbine rotor blade including a platform at an interface between an airfoil and a root. In one embodiment, the configuration of cooling channels includes: an interior cooling passage that is configured to extend from a connection with a coolant source in the root to the interior of the airfoil; a platform cooling channel that traverses at least a portion of the platform; a turndown extension that includes a first section, which comprises a connection with the platform cooling channel, and a second section, which comprises a radially oriented cooling channel; and a connector that extends from a connector opening formed through an outer face of the root to a connection with the interior cooling passage and, therebetween, bisects the second section of the turndown extension.

Abstract: A cooling circuit for a turbine bucket having a shank, a platform and an airfoil. The cooling circuit includes a first cooling passage extending from an inlet located at a radially inward end of the shank and adapted to communicate with a turbine wheel-space, the first cooling passage, in use, supplying cooling air to a serpentine cooling circuit extending within and across at least one region of the platform. The serpentine cooling circuit connects with a separate internal cooling circuit in the airfoil, such that the cooling air used to cool the platform is re-used in the airfoil cooling circuit.

Abstract: A configuration of cooling channels through the interior of a turbine rotor blade, the turbine rotor blade including a platform at an interface between an airfoil and a root. In one embodiment, the configuration of cooling channels includes: an interior cooling passage that is configured to extend from a connection with a coolant source in the root to the interior of the airfoil; a platform cooling channel that traverses at least a portion of the platform; a turndown extension that includes a first section, which comprises a connection with the platform cooling channel, and a second section, which comprises a radially oriented cooling channel; and a connector that extends from a connector opening formed through an outer face of the root to a connection with the interior cooling passage and, therebetween, bisects the second section of the turndown extension.

Abstract: A cooling circuit for a turbine bucket having a shank, a platform and an airfoil. The cooling circuit includes a first cooling passage extending from an inlet located at a radially inward end of the shank and adapted to communicate with a turbine wheel-space, the first cooling passage, in use, supplying cooling air to a serpentine cooling circuit extending within and across at least one region of the platform. The serpentine cooling circuit connects with a separate internal cooling circuit in the airfoil, such that the cooling air used to cool the platform is re-used in the airfoil cooling circuit.