Abstract: A drill string tool assembly, in some embodiments, comprises a punching tool that induces fissures to increase permeability in a localized region of a borehole wall. The assembly also comprises a sensor that detects spatial features of the fissures and processing logic, coupled to the sensor and punching tool, that adapts operation of the punching tool based on the spatial features. The assembly further comprises a fluid sampling probe, coupled to the processing logic, that samples fluid from the localized region.

Abstract: A drill string tool assembly, in some embodiments, comprises a punching tool that induces fissures to increase permeability in a localized region of a borehole wall. The assembly also comprises a sensor that detects spatial features of the fissures and processing logic, coupled to the sensor and punching tool, that adapts operation of the punching tool based on the spatial features. The assembly further comprises a fluid sampling probe, coupled to the processing logic, that samples fluid from the localized region.

Abstract: A condition monitoring system for a pressure vessel includes at least one vibration monitoring probe coupled to at least one pressure vessel component. The system also includes at least one computing device that includes a memory device configured to store data associated with the at least one vibration monitoring probe. The computing device also includes at least one input channel configured to receive the data associated with the at least one vibration monitoring probe. The computing device further includes a processor coupled to the memory device and the at least one input channel. The processor is programmed to determine a deterioration of the material condition of the at least one pressure vessel component by comparing at least a portion of the data associated with the at least one vibration monitoring probe with predetermined vibration parameters.

Abstract: A method for distributing effects of a circumferential hot streak condition in a turbine includes communicating a control signal to a rotator moving a stator ring with the rotator in response to the control signal.

Abstract: The trailing edge region of a nozzle airfoil is provided with a cooling configuration wherein post-impingement cooling air flows between radially spaced ribs defining convective cooling channels into a generally radially extending plenum. Cooling air in the plenum is split between film cooling holes for film cooling the pressure side of the trailing edge region and for flow about downstream pins for pin cooling the downstream regions of the opposite sides of the airfoil. The cooling air exiting the pins is directed through convective channels defined by a second set of radially spaced ribs and through exit apertures on the pressure side of the trailing edge.

Abstract: First stage nozzle airfoils have internal core profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X, Y and Z values are in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define internal core profile sections at each radial distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete internal core profile. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled-up or scaled-down internal core profile. The nominal internal core profile given by the X, Y and Z distances lies within an envelope of ±0.030 inches in directions normal to any internal core surface location.

Abstract: The trailing edge region of a nozzle airfoil is provided with a cooling configuration wherein post-impingement cooling air flows between radially spaced ribs defining convective cooling channels into a generally radially extending plenum. Cooling air in the plenum is split between film cooling holes for film cooling the pressure side of the trailing edge region and for flow about downstream pins for pin cooling the downstream regions of the opposite sides of the airfoil. The cooling air exiting the pins is directed through convective channels defined by a second set of radially spaced ribs and through exit apertures on the pressure side of the trailing edge.

Abstract: The first stage nozzles have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table 1. The X and Y values are in inches and the Z value is non-dimensional along the nozzle-stacking axis coincident with a turbine radius and convertible to a Z distance in inches from the turbine axis by multiplying the Z value by the height of the airfoil and adding the root radius to the result. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.160 inches.