Abstract: An electronic gaming machine may include an illuminable notification mechanism, which may be disposed on a rear surface of the electronic gaming machine in a position or location that makes the notification mechanism visible to a casino operator. The notification mechanism may include a display, such as, for example, a display that includes at least one tri-color light emitting diode (LED). The display of the notification mechanism may be selectively illuminated in a variety of lighting configurations based, for example, upon gameplay activity of a player of the gaming machine. For instance, in some embodiments, the notification mechanism may be selectively illuminated in any of an inactive lighting configuration, an active lighting configuration, or a privileged lighting configuration. In the privileged lighting configuration, the notification mechanism may indicate that a player of the gaming machine is entitled to a complimentary item (e.g., a free or reduced-price item or service).

Abstract: A method facilitates assembling a rotor assembly for gas turbine engine. The method comprises providing a first rotor blade that includes an airfoil having a leading edge and a trailing edge including a plurality of trailing edge openings, a platform, a shank, and a dovetail, wherein the platform extends between the airfoil and the dovetail and includes a radially outer surface, a radially inner surface, and a recessed area extending at least partially between the radially outer and inner surfaces. The method also comprises coupling the first rotor blade to a rotor shaft using the dovetail, and coupling a second rotor blade to the rotor shaft such that cooling air is substantially continuously channeled through the platform recessed area during engine operation to facilitate reducing stresses induced to at least a portion of the airfoil trailing edge.

Abstract: The second stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X, Y and Z values are in inches. Z represents a distance in inches from and perpendicular to a plane passing through the engine centerline. X and Y are distances in inches which, when connected by smooth continuous arcs, define airfoil profile sections at each distance Z. The profile sections at the Z distances are joined smoothly with one another to form the complete airfoil shape. The X and Y distances and optionally the Z distance may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of ±0.016 inches.

Abstract: The second stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X, Y and Z values are in inches. Z represents a distance in inches from and perpendicular to a plane passing through the engine centerline. X and Y are distances in inches which, when connected by smooth continuous arcs, define airfoil profile sections at each distance Z. The profile sections at the Z distances are joined smoothly with one another to form the complete airfoil shape. The X and Y distances and optionally the Z distance may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of ±0.016 inches.

Abstract: The shroud includes a seal extending continuously between leading and trailing edges of the shroud at the tip of the airfoil. A cutter tooth is provided substantially medially of the shroud and in substantial radial alignment with a line through the center of mass of the airfoil. In this manner, any moment arm generated by movement of the shroud is eliminated or minimized to reduce the stresses in the fillet region between the shroud and the airfoil tip and hence increase the creep life of the bucket.

Abstract: The shroud includes a seal extending continuously between leading and trailing edges of the shroud at the tip of the airfoil. A cutter tooth is provided substantially medially of the shroud and in substantial radial alignment with a line through the center of mass of the airfoil. In this manner, any moment arm generated by movement of the shroud is eliminated or minimized to reduce the stresses in the fillet region between the shroud and the airfoil tip and hence increase the creep life of the bucket.