Abstract: A node of a database system is operable to determine, at a first time, to prepare for a shutdown. The shutdown of the node is performed at a second time that is a period of time after the first time based on the node delaying the shutdown until a plurality of currently running processes being run by the node that initiated prior to the first time are determined to be complete. During the period of time after the first time and prior to performing the shutdown, a set of new processing requests are rejected by the node.

Abstract: Generating a recipe for controlling a polishing system includes receiving a target removal profile that includes a target thickness to remove for a plurality of locations on a substrate that are angularly distributed around the substrate, and storing a first function defining a polishing rate for a zone from a plurality of pressurizable zones of a carrier head that are angularly distributed around a the carrier head. The first function defines polishing rates as a function of pressures. For each particular zone of the plurality of zones a recipe defining a pressure for the particular zone over time is calculated by calculating an expected thickness profile after polishing using the first function, and minimizing a cost function that incorporates a first term representing a difference between the expected thickness profile and a target thickness profile.

Abstract: A method for chemical mechanical polishing includes receiving an angular removal profile for a carrier head and an angular thickness profile of a substrate. Prior to polishing the substrate, a desired angle of the carrier head relative to the substrate is selected for loading the substrate into the carrier head. Selecting the desired angle is performed based on a comparison of the angular removal profile for the carrier head and the angular thickness profile of the substrate to reduce angular non-uniformity in polishing. The carrier head is rotated to receive the substrate at the desired angle, the substrate is transferred to the carrier head and loaded in the carrier head with the carrier head at the desired angle relative to the substrate, and the substrate is polished.

Abstract: Provided is a combustor of a gas turbine including a combustion liner where combustion occurs, a transition piece connected to the combustion liner to allow combustion gases to pass through, and a honeycomb seal ring disposed between the combustion liner and the transition piece to prevent compressed air from leaking through a gap between the combustion liner and the transition piece. The honeycomb seal ring is inserted into the exit portion of the combustion liner to prevent compressed air from leaking when the combustion liner and the transition piece are coupled with each other.

Abstract: Provided is a stationary nozzle assembly of a gas turbine including a plurality of vane segments converting hot gas energy into a kinetic form, a fixed seal disposed between two adjacent vane segments, and honeycomb seal elements disposed between the two adjacent vane segments to prevent hot gases from escaping through a gap between the two adjacent vane segments. Here, the fixed seal and the honeycomb seal elements face each other. In addition, the vane segments each include airfoil shaped vanes, an outer wall and an inner wall that are disposed at opposite sides of the airfoil shaped vanes, and the fixed seal and the honeycomb seal elements are installed in at least one of the outer wall or the inner wall.

Abstract: Provided is a turbine blade of a gas turbine including a turbine blade part having an airfoil shape including an internal cavity therein, a cast tip disposed at an upper portion of the turbine blade part, and a braze joint to attach the turbine blade part and the cast tip to each other. The turbine blade part and the cast tip has substantially the same cross-sectional shape in a top plan view. In addition, the turbine blade part further includes a protrusion disposed at a surface where the turbine blade part is attached to the cast tip. In a similar manner, the cast tip may have a concave portion at a surface where the cast tip is attached to the turbine blade part to allow the concave portion to be coupled to the protrusion of the turbine blade part.

Abstract: Provided is a turbine blade of a gas turbine including a turbine blade part having an airfoil shape including an internal cavity therein, a cast tip disposed at an upper portion of the turbine blade part, and a braze joint to attach the turbine blade part and the cast tip to each other. The turbine blade part and the cast tip has substantially the same cross-sectional shape in a top plan view. In addition, the turbine blade part further includes a protrusion disposed at a surface where the turbine blade part is attached to the cast tip. In a similar manner, the cast tip may have a concave portion at a surface where the cast tip is attached to the turbine blade part to allow the concave portion to be coupled to the protrusion of the turbine blade part.

Abstract: Provided is a combustor of a gas turbine including a combustion liner where combustion occurs, a transition piece connected to the combustion liner to allow combustion gases to pass through, and a honeycomb seal ring disposed between the combustion liner and the transition piece to prevent compressed air from leaking through a gap between the combustion liner and the transition piece. The honeycomb seal ring is inserted into the exit portion of the combustion liner to prevent compressed air from leaking when the combustion liner and the transition piece are coupled with each other.

Abstract: Provided is a stationary nozzle assembly of a gas turbine including a plurality of vane segments converting hot gas energy into a kinetic form, a fixed seal disposed between two adjacent vane segments, and honeycomb seal elements disposed between the two adjacent vane segments to prevent hot gases from escaping through a gap between the two adjacent vane segments. Here, the fixed seal and the honeycomb seal elements face each other. In addition, the vane segments each include airfoil shaped vanes, an outer wall and an inner wall that are disposed at opposite sides of the airfoil shaped vanes, and the fixed seal and the honeycomb seal elements are installed in at least one of the outer wall or the inner wall.

Abstract: The restoring process machines out a crack in the platform of a turbine blade to form a pocket that then receives a plug of compatible material. The plug is brazed in place and the blade is the machined and cleaned to present a clean fresh surface where the plug is inserted. The plug has a lower coefficient of thermal expansion so that the plug area has less compressive stresses in the repaired area.

Abstract: Interior architectural structures and lighting for aircraft, particularly commercial passenger airplanes. Light diffusers and ceiling panels in a “wing-shape” and other secondary panels are utilized to create different interior designs and structures. A permeable secondary panel is utilized in one passenger cabin in order to provide a more private-type space. An enlarged ceiling arch with blended curves forming a “wing-type” configuration provides a more spacious cabin arrangement. Other features include air and light diffusers, passenger service modules, a “shelf”-like configuration and lighting above the airplane entrance/exit door, and bulkheads and monuments positioned at various positions in the cabin.