Abstract: A system and methods for synchronizing datasets are provided that are especially suitable and efficient for a user who has three or more datasets that need to be occasionally synchronized, with no one dataset or synchronization system being guaranteed to participate in every synchronization. Synchronization status information, such as correspondences between data records of particular multiple datasets, is stored with more than one of the datasets. When two datasets that contain synchronization status information synchronize with each other, they not only synchronize user data and exchange status information involving each other, but they also synchronize and exchange status information involving “third-party” datasets that may not be participating in the synchronization.

Abstract: A computer-implemented method for verifying geometries of airfoils includes the steps of providing a part having an airfoil having an intended positional geometry and an intended feature geometry; measuring a first set of points of a primary datum system; determining an actual positional geometry of the airfoil based on the primary datum system measurements; calculating a first deviation between the intended positional geometry and the actual positional geometry of the airfoil; measuring a plurality of sets of points of at least one secondary datum system; determining an actual feature geometry of the airfoil based on the at least one secondary datum system measurement; calculating a second deviation between the intended feature geometry and the actual feature geometry of the airfoil; and performing a verification of the intended positional geometry and the intended feature geometry of the airfoil based upon the first deviation and the second deviation.

Abstract: A sacrificial core is used for forming an interior space of a part and includes a ceramic core element and a first core element including a refractory metal element. The ceramic core element may be molded over the first core element or molded with assembly features permitting assembly with the first core element.

Abstract: A turbine blade for use in a gas turbine engine is provided. The turbine blade includes an airfoil portion having a tip end, a shroud attached to the tip end, which shroud has an outer surface, and a knife edge attached to an outer surface of the shroud. The knife edge has a pair of cutter blades disposed substantially over an axis of the airfoil portion.

Abstract: A blade is provided for use in a gas turbine engine. The blade has a platform, an airfoil portion extending radially from a first side of the platform, and an attachment portion extending from a second or underside side of the platform. The attachment portion includes a buttress which abuts the second side of the platform. The blade is provided with additional material on the second side of the platform for redistributing load away from the buttress.

Abstract: A turbine blade is provided for use in a gas turbine engine. The turbine blade has a platform, an airfoil radially extending from the platform, and an attachment portion comprising an asymmetric root neck portion having a higher stress side and a lower stress side. The turbine blade may further have additional material and a compound fillet for dispersing strain in a region where the airfoil overhangs the neck portion.

Abstract: An improved Internet delivery system for digitized photographs is described. The system embodies methodologies that speed the delivery of digitized images from photographic film scan centers to consumers across the Internet with high reliability. By delivering all the digital images to a more powerful centralized server infrastructure prior to the consumer's earliest opportunity to view them on-line, these images or pictures can be downloaded to a viewer of interest (e.g., user or family member) quickly enough to provide an appropriate Web response. Optimizations are also described that streamline the throughput with load balancing and provide virtually guaranteed uniform service with fail-over. In this manner, the system provides improved access, storage, and on-line availability of digital images.

Abstract: An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes an embedded microcircuit that traverses a tip between a suction sidewall and a pressure sidewall of the airfoil. The microcircuit includes at least on inlet disposed proximate to the tip and one of the sidewalls for receiving cooling air from an internal cooling cavity of the airfoil and at least outlet disposed proximate to the tip through which the cooling air ejects into a region outside the airfoil.

Abstract: A turbine blade having improved cooling has an airfoil with a root end and a tip end and at least one cooling passageway in the airfoil. Each cooling passageway extends from the root end to the tip end and has a circular cross-section. A plurality of turbulation promotion devices are arranged in each cooling passageway. Each of the turbulation promotion devices is arcuate in shape and circumscribes an arc less than 180 degrees.

Abstract: A turbine blade for use in a gas turbine engine is provided. The turbine blade includes an airfoil portion having a tip end, a shroud attached to the tip end, which shroud has an outer surface, and a knife edge attached to an outer surface of the shroud. The knife edge has a pair of cutter blades protruding outwardly from the knife edge.

Abstract: A turbine blade having improved cooling characteristics is provided. The turbine blade has an airfoil portion having a span, and at least one cooling passageway in the airfoil portion extending from a root portion of the airfoil portion to a tip portion of the airfoil portion. A plurality of turbulation promotion devices are placed in the at least one cooling passageway. The turbulation promotion devices have a P/e ratio which varies along the span of the airfoil portion, where P is the pitch between adjacent turbulation promotion devices and e is the height of the turbulation promotion devices.

Abstract: A rotor blade having a wing and beam construction for a tip shroud is disclosed. Various construction details are developed for providing a transition zone that extends from the suction side and pressure side of the airfoil to provide a flow path surface of the shroud. In one detailed embodiment, the transition zone is contoured under the beam differently than a portion under the rear portions of the wings.

Abstract: A rotor blade having a wing and beam construction for a tip shroud is disclosed. Various construction details are developed for providing the shroud with depression in the shroud and a transition zone that extends from the suction side and pressure side of the airfoil to provide a flow path surface of the shroud. In one detailed embodiment, the tip shroud has a depression generally outwardly of the airfoil and generally following the curve of the pressure and suction sides of the airfoil from the leading edge region to the trailing edge region.

Abstract: A rotor blade having a wing and beam construction for a tip shroud is disclosed. Various construction details are developed for providing a transition zone that extends from the suction side and pressure side of the airfoil to provide a flow path surface of the shroud. In one detailed embodiment, the transition zone over substantially all of its extent between the leading edge region and the trailing edge region is contoured to extend to the sides of the wings to provide a spanwise taper that extends to the side of the wing.

Abstract: A synchronization system providing multi-client synchronization is described. By storing the data that is actually being synchronized (i.e., storing the actual physical body of a memo, for instance) inside an extra database, “Grand Unification Database” (GUD), (or by specially-designated client data set) under control of a central or core synchronization engine, rather than transferring such data on a point-to-point basis, the system of the present invention provides a repository of information that is available at all times and does not require that any other synchronization client (e.g., PIM client or hand-held device) be connected. The GUD provides a super-set of the other client data sets. Therefore, if the user now includes an additional client, such as a server computer storing user information, the synchronization system has all the information necessary for synchronizing the new client, regardless of whether any of the other clients are currently available.

Abstract: A sacrificial core for forming an interior space of a part includes a ceramic core element and a first core element including a refractory metal element. The ceramic core element may be molded over the first core element or molded with assembly features permitting assembly with the first core element.

Abstract: The present invention relates to a system for delivering cooling air to a seal arrangement in a turbine stage of a gas turbine engine. The system comprises at least one vane having a passageway extending from an outer platform of the at least one vane to an inner platform of the at least one vane. A tube insert is positioned within the passageway. The tube insert has an inlet at one end for receiving cooling air from a source of cooling air and an outlet at a second end. A cover assembly is attached to the second end of the tube for receiving cooling air from the tube and delivering the cooling air to the seal arrangement. In a preferred embodiment, the cooling air is pre-swirled in the direction of rotation of a rotor stage of the turbine stage.

Abstract: The present invention relates to a system for delivering cooling air to a seal arrangement in a turbine stage of a gas turbine engine. The system comprises at least one vane having a passageway extending from an outer platform of the at least one vane to an inner platform of the at least one vane. A tube insert is positioned within the passageway. The tube insert has an inlet at one end for receiving cooling air from a source of cooling air and an outlet at a second end. A cover assembly is attached to the second end of the tube for receiving cooling air from the tube and delivering the cooling air to the seal arrangement. In a preferred embodiment, the cooling air is pre-swirled in the direction of rotation of a rotor stage-of the turbine stage.

Abstract: A system and methods for synchronizing information in datasets via a communication medium are provided that are suitable for synchronizing even across communication mediums that are susceptible to high latency, non-FIFO (non-First-In-First-Out) delivery order, or other adverse characteristics. According to an aspect of the invention, in an information processing system, a method for synchronizing a first dataset with at least a second dataset via a communication medium includes a step of storing information that is indicative of a first version of user data of the first dataset, wherein the first version has been involved in prior use for synchronizing with the second dataset.

Abstract: A system and methods for synchronizing information in datasets via a communication medium are provided that are suitable for synchronizing even across communication mediums that are susceptible to high latency, non-FIFO (non-First-In-First-Out) delivery order, or other adverse characteristics. According to an aspect of the invention, a computer-implemented method is for synchronizing user data in a first dataset with user data in at least a second dataset via a communication medium. The user data in the first dataset and the user data in the second dataset are capable of having been independently modified prior to the synchronization.