Abstract: Methods and systems for associating, in a secure manner, a link between web sites (or other network resources) and installed applications. In one embodiment, a signed list of one or more URLs is downloaded and validated to establish an association, which is stored in a data structure, between a first application and a second application. In response to receiving a selection of a URL in the second application, comparing the selected URL to URLs in the data structure and displaying, in the first application, content of the selected URL in response to determining that at least a prefix portion of the selected URL matches one of the URLs associated with the first application in the data structure.

Abstract: A system and method for displaying a wellbore. A well profile is generated in a computing system. The wellbore is associated with the well profile. Information associated with the wellbore is received including at least components. The wellbore is displayed in three dimensions for review by one or more users.

Abstract: A turbine rotor blade with a blade root, the blade root has, with respect to a direction of flow of a work medium circulating around the turbine rotor blade, a front end face and a rear end face. At least one of the front end face and the rear end face has at least one recess located at a distance to an edge of the respective end face.

Abstract: Methods and systems for associating, in a secure manner, a link between web sites (or other network resources) and installed applications. In one embodiment, a signed list of one or more URLs is downloaded and validated to establish an association, which is stored in a data structure, between a first application and a second application. In response to receiving a selection of a URL in the second application, comparing the selected URL to URLs in the data structure and displaying, in the first application, content of the selected URL in response to determining that at least a prefix portion of the selected URL matches one of the URLs associated with the first application in the data structure.

Abstract: A system and method for displaying a wellbore. A well profile is generated in a computing system. The wellbore is associated with the well profile. Information associated with the wellbore is received including at least components. The wellbore is displayed in three dimensions for review by one or more users.

Abstract: A method of monitoring or assessing the motion of the limbs of a body when performing repetitive cyclic activity uses inertial measurement units secured to each of the limbs to be monitored. The operation of all of the IMUs is synchronized by way of a pulse from a computer. On performing the repetitive cyclic activity such as walking, running, trotting or galloping, the outputs of the IMUs are assembled and analyzed in realtime, to determine the relative phase of the limb movements, from which an assessment of the gait may be made.

Abstract: A turbine blade assembly in a turbine engine. The turbine blade assembly includes a turbine blade and a first snubber structure. The turbine blade includes an internal cooling passage containing cooling air. The first snubber structure extends outwardly from a sidewall of the turbine blade and includes a hollow interior portion that receives cooling air from the internal cooling passage of the turbine blade.

Abstract: A method of monitoring or assessing the motion of the limbs of a body when performing repetitive cyclic activity uses inertial measurement units secured to each of the limbs to be monitored. The operation of all of the IMUs is synchronised by way of a pulse from a computer. On performing the repetitive cyclic activity such as walking, running, trotting or galloping, the outputs of the IMUs are assembled and analysed in realtime, to determine the relative phase of the limb movements, from which an assessment of the gait may be made.

Abstract: A cooling system for a turbine airfoil of a turbine engine having a trailing edge cooling slot positioned within the generally elongated, hollow airfoil and extending from the trailing edge chordwise into the generally elongated, hollow airfoil toward the leading edge such that a secondary trailing edge is offset upstream from the trailing edge. As such, the trailing edge cooling slot reduces stress formation at the trailing edge of the turbine airfoil.

Abstract: A turbine blade assembly in a turbine engine. The turbine blade assembly includes a turbine blade and a first snubber structure. The turbine blade includes an internal cooling passage containing cooling air. The first snubber structure extends outwardly from a sidewall of the turbine blade and includes a hollow interior portion that receives cooling air from the internal cooling passage of the turbine blade.

Abstract: A cooling system for a turbine airfoil of a turbine engine having a trailing edge cooling slot positioned within the generally elongated, hollow airfoil and extending from the trailing edge chordwise into the generally elongated, hollow airfoil toward the leading edge such that a secondary trailing edge is offset upstream from the trailing edge. As such, the trailing edge cooling slot reduces stress formation at the trailing edge of the turbine airfoil.

Abstract: In a guide vane element for a gas turbine with a vane blade extending between a platform that is located radially inward in relation to the main housing of the gas turbine and a radially outward platform, a flange is provided on at least one edge of the platforms adjoining an adjacent second guide vane element in the circumferential direction and on the side of the platform facing away from the vane blade. The second guide vane element can be attached, via a second flange provided on a second platform on the second guide vane element. The connection of the platforms forms a cover band, or a connection between the guide vane elements that is tight, flush, and stress-free at different temperatures.

Abstract: In a guide vane element for a gas turbine with a vane blade extending between a platform that is located radially inward in relation to the main housing of the gas turbine and a radially outward platform, a flange is provided on at least one edge of the platforms adjoining an adjacent second guide vane element in the circumferential direction and on the side of the platform facing away from the vane blade. The second guide vane element can be attached, via a second flange provided on a second platform on the second guide vane element. The connection of the platforms forms a cover band, or a connection between the guide vane elements that is tight, flush, and stress-free at different temperatures.

Abstract: In a guide vane element for a gas turbine with a vane blade extending between a platform that is located radially inward in relation to the main housing of the gas turbine and a radially outward platform, a flange is provided on at least one edge of the platforms adjoining an adjacent second guide vane element in the circumferential direction and on the side of the platform facing away from the vane blade. The second guide vane element can be attached, via a second flange provided on a second platform on the second guide vane element. The connection of the platforms forms a cover band, or a connection between the guide vane elements that is tight, flush, and stress-free at different temperatures.