Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, an aerodynamic profile defining an arm of a structural casing of a turbine having a central hub and a shroud is substantially identical to a nominal profile determined by Cartesian coordinates X,Y,Zadim given in Table 1, in which the coordinate Zadim is a quotient D/H where D is a distance of a point under consideration from a first reference plane P0 situated at a base of the nominal profile, and H is a height of said nominal profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to an axial direction of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: A computer-implemented method executed by one or more computer servers includes receiving a notification from a first communication device. The notification indicates an armed intruder within a first stationary geofence. The method further includes determining whether one or more of a first plurality of communication devices are within a second stationary geofence different than the first stationary geofence, and in response to the notification, providing an emergency alert to the communication device(s) determined to be within the second stationary geofence. Other example computer-implemented methods, communication devices including software applications, and systems for notifying one or more LEOs of an armed intruder by a premises personnel associated with a premises are also disclosed.

Abstract: The disclosure relates to a driver assistance system for a motor vehicle. The driver assistance system includes a wrong-way driving detection device that detects underway or imminent wrong-way driving of the motor vehicle. The driver assistance system also includes an output device that outputs a signal to a driver of the motor vehicle indicative of a wrong-way driving detection. The driver assistance system, via the output device, is configured to modify an operating state of the infotainment device according to the wrong-way driving detection.

Abstract: A computer-implemented method executed by one or more computer servers includes receiving a notification from a first communication device. The notification indicates an armed intruder within a first stationary geofence. The method further includes determining whether one or more of a first plurality of communication devices are within a second stationary geofence different than the first stationary geofence, and in response to the notification, providing an emergency alert to the communication device(s) determined to be within the second stationary geofence. Other example computer-implemented methods, communication devices including software applications, and systems for notifying one or more LEOs of an armed intruder by a premises personnel associated with a premises are also disclosed.

Abstract: An aviation turbine blade extending in the radial direction and presenting a pressure side and a suction side, including a plurality of pressure side cavities extending radially at the pressure side of the blade, a plurality of suction side cavities extending radially at the suction side of the blade, and at least one central cavity located in the central portion of the blade and surrounded by pressure side cavities and by suction side cavities, the blade further including a plurality of cooling circuits, in which at least a first cooling circuit comprises: a first cavity and a second cavity, the first and second cavities communicating with each other at a radially inner end and at a radially outer end of the blade.

Abstract: A microfabricated optical probe includes: a cantilever; an optical waveguide disposed at a periphery of the cantilever and including an optical loop, the optical loop being disposed coplanar with the cantilever; a mechanical support interposed between and interconnecting the cantilever and the optical waveguide with the mechanical support such that the cantilever and optical waveguide move together; and a substrate on which the cantilever is disposed and from which the cantilever and the optical loop protrude, wherein the cantilever and the optical waveguide flex independently of the substrate.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X, Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: A microfabricated optical probe includes: a cantilever; an optical waveguide disposed at a periphery of the cantilever and including an optical loop, the optical loop being disposed coplanar with the cantilever; a mechanical support interposed between and interconnecting the cantilever and the optical waveguide with the mechanical support such that the cantilever and optical waveguide move together; and a substrate on which the cantilever is disposed and from which the cantilever and the optical loop protrude, wherein the cantilever and the optical waveguide flex independently of the substrate.

Abstract: The disclosure relates to a driver assistance system for a motor vehicle. The driver assistance system includes a wrong-way driving detection device that detects underway or imminent wrong-way driving of the motor vehicle. The driver assistance system also includes an output device that outputs a signal to a driver of the motor vehicle indicative of a wrong-way driving detection. The driver assistance system, via the output device, is configured to modify an operating state of the infotainment device according to the wrong-way driving detection.