Abstract: One or more protuberances are provided on a turbine blade on its suction side in a vicinity of its trailing edge. The protuberances serve to reduce a separation zone in a vicinity of a blade surface that is responsible for disturbances that affect efficiency 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,Z? given in Table 1, in which the coordinate Z? 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 the 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,Z? given in Table 1, in which the coordinate Z? 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,Z? given in Table 1, in which the coordinate Z? 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,Z? given in Table 1, in which the coordinate Z? 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,Z? given in Table 1, in which the coordinate Z? 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,Z? given in Table 1, in which the coordinate Z? 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: The invention relates to a blade possessing a leading edge and a trailing edge, the blade comprising a first airfoil possessing an inner face and an outer face extending between said leading edge and said trailing edge, a second airfoil possessing an inner face and an outer face extending between said leading edge and said trailing edge, and at least one spacer strip interconnecting said inner face of the first airfoil and said inner face of the second airfoil, said at least one strip extending to said trailing edge, the distance between the inner face of the first airfoil and the inner face of the second airfoil being of the same order of magnitude as the maximum thickness of the first or the second airfoil.

Abstract: One or more protuberances are provided on a turbine blade on its suction side in a vicinity of its trailing edge. The protuberances serve to reduce a separation zone in a vicinity of a blade surface that is responsible for disturbances that affect efficiency of the turbine.

Abstract: The invention relates to a blade possessing a leading edge and a trailing edge, the blade comprising a first airfoil possessing an inner face and an outer face extending between said leading edge and said trailing edge, a second airfoil possessing an inner face and an outer face extending between said leading edge and said trailing edge, and at least one spacer strip interconnecting said inner face of the first airfoil and said inner face of the second airfoil, said at least one strip extending to said trailing edge, the distance between the inner face of the first airfoil and the inner face of the second airfoil being of the same order of magnitude as the maximum thickness of the first or the second airfoil.