Abstract: A method is disclosed for cooling a gas turbine having a turbine, wherein a rotor, which rotates about a machine axis, carries a plurality of rotating blades, which are mounted by blade roots and extend with their airfoils into a hot gas path of the gas turbine. The rotor is concentrically surrounded by a turbine vane carrier carrying a plurality of stationary vanes, whereby the rotating blades and the stationary vanes are arranged in alternating rows in axial direction. An extended lifetime with external cooling is achieved by providing first and second cooling systems for the turbine.

Abstract: A method is disclosed for cooling a gas turbine having a turbine, wherein a rotor, which rotates about a machine axis, carries a plurality of rotating blades, which are mounted by blade roots and extend with their airfoils into a hot gas path of the gas turbine. The rotor is concentrically surrounded by a turbine vane carrier carrying a plurality of stationary vanes, whereby the rotating blades and the stationary vanes are arranged in alternating rows in axial direction. An extended lifetime with external cooling is achieved by providing first and second cooling systems for the turbine.

Abstract: Disclosed is an engine, the engine having a compressor, an expansion machine, and a shaft, the shaft having a direction of rotation. The engine includes a compressed fluid main flow path, a flow divider arranged at and fluidly connected to the compressed fluid main flow path, and a duct fluidly connecting the flow divider and components of the expansion machine. The duct is arranged such that, when the engine is operated, a fluid is guided through the duct from the flow divider towards the expansion machine components. A flow deflector device is arranged within a flow path and configured to deflect and thereby accelerate a flow therethrough directed form the flow divider towards the expansion machine components in a tangential direction, wherein the deflection can be effected into the shaft direction of rotation.

Abstract: A motor-compressor includes a compressor, an electric motor directly connected to the compressor, magnetic bearings and one gas support located adjacent to a magnetic bearing to seal and support an end of the compressor's rotor. The compressor and the electric motor are integrated in a single unit, being housed in a single box or casing.

Abstract: Motor-compressor comprising a compressor, an electric motor directly connected to said compressor, wherein the compressor and the electric motor are integrated in a single unit, housed in a single box or casing.

Abstract: A cylindrical blade for a rotor of the purely radial type of a centrifugal compressor with a medium-high flow coefficient comprises a first surface (3) of the pressure side and a second surface (5) of the suction side of equal curvature with generatrices parallel to the axis (Z) of rotation of the rotor, the lines of curvature of the said surfaces (3, 5) being defined, in a system of Cartesian coordinates (X, Y, Z) by the ratio between the coordinates of a discrete set of points (10) belonging to them and the outer radius (R) of the rotor (20).

Abstract: A cylindrical blade for a rotor of the purely radial type of a centrifugal compressor with a medium flow coefficient comprises a first surface (3) of the pressure side and a second surface (5) of the suction side of equal curvature, both having generatrices parallel to the axis (Z) of rotation of the rotor, in which the line (7) of curvature of the said surfaces (3, 5) is defined, in a Cartesian reference system, by the ratio between the coordinates of a discrete set of points (9) belonging to the line and the outer radius (R) of the rotor (10).

Abstract: Stator blading (10) of return channels for two-dimensional centrifugal stages of a multi-stage centrifugal compressor with improved efficiency, of the type comprising a plurality of blades (20) disposed circumferentially equally spaced on a ring (12) which surrounds a rotor of the compressor, these blades (20) each having a cross-section in the shape of a half-moon formed by a concave area (21) and a convex area (22), these concave (21) and convex (22) areas being connected to one another such as to determine a trailing edge (24) and a leading edge (23) on an inner radius (R); the profile of the concave area (21) of each blade (20) is produced by connecting to one another points which have particular Cartesian co-ordinates relative to a system of axes which are at right-angles to one another, of x-co-ordinates (X) and y-co-ordinates (Y) with an origin (O) located on the axis of rotation.

Abstract: A cylindrical blade for a rotor of the purely radial type of a centrifugal compressor with a medium-high flow coefficient comprises a first surface (3) of the pressure side and a second surface (5) of the suction side of equal curvature with generatrices parallel to the axis (Z) of rotation of the rotor, the lines of curvature of the said surfaces (3, 5) being defined, in a system of Cartesian coordinates (X, Y, Z) by the ratio between the coordinates of a discrete set of points (10) belonging to them and the outer radius (R) of the rotor (20).

Abstract: A cylindrical blade for a rotor of the purely radial type of a centrifugal compressor with a medium flow coefficient comprises a first surface (3) of the pressure side and a second surface (5) of the suction side of equal curvature, both having generatrices parallel to the axis (Z) of rotation of the rotor, in which the line (7) of curvature of the said surfaces (3, 5) is defined, in a Cartesian reference system, by the ratio between the coordinates of a discrete set of points (9) belonging to the line and the outer radius (R) of the rotor (10).

Abstract: Stator blading (10) of return channels for two-dimensional centrifugal stages of a multi-stage centrifugal compressor with improved efficiency, of the type comprising a plurality of blades (20) disposed circumferentially equally spaced on a ring (12) which surrounds a rotor of the compressor, these blades (20) each having a cross-section in the shape of a half-moon formed by a concave area (21) and a convex area (22), these concave (21) and convex (22) areas being connected to one another such as to determine a trailing edge (24) and a leading edge (23) on an inner radius (R); the profile of the concave area (21) of each blade (20) is produced by connecting to one another points which have particular Cartesian co-ordinates relative to a system of axes which are at right-angles to one another, of x-co-ordinates (X) and y-co-ordinates (Y) with an origin (O) located on the axis of rotation.