Abstract: A method for similitude testing of a turbomachine, the method comprising selecting a test gas having a molecular weight between 40 g/gmol and 150 g/gmol, a global warming potential (GWP) of less than 700, and a gas specific heat ratio of between 1 and 1.5; operating the turbomachine using the selected test gas; identifying at least one parameter while operating the turbomachine; establishing at least one test parameter associated with the at least one parameter; and comparing the at least one test parameter with a corresponding at least one specified parameter to determine whether the turbomachine has passed the similitude test.

Abstract: A method for similitude testing of a turbomachine, the method comprising selecting a test gas having a molecular weight between 40 g/gmol and 150 g/gmol, a global warming potential (GWP) of less than 700, and a gas specific heat ratio of between 1 and 1.5; operating the turbomachine using the selected test gas; identifying at least one parameter while operating the turbomachine; establishing at least one test parameter associated with the at least one parameter; and comparing the at least one test parameter with a corresponding at least one specified parameter to determine whether the turbomachine has passed the similitude test.

Abstract: Disk of a disk rotor for a gas turbine comprising a central portion (22), an intermediate portion (24), an outer portion (28), a series of axial pass-through holes (27) for a series of tie rods and a series of slots (50) for housing a corresponding series of vanes, the central portion (22) comprises a central axial pass-through hole (23), a first collar (30) situated at a first end and a second collar (40) situated at a second end of the central portion (22). The series of holes (27) is positioned in the outer portion (28) of the disk so as to obtain high dynamic characteristics of the rotor and at the same time a sufficient useful life thereof.

Abstract: Disk of a disk rotor for a gas turbine comprising a central portion (22), an intermediate portion (24), an outer portion (28), a series of axial pass-through holes (27) for a series of tie rods and a series of slots (50) for housing a corresponding series of vanes, the central portion (22) comprises a central axial pass-through hole (23), a first collar (30) situated at a first end and a second collar (40) situated at a second end of the central portion (22). The series of holes (27) is positioned in the outer portion (28) of the disk so as to obtain high dynamic characteristics of the rotor and at the same time a sufficient useful life thereof.

Abstract: System for connecting and locking blades which are fixed circumferentially to a rotor disc (1) of an axial compressor, comprising a plurality of blades (10, 10?) positioned in an array along the circumference of rotor disc (1), each blade (10, 10?) being provided with a shaped root (13) for connection to the rotor disc (1), and a dowel for positioning and locking the blades (10, 10?) in a predetermined position in a circumferential seat (3) which has a shaped profile and which is formed along the circumference of the rotor disc (1). At least one insertion slot (4) intersects the circumferential seat (3) to permit the insertion of the roots (13) of the blades (10, 10?) and the dowel.

Abstract: System for connecting and locking blades which are fixed circumferentially to a rotor disc (1) of an axial compressor, comprising a plurality of blades (10, 10′) positioned in an array along the circumference of a rotor disc (1), each blade (10, 10′) being provided with a shaped root (13) for connection to the rotor disc (1), and means of positioning and locking the blades (10, 10′) which can lock them in a predetermined position in a circumferential seat (3) which has a shaped profile and which is formed along the circumference of the rotor disc (1). At least one insertion slot (4) intersects the said circumferential seat (3) to permit the insertion of the roots (13) of the blades (10, 10′) and the positioning and locking means.

Abstract: A flange (20) for connection between an axial compressor and high-pressure rotor disc unit (14) in a gas turbine (10), wherein the flange (20) has a body (22) with a frusto-conical shape which is joined to a shaft (12) of the axial compressor by means of a hub (24) which has a cylindrical shape and which, at the larger base of the frustum of the cone of the body (22) is connected to the rotor disc unit (14) by means of an extension (26) of the hub in the form of a circular ring, a circumferential recess (28) provided in a surface (29) of the extension (26) which faces the rotor disc unit (14) being connected by interference with a projection, which is complementary to the recess and is provided on the rotor disc unit (14); the body (22) has an outer generatrix which is inclined relative to the direction at right-angles to the axis (X) by an angle &agr;1 of between 25° and 35° and an inner generatrix which is inclined by an angle &agr;2 of between 12° and 18°.

Abstract: A flange (20) for connection between an axial compressor and high-pressure rotor disc unit (14) in a gas turbine (10), wherein the flange (20) has a body (22) with a frusto-conical shape which is joined to a shaft (12) of the axial compressor by means of a hub (24) which has a cylindrical shape and which, at the larger base of the frustum of the cone of the body (22) is connected to the rotor disc unit (14) by means of an extension (26) of the hub in the form of a circular ring, a circumferential recess (28) provided in a surface (29) of the extension (26) which faces the rotor disc unit (14) being connected by interference with a projection, which is complementary to the recess and is provided on the rotor disc unit (14); the body (22) has an outer generatrix which is inclined relative to the direction at right-angles to the axis (X) by an angle &agr;1 of between 25° and 35° and an inner generatrix which is inclined by an angle &agr;2 of between 12° and 18°.