ROTOR
A rotor for a gas-turbine engine, is provided having a first and a second rotor disc that are suitable to be joined directly. The first and second rotor discs are symmetric with respect to an axis of rotation common to the two rotor discs. The first rotor disc provides an interrupted screw on one side. The second rotor disc provides an interrupted screw on another side. The interrupted screw of the second rotor disc reciprocates the interrupted screw of the first rotor disc.
1 . A rotor comprising:
a first rotor disc;
a second rotor disc;
wherein the first rotor disc provides a first interrupted screw on at least one side, the second rotor disc provides a second interrupted screw on at least one side, the second interrupted screw of the second rotor disc being connected to the first interrupted screw of the first rotor disc.
2 . The rotor according to claim 1 , wherein the first and second rotor discs are substantially symmetric with respect to the axis of rotation of the rotor.
3 . The rotor according to claim 1 , wherein the first and second rotor discs are suitable to be connected directly to one another.
4 . The rotor according to claim 1 , wherein at least one of the first and second rotor discs provides two interrupted screws on both of its sides.
5 . The rotor according to claim 1 , wherein the first rotor disc provides a first interrupted screw with a protruding rim with a sidewall, a first set of wedges being arranged along the sidewall of the protruding rim; and
the second rotor disc provides a second interrupted screw comprising a groove with a sidewall, a second set of wedges being arranged along the sidewall of the groove.
6 . The rotor according to claim 5 , wherein the first set of wedges is evenly arranged along the sidewall of the protruding rim and the second set of wedges is evenly arranged along the sidewall of the groove.
7 . The rotor according to claim 5 , wherein the first set of wedges comprises eight wedges and the second set of wedges comprises eight wedges.
8 . The rotor according to claim 1 , wherein the first rotor disc provides an interrupted screw comprising a plurality of slots, and wherein the second rotor disc provides an interrupted screw comprising a plurality of segments .
9 . The rotor according to claim 8 , wherein each slot comprises a clamping surface.
10 . The rotor according to claim 8 , wherein the slots of the first rotor disc are evenly arranged along the inner perimeter of the first rotor disc and the segments of the second rotor disc are evenly arranged along the inner perimeter of the second rotor disc.
11 . The rotor according to claim 8 , wherein the first rotor disc provides six slots and the second rotor disc provides six segments.
12 . A gas-turbine engine with a rotor according to claim 1 .
13 . A turbogenerator with a rotor according to claim 1 .
14 . A method for directly joining a first rotor disc and a second rotor disc, the first rotor disc providing an interrupted screw on at least one side, and the second rotor disc provides an interrupted screw on at least one side, the interrupted screw of the second rotor disc reciprocating the interrupted screw of the first rotor disc;
the method comprising:
connecting the first rotor disc with the second rotor disc by engaging the first interrupted screw of the first rotor disc with the second interrupted screw of the second rotor disc, and rotating the first rotor disc against the second rotor disc by a fraction of a turn.
15 . A method according to claim 11 , wherein the size of the interrupted screw of one rotor disc is increased by heating before engaging the interrupted screws of the two rotor discs.