A turbomachine ( 1 ), in particular a gas turbine, has a stator ( 2 ) and a rotor ( 3 ) and with at least one axial sealing device ( 6 ) arranged between them. On the stator side, the sealing device ( 6 ) has a radially stepped sealing contour ( 8 ) with regions ( 9, 10 ) projecting and retracting in the direction of the rotor ( 3 ), on the rotor side a plurality of sealing fins ( 11 ) projecting in the direction of the stator ( 2 ) being arranged, which engage in each case into adjacent retracting regions ( 10 ) of the stator-side sealing contour ( 8 ). On the rotor side, at least one additional fin ( 12 ) projecting in the direction of the stator ( 2 ) is provided, which is positioned between two adjacent sealing fins ( 11 ) arranged on the rotor side and which lies opposite a projecting region of the stator-side sealing contour ( 8 ).
1. A turbomachine comprising:
a stator, a rotor, and an axial sealing device arranged between the stator and the rotor, wherein the sealing device has on the stator side a radially stepped sealing honeycomb contour with regions projecting and retracting in the direction of the rotor;
a plurality of sealing fins on the rotor side projecting in the direction of the stator, each of the plurality of sealing fins engaging into adjacent retracting regions of the stator-side sealing contour; and
at least one additional fin on the rotor side projecting in the direction of the stator, the at least one additional fin positioned between two adjacent sealing fins arranged on the rotor side and lying opposite a projecting region of the stator-side sealing contour;
wherein at least one of the at least one additional fin, at least one of the plurality of sealing fins, or both, is arranged inclined radially and axially on the rotor;
wherein a degree of inclination of the at least one additional fin, of the at least one sealing fin, or of both, is approximately 25° to 35°.
2. The turbomachine as claimed in claim 1 , wherein the at least one additional fin, the plurality of sealing fins, or both, is inclined in the direction opposite to the main flow.
3. The turbomachine as claimed in claim 1 , wherein an axial distance between two projecting or retracting stator-side regions is approximately double a radial height (h) of the plurality of sealing fins.
4. The turbomachine as claimed in claim 3 , wherein the radial height (h) of the plurality of sealing fins is 2 to 4 times greater than a radial height of the at least one additional fin.
5. The turbomachine as claimed in claim 1 , wherein a stator-side retracting region is wider than a stator-side projecting region.
6. The turbomachine as claimed in claim 1 , wherein a stator-side retracting region has an axial longitudinal extent of twice to three times a radial height (h) of the plurality of sealing fins, and a stator-side projecting region has an axial longitudinal extent of 1 to 2.5 times said radial height (h).
7. The turbomachine as claimed in claim 1 , wherein the plurality of sealing fins each have a wedge-shaped cross-sectional profile in the circumferential direction.