Sealing structure on a shroud of a turbine blade

1. A sealing device on a shroud of a turbine rotor blade tip, the sealing device including five surface sections extending along a longitudinal axis of the sealing device, comprising:

first and second side edges extending parallel to the longitudinal axis and delimiting a first surface section, and a rear third delimiting edge inclined relative to the longitudinal axis, wherein the first and second side edges have a mutual latitudinal spacing f 1 , the first side edge extending to a distance a 1 and the second side edge extending to a distance a 2 , the distances a 1 and a 2 being measured from a first reference plane B 1 which orthogonally intersects the longitudinal axis and delimits an end face at a rear end wherein the second side edge is spaced a distance from the first reference plane B 1 and is connected to the first side edge via the rear third delimiting edge;

fourth and fifth side edges extending in an inclined manner relative to the longitudinal axis and delimiting a second surface section, the fourth side edge extending from an end of the first side edge to a distance b 1 , and the fifth side edge extending from the second side edge to a distance b 2 , both the distances b 1 and b 2 measured from the first reference plane B 1 ;

sixth and seventh side edges extending parallel to the longitudinal axis and delimiting a third surface section, the sixth and seventh side edges having a mutual latitudinal spacing f 2 , the sixth side edge being connected to the fourth side edge and the seventh side edge being connected to the fifth side edge;

eighth and ninth side edges extending parallel to the longitudinal axis and delimiting a fifth surface section, and a front tenth delimiting edge inclined relative to the longitudinal axis, the eighth and ninth side edges having a mutual latitudinal spacing f 3 , the eighth side edge extending to a distance c 1 and the ninth side edge extending to a distance c 2 , the distances c 1 and c 2 being measured from a second reference plane B 2 which orthogonally intersects the longitudinal axis and delimits an end face at a front end, wherein the eighth side edge is spaced from the second reference plane and is connected to the ninth side edge via the front tenth delimiting edge; and

eleventh and twelfth side edges each comprising a cutting edge e 1 , e 2 and together delimiting a fourth surface section, the eleventh and twelfth side edges both extending in an inclined manner relative to the longitudinal axis, the eleventh cutting edge extending from a distance d 1 to the distance c 1 , and the twelfth cutting edge extending from a distance d 2 to the distance c 2 , the distances d 1 and d 2 being measured from the second reference plane, and the eleventh side edge is connected to the sixth side edge and the twelfth side edge is connected to the seventh side edge,

wherein the cutting edges e 1 , e 2 facing in the direction of rotation, serve as transition regions between the rib region, of narrower design in the axial extent, in the fifth surface section with the mutual latitudinal spacing f 3 , and the third surface section, of axially wider design, with the mutual latitudinal spacing f 2 , and

wherein the first and second reference planes B 1 and B 2 are spaced apart a distance S, and

S=45 mm to 200 mm,

A 1 <a 2 and 1/16 S<(a 1 , a 2 )<½ S,

b 1 <b 2 and 1/16 S<(b 1 , b 2 L<½ S,

c 1 <c 2 and 1/16 S<(c 1 , c 2 )<½ S,

d 1 <d 2 and 1/16 S <(d 1 , d 2 )<½ S,

f 3 <f 1 and 1/62 S <(f 1 , f 3 )< 1/14 S, and

1/42 S<f 2 <⅕ S.

2. The device as claimed in claim 1 , wherein at least the eleventh and twelfth side edges are coated with a surface-hardened coating and are configured and arranged as cutting structures.

3. The device as claimed in claim 1 , wherein:

the first, second, sixth, and seventh side edges each are spaced from the longitudinal axis; and

the longitudinal axis aligns with the eighth side edge.

4. The device as claimed in claim 1 , comprising:

side flanks extending in an inclined manner relative to a flat end face, which is configured to radially face away from the turbine rotor blade, the inclinations of which side flanks each face each other, and wherein the side flanks each include radially upper edges which delimit the flat end face.

5. The device as claimed in claim 4 , wherein the side flanks include flanks at the sixth and seventh side edges which are each inclined at an inclination angle of between 0.1° and 45° to orthogonals of the third surface section.

6. The device as claimed in claim 1 , comprising:

a surface-hardened coating included to at least one of the surface sections.

7. The device as claimed in claim 6 , wherein the surface-hardened coating has a coating thickness of up to 4.5 mm.

8. The device as claimed in claim 6 , wherein the surface-hardened coating consists essentially of Cr 2 C or CBN.

9. A turbine blade shroud comprising:

a shroud plate having a radially outer surface; and

at least one sealing device according to claim 1 on the radially outer surface.

10. The turbine blade shroud as claimed in claim 9 , wherein a longitudinal length of the sealing device is a length of the shroud in a direction of rotation.

11. The turbine blade shroud as claimed in claim 9 , wherein the at least one sealing device tapers with increasing radial distance from the shroud.

12. A turbine blade comprising:

an airfoil having a tip and a root end, wherein the root end is configured and arranged to be attached to a rotor; and

a turbine blade shroud according to claim 9 attached to said airfoil tip.

13. A turbine blade according to claim 12 , wherein:

the airfoil comprises a contour which defines a pressure side and a suction side of the blade.

14. A turbine blade according to claim 12 , wherein:

the at least one sealing device is arranged as a line of ribs radially projecting over the shroud relative to a rotational axis around which the turbine rotor blade is rotatably arranged;

the at least one sealing device has a longitudinal length oriented in the direction of rotation of the turbine rotor blade;

the at least one sealing device tapers with increasing radial distance from the shroud and terminates at a flat end face which radially faces away from the turbine rotor blade.

15. The device as claimed in claim 1 , wherein:

the distance a 1 is less than the distance b 1 ;

the distance a 2 is less than the distance b 2 ;

the distance c 1 is less than the distance d 1 ; and

the distance c 2 is less than the distance d 2 .

16. The device as claimed in claim 1 , wherein

the distance a 1 extends from the first reference plane B 1 to the end of the first side edge,

the distance a 2 extends from the first reference plane B 1 to an end of the second side edge, and wherein the fifth side edge extends from the end of the second side edge,

the distance c 1 extends from the second reference plane B 2 to an end of the eighth side edge, and

the distance c 2 extends from the second reference plane B 2 to an end of the ninth side edge.

17. A sealing device on a shroud of a turbine rotor blade tip, the sealing device including five surface sections extending along a longitudinal axis of the sealing device, comprising:

first and second side edges extending parallel to the longitudinal axis and delimiting a first surface section, and a rear third delimiting edge inclined relative to the longitudinal axis, wherein the first and second side edges have a mutual latitudinal spacing f 1 , the first side edge extending to a distance a 1 and the second side edge extending to a distance a 2 , the distances a 1 and a 2 being measured from a first reference plane B 1 which orthogonally intersects the longitudinal axis and delimits an end face at a rear end wherein the second side edge is spaced a distance from the first reference plane B 1 and is connected to the first side edge via the rear third delimiting edge;

fourth and fifth side edges extending in an inclined manner relative to the longitudinal axis and delimiting a second surface section, the fourth side edge extending from an end of the first side edge to a distance b 1 , and the fifth side edge extending from the second side edge to a distance b 2 , both the distances b 1 and b 2 measured from the first reference plane B 1 ;

sixth and seventh side edges extending parallel to the longitudinal axis and delimiting a third surface section, the sixth and seventh side edges having a mutual latitudinal spacing f 2 , the sixth side edge being connected to the fourth side edge and the seventh side edge being connected to the fifth side edge;

eighth and ninth side edges extending parallel to the longitudinal axis and delimiting a fifth surface section, and a front tenth delimiting edge inclined relative to the longitudinal axis, the eighth and ninth side edges having a mutual latitudinal spacing f 3 , the eighth side edge extending to a distance c 1 and the ninth side edge extending to a distance c 2 , the distances c 1 and c 2 being measured from a second reference plane B 2 which orthogonally intersects the longitudinal axis and delimits an end face at a front end, wherein the eighth side edge is spaced from the second reference plane and is connected to the ninth side edge via the front tenth delimiting edge; and

eleventh and twelfth side edges each comprising a cutting edge e 1 , e 2 and together delimiting a fourth surface section, the eleventh and twelfth side edges both extending in an inclined manner relative to the longitudinal axis, the eleventh cutting edge extending from a distance d 1 to the distance c 1 , and the twelfth cutting edge extending from a distance d 2 to the distance c 2 , the distances d 1 and d 2 being measured from the second reference plane, and the eleventh side edge is connected to the sixth side edge and the twelfth side edge is connected to the seventh side edge,

wherein the distance a 1 is less than the distance b 1 , the distance a 2 is less than the distance b 2 , the distance c 1 is less than the distance d 1 , and the distance c 2 is less than the distance d 2 , and

wherein the cutting edges e 1 , e 2 facing in the direction of rotation, serve as transition regions between the rib region, of narrower design in the axial extent, in the fifth surface section with the mutual latitudinal spacing f 3 , and the third surface section, of axially wider design, with the mutual latitudinal spacing f 2 , and

wherein the first and second reference planes B 1 and B 2 are spaced apart a distance S, and

S=45 mm to 200 mm,

A 1 <a 2 and 1/16 S<(a 1 , a 2 )<½ S,

b 1 <b 2 and 1/16 S<(b 1 , b 2 L<½ S,

c 1 <c 2 and 1/16 S<(c 1 , c 2 )<½ S,

d 1 <d 2 and 1/16 S <(d 1 , d 2 )<½ S,

f 3 <f 1 and 1/62 S<(f 1 , f 3 )< 1/14 S, and

1/42 S<f 2 <⅕ S.

18. The device as claimed in claim 17 , wherein

the distance a 1 extends from the first reference plane B 1 to the end of the first side edge,

the distance a 2 extends from the first reference plane B 1 to an end of the second side edge, and wherein the fifth side edge extends from the end of the second side edge,

the distance c 1 extends from the second reference plane B 2 to an end of the eighth side edge, and

the distance c 2 extends from the second reference plane B 2 to an end of the ninth side edge.