Sealing structure on a shroud of a turbine blade

摘要

A device on a shroud which is provided on a turbine rotor blade tip has a cutting structure designed like a line of ribs, locally projecting over the shroud radially to the rotational axis around which the turbine rotor blade is rotatably arranged. The sealing structure has a longitudinal extent (S) oriented in the direction of rotation (U) of the turbine rotor blade, tapers with increasing radial distance from the shroud, and terminates with a flat end face (St) which radially faces away from the turbine rotor blade, and can be divided into five interrelated surfaces.

主权项

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 f1, the first side edge extending to a distance a1 and the second side edge extending to a distance a2, the distances a1 and a2 being measured from a first reference plane B1 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 B1 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 b1, and the fifth side edge extending from the second side edge to a distance b2, both the distances b1 and b2 measured from the first reference plane B1; 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 f2, 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 f3, the eighth side edge extending to a distance c1 and the ninth side edge extending to a distance c2, the distances c1 and c2 being measured from a second reference plane B2 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 e1, e2 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 d1 to the distance c1, and the twelfth cutting edge extending from a distance d2 to the distance c2, the distances d1 and d2 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 e1, e2 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 f3, and the third surface section, of axially wider design, with the mutual latitudinal spacing f2, and wherein the first and second reference planes B1 and B2 are spaced apart a distance S, and
S=45 mm to 200 mm,A1