Blade row for a turbomachine

摘要

A blade row for a turbomachine, in particular a gas turbine, is disclosed. The blade row has a number of first blade arrangements each having at least one first blade and a first shroud with a first extension in the circumferential and/or axial direction and at least a number of additional blade arrangements each having at least one additional blade and one additional shroud with an additional extension in the same direction, which is different from the first extension.

主权项

1. A blade row for a turbomachine, comprising:
a plurality of first blade arrangements each having a first shroud and a first number of blades, wherein the first shroud is attached to a respective tip of the first number of blades, and wherein the first shroud has a first extension in a circumferential direction; and a plurality of second blade arrangements each having a second shroud and a second number of blades, wherein the second shroud is attached to a respective tip of the second number of blades, and wherein the second shroud has a second extension in the circumferential direction; wherein adjacent first and second shrouds in the blade row have complementary, undulated contact surfaces facing each other in the circumferential direction, wherein the first number of blades is equal to the second number of blades, and wherein the first extension is longer than the second extension; and wherein an overhang of the blades in the first blade arrangements in an axial direction relative to the first shroud is the same as the overhang of the blades in the second blade arrangements in the axial direction relative to the second shroud.