Abstract: A compressor, in particular, of a turbomachine. The compressor comprises at least one blade ring and at least two ring segments, wherein the blade ring has at least two equally large ring segments. The compressor also comprises blades, which are arranged in the ring segments of the blade ring in such a way that a first number of blades is arranged in a first ring segment and a second number of blades is arranged in a second ring segment. The first number of blades is not equal to the second number of blades.

Abstract: A guide vane airfoil for placement in a flow path portion of a turbomachine is provided, which, relative to a flow pattern in flow path portion, has a leading edge and, downstream thereof, a trailing edge, as well as a suction side and a pressure side; relative to a longitudinal axis of the turbomachine, viewed in the axial direction, in a radially inner portion, forming a first angle ? with a circular arc about the longitudinal axis, and, in a radially outer portion, a second angle ? with a circular arc about the longitudinal axis. The guide vane airfoil is inclined in the outer portion, thus ??90°, in terms of absolute value, being >0° (|??90°|>0°), and the guide vane airfoil being more highly inclined in the outer portion than in the inner portion, thus ??90°, in terms of absolute value, being >??90° (|??90°|>??90°).

Abstract: A guide vane airfoil for placement in a flow path portion of a turbomachine is provided, which, relative to a flow pattern in flow path portion, has a leading edge and, downstream thereof, a trailing edge, as well as a suction side and a pressure side; relative to a longitudinal axis of the turbomachine, viewed in the axial direction, in a radially inner portion, forming a first angle ? with a circular arc about the longitudinal axis, and, in a radially outer portion, a second angle ? with a circular arc about the longitudinal axis. The guide vane airfoil is inclined in the outer portion, thus ??90°, in terms of absolute value, being >0° (|??90°|>0°), and the guide vane airfoil being more highly inclined in the outer portion than in the inner portion, thus ??90°, in terms of absolute value, being >??90° (|??90°|>??90°).

Abstract: A compressor, in particular, of a turbomachine The compressor comprises at least one blade ring and at least two ring segments, wherein the blade ring has at least two equally large ring segments. The compressor also comprises blades, which are arranged in the ring segments of the blade ring in such a way that a first number of blades is arranged in a first ring segment and a second number of blades is arranged in a second ring segment. The first number of blades is not equal to the second number of blades.