Patent ID: 9512727
Filing Date: 2016-12-06
CPC Classification: F01D,F05D,Y02T

Claim Text:
1. A rotor of an axial compressor stage of a turbomachine, comprising: a rotor assembly including a rotary axis, a circumference, and a blade ring with a radially outer ring surface formed on the circumference, and a plurality of rotor blades arranged on the blade ring, wherein the ring surface has at least in an area between two adjacent rotor blades of the plurality of rotor blades, a changing radius relative to the rotary axis of the rotor assembly both in an axial direction and in a circumferential direction; wherein, in the area between two adjacent rotor blades, the ring surface is shaped to have a resultant surface line including a concave depression positioned toward an axially front face of the blade ring transitioning to a convex bulge positioned toward an axially rear face of the blade ring; wherein, the convex bulge includes a peak spaced circumferentially apart from both a suction side surface of one of the two adjacent rotor blades and an opposing pressure side surface of another of the two adjacent rotor blades, the peak positioned closer to the suction side surface; wherein, in the area between two adjacent rotor blades where the ring surface is shaped with the concave depression and the convex bulge, a second surface line of a section through the blade ring in a plane normal to the rotary axis conforms to a mathematical function including at least one chosen from: a sine function, a cosine function and a combination of sine and cosine functions; wherein, in the area between two adjacent rotor blades, every section through the blade ring in a further plane normal to the rotary axis has a surface line defined by at least one chosen from: a sine function, a cosine function and a combination of sine and cosine functions.