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A rotary turbomachine, and particularly a turbojet engine, has a compressor stage that is especially adapted for operation in the transonic region. The compressor stage includes a rotor (1) having a hub (2) and a plurality of compressor blades (3) extending radially therefrom, and a stator having a

A rotary turbomachine, and particularly a turbojet engine, has a compressor stage that is especially adapted for operation in the transonic region. The compressor stage includes a rotor (1) having a hub (2) and a plurality of compressor blades (3) extending radially therefrom, and a stator having a plurality of compressor blades extending radially between a stator hub and a housing. The hub (2) of the rotor (1), and/or the hub of the stator, and/or the housing of the stator, have a circumferential surface contour that is not continuously rotationally symmetrical. Namely, a concave contour (K) is provided in the circumferential surface of the hub near the base of each blade (3) on the pressure side (PS) thereof, while the circumferential surface on the suction side (SS) of the base of each blade has a contour that is linear, slightly convex, convex/concave, or slightly concave to a lesser degree than the concave contour (K) on the pressure side of each blade. The hub contour slopes and transitions smoothly radially outwardly from the concave contour (K) on the pressure side to the flatter or convex contour on the suction side. In this manner, fluid flow velocities on both the pressure side and the suction side of each blade are reduced, especially under transonic operating conditions, and compression shock losses can be minimized.

대표청구항 ▼

[ What is claimed is:] [1.] A rotary machine having a compressor stage adapted for operation under transonic flow conditions, comprising a hub, a plurality of blades respectively extending radially outwardly from said hub, and a cylindrical housing arranged radially outwardly around said blades;wher

[ What is claimed is:] [1.] A rotary machine having a compressor stage adapted for operation under transonic flow conditions, comprising a hub, a plurality of blades respectively extending radially outwardly from said hub, and a cylindrical housing arranged radially outwardly around said blades;wherein each one of said blades has a pressure side adapted to cause fluid flow therealong at a higher relative pressure and a suction side adapted to cause fluid flow therealong at a lower relative pressure;wherein at least one of said hub and said housing has a circumferential surface with a sectional profile that varies around a circumference thereof, said sectional profile has a respective pressure side contour adjacent each one of said blades respectively on said pressure side thereof, and said sectional profile has a respective suction side contour adjacent each one of said blades respectively on said suction side thereof which is different from said pressure side contour; andwherein each said pressure side contour has a first axial section profile shape adapted to reduce the velocity of a subsonic fluid flow respectively on said pressure sides of said blades, and each said suction side contour has a second axial section profile shape adapted to reduce the velocity of a supersonic fluid flow respectively on said suction sides of said blades.