| 摘要 |
The present invention relates to a centrifugal compressor rotor with serial arrangement of blades, wherein the compressor cascade is divided into two separated sections, where the first section (a) is formed by an inlet axial compressor cascade with axial or axially-diagonal flow with the number n of identical blades distributed regularly along the circumference and the second section (b) is formed by a follow-up compressor cascade with two sets of the number 2n of non-identical blades distributed regularly along the circumference with an axial or diagonal inlet and a radial outlet with outlet angles ({beta}) as measured from the radial direction in positive or and negative sense within the range of +/- 60 degrees, arranged in such a manner the individual blades of the second section (b) compressor cascade form on the rotor disk two different compressor cascades of the second section (B+, B2) with the number of blades of the cascade of the second section (b1) n1 = n and the number of blades of the cascade of the second section (b2) n2 = n, such that the blades of both the cascades of the second section (b1 and b2) mutually alternate along the circumference and between the outlet edges of the both the cascade second sections (b1, b2), there is identical circular pitch (s4) and outlet angles ({beta41} and {beta42}) of the both the cascade second sections (b1, b2) are identical and equal to the outlet angle ({beta}), whereby the second section (b) of the compressor cascade is angularly displaced relative to the first section (a) of the compressor cascade in the direction of the rotor rotational rate ({omega}) such that trailing edges of the first section (a) cascade form with the leading edges of the cascade second section (b) an angle ({gamma}), the magnitude of which is in the angle range of zero to 360 degrees divided by the quadruple of n blades of the first section (a) cascade, i.e. 0 degree <={gamma} > = 360 degrees ÷ 4n. |
