Backfeed Stage Guide Vane Asymmetry for Radial Compressor Flow
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Solution Overview
Problem
Existing recirculation stages in radial turbo fluid energy machines are space-consuming and lossy due to inefficient flow management, particularly in multi-stage single-shaft compressors where fluid must be routed to downstream impellers without twisting.
Innovation Solution
A compact recirculation stage design with a first section that directs fluid radially outward, a second section that deflects fluid from radially outside to radially inward, and a third section that guides fluid axially, utilizing staggered and asymmetrically arranged guide vanes to reduce aerodynamic losses, with the second guide vanes positioned closer to the suction side of the first vanes for improved flow alignment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional recirculation stage design is used, then the structure is simple and easy to manufacture, but the device occupies more space and generates higher flow losses
Solution Approach 1:
The patent applies asymmetry by positioning the second guide vanes closer to the suction side of the first guide vanes rather than symmetrically between them. This asymmetric arrangement optimizes the flow path, reducing aerodynamic losses and improving flow alignment while maintaining structural feasibility
Solution Approach 2:
The patent utilizes three-dimensional spatial optimization by arranging guide vanes in multiple sections (first, second, and third sections) with different orientations. The second guide vanes are positioned at an optimized distance from the first guide vanes' suction side, creating a compact yet efficient flow path that reduces losses without excessive complexity
2Volume of moving object
If conventional recirculation stage design is used, then the structure is simple, but the device occupies more space
Solution Approach 1:
The patent achieves compactness through three-dimensional optimization of the guide vane arrangement. By positioning the second guide vanes at an optimized distance from the first guide vanes and creating a multi-section recirculation path, the design reduces the overall volume occupied by the recirculation stage while maintaining efficient flow characteristics
Solution Approach 2:
The patent employs curved flow paths in the recirculation stage, particularly in the second section where the flow is deflected from radially outside to radially inside. The smooth curved transitions minimize flow separation and turbulence, reducing energy losses in the compact configuration
Data Source
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AI summary
The invention relates to a backfeed stage (BFS) of a radial turbo fluid energy machine (RTFEM), in particular a radial turbo compressor (RTC), for deflecting a flow direction (FD) of a process fluid (PF) flowing out of a rotor (R) rotating about an axis (X) from radially outward to radially inward, comprising a backfeed channel (BFC), which has three sections (S1, S2, S3) adjacent in the flow direction, wherein a first section (S1) is designed to conduct the process fluid (PF) radially outward, wherein a second section (S2) is designed to deflect the process fluid (PF) from radially outward to radially inward, wherein a third section (S3) is designed to conduct the process fluid (PF) radially inward, wherein the second section (S2) and the third section (S3) or only the third section (S3) has first guide vanes (L1), which define flow channels (FC) of the backfeed channel (BFC) in relation to each other in the circumferential direction. In order to improve efficiency, the second section (S2) and the third section (S3) or only the third section (S3), according to the invention, has second guide vanes (L2), leading edges (L2LE) of which are offset downstream to leading edges (L1LE) of the first guide vanes (L1) and which define flow channels (FC) of the backfeed channel (BFC) in relation to each other in the circumferential direction, wherein the second guide vanes (L2) are designed and arranged in such a way that, in a radially extending plane in the region of the axial extent of the third section (S3), a connection line (CLTE) through two trailing edges (L1TE) of adjacent first guide vanes (L1) is divided non-centrally by a radial stream (RS) through the leading edge (L1LE) of a second guide vane (L2) arranged between the two first guide vanes (L1) in the circumferential direction.