Diffuser Guide Vane Inlet Edge Angle Optimization
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Solution Overview
Problem
Current designs for impeller and diffuser blades in turbomachines lack a comprehensive technical theory to reliably improve aerodynamics, leading to inconsistent pressure loss reduction and flow efficiency.
Innovation Solution
The design features two-dimensional blade profiles with varying angles of attack and curvature, where the leading edge angle on the cover disk side is smaller than on the wheel disk side, and the guide vanes are inclined to optimize the flow transition from the impeller to the diffuser, reducing vortex formation and enhancing aerodynamic properties.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional two-dimensional blade profiles are used in impeller and diffuser, then manufacturing is simple, but aerodynamic performance is insufficient with inconsistent pressure loss reduction
Solution Approach 1:
The patent transitions from conventional two-dimensional blade profiles to three-dimensional blade profiles with varying angles of attack along the blade height. This dimensional change allows the blade geometry to better match the three-dimensional flow patterns in the impeller and diffuser, reducing flow separation and vortex formation while maintaining manufacturing feasibility through standardized profile stacks.
Solution Approach 2:
The patent applies different angles of attack at different blade height positions to optimize local flow conditions. The angle of attack varies along the blade height to match the local flow incidence angles, creating optimal aerodynamic conditions at each section of the blade while maintaining overall blade functionality.
2Loss of energy
If guide vanes are arranged in an inclined shape with large circumferential spacing, then pressure loss may be reduced, but the effect is inconsistent and depends on specific aerodynamic boundary conditions
Solution Approach 1:
The patent systematically varies the angle of attack parameter along the blade height and across different blade positions to optimize aerodynamic performance. By changing geometric parameters in a controlled manner rather than using fixed inclined shapes, the design achieves consistent pressure loss reduction across different operating conditions and boundary conditions.
Solution Approach 2:
The patent introduces dynamic adaptation to flow conditions by varying the blade profile characteristics along the height, allowing the blade to respond to changing flow angles and velocities at different radial positions. This dynamic geometric variation provides more reliable and consistent aerodynamic performance compared to static inclined arrangements.
3Reliability
If three-dimensional diffuser-guide vane designs are used downstream of open impeller, then flow patterns improve, but the design is not comparable to closed impeller conditions due to adhesion differences
Solution Approach 1:
The patent develops a universal three-dimensional blade profile design methodology that can be applied to both open and closed impeller configurations. By focusing on the fundamental flow physics and using scalable geometric parameters, the design achieves good flow patterns across different impeller types without requiring completely separate design approaches for each configuration.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This configuration results in a significant improvement in aerodynamic performance by ensuring a loss-free flow into the diffuser and reducing pressure loss, achieving a harmonious, low-pressure flow pattern.
Implementation Method 1
a stationary diffuser located downstream of the impeller and equipped with guide vanes
Implementation Method 2
ensuring a loss-free flow into the diffuser and reducing pressure loss
Data Source
Figure 1~2
Figure 3
Figure 4
AI summary
The invention relates to an arrangement (ARG), through which a process fluid (PFF) can flow along a main flow direction (MFD), comprising an impeller (IMP) that can rotate about an axis (X) in a rotation direction (RTD) and a stationary diffuser (DFF) located downstream of the impeller (IMP) and being provided with guide vanes (VNE), wherein the impeller (IMP) has an inlet (ILI) for a substantially axial inflow and an outlet (EXI) for a substantially radial outflow, wherein: radially and axially extending impeller vanes (BLD) are arranged between a wheel disc (HWI) and a cover disc (SWI) of the impeller (IMP), said vanes separating impeller channels (ICH) from one another in a circumferential direction (CDR); the diffuser (DFF) extends substantially radially along a main flow direction (MFD); the diffuser (DFF) has an axial cover disc side (SWS) and an axial wheel disc side (HWS) which delimit an axial channel width (SAC) of the diffuser (DFF) therebetween; the diffuser (DFF) has a diffuser inlet (IND) for a substantially radial inflow and a diffuser outlet (EXD); and guide vanes (VNE) extending axially along a vane vertical direction and radially along a through-flow direction are arranged between the wheel disc side (HWS) and the cover disc side (SWS) of the diffuser (DFF), said vanes separating the guide vane channels (HCN) from one another in a circumferential direction (CDR). According to the invention, an inlet edge angle (LEA) for each axial vane height is defined as an angle between an inlet edge tangent (TLV) on a mean line (BWL) on an inlet edge (DLE) of the respective guide vane (VNE) and a circumferential tangent (CTG) through the inlet edge, wherein the inlet edge angle (LEA) is smaller on the cover disc side than on the wheel disc side.