Axial Flow Impeller Blade Tip Geometry for Vortex Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Conventional blades in rotary machinery suffer from low aerodynamic performance and high noise due to severe flow separation and vortex formation, leading to inefficient air handling and increased noise levels.
Innovation Solution
The blade design features a unique geometry with a blade tip trailing part angled more aggressively than the base part, multiple grooves on the trailing edge, and a smooth extension from the leading edge to the root, which splits large vortices into smaller ones, reducing turbulence and noise, and enhances air volume and static pressure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If the blade uses conventional monotonic smooth curves, then the structure is simple, but flow separation is severe causing low aerodynamic performance and high noise
Solution Approach 1:
The blade is divided into multiple sections with different geometric characteristics: the leading edge has a specific curvature radius, the trailing edge has a beveled structure with multiple grooves, and the blade tip has a bent configuration. This segmentation allows each part to control flow separation locally, transforming the harmful vortex formation into a controlled flow pattern that reduces noise and improves aerodynamic performance.
Solution Approach 2:
Different parts of the blade are given different local geometric properties optimized for their specific functions. The leading edge uses a larger curvature radius to reduce flow separation, the trailing edge uses a beveled structure with grooves to control vortex formation, and the blade tip uses a bent configuration to reduce tip vortices. This local optimization resolves the contradiction between structural simplicity and flow control.
2Productivity
If the blade tip trailing part is bent upwards with greater angle of attack, then aerodynamic performance improves, but blade structure complexity increases
Solution Approach 1:
The blade tip trailing part is designed with a bent configuration that creates a dynamic flow pattern. The upward bending with a greater angle of attack (20-30 degrees) compared to the base part generates controlled vortices that improve aerodynamic efficiency. This dynamic geometric feature, while increasing complexity, is optimized to achieve superior performance in air handling and static pressure.
3Object-generated harmful factors
If multiple grooves are added to the trailing edge, then vortex formation is controlled and noise is reduced, but manufacturing complexity increases
Solution Approach 1:
The trailing edge is segmented into multiple grooves with specific geometric parameters (included angle 10-110 degrees, groove depth H=W×L where W is 1.5-20% of the trailing edge width). This segmentation allows controlled vortex formation in each groove while maintaining overall structural integrity. The standardized groove parameters make the complex structure manufacturable by controlling the geometry within specific ranges.
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 design improves aerodynamic efficiency by 25%, reduces noise by 13%, and increases air volume while maintaining high static pressure, effectively addressing the limitations of conventional blades.
Implementation Method 1
Due to serious flow separation at the surface of the blade, vortices are formed
Implementation Method 2
Due to serious flow separation at the surface of the blade, vortices are formed
Implementation Method 3
the blade has low aerodynamic performance
Data Source
AI summary
Disclosed in the present application is a blade and an axial flow impeller using same. The blade comprises a blade tip, a blade root, a leading edge, a trailing edge, an upper surface and a lower surface. The upper surface and lower surface are disposed opposite each other; the blade tip, the blade root, the leading edge and the trailing edge surround the upper surface and the lower surface, and connect the upper surface and the lower surface. The blade is rotatable about a rotation axis, the rotation axis being perpendicular to a normal plane. The blade tip comprises a blade tip base part and a blade tip trailing part, the blade tip base part being close to the leading edge, and the blade tip trailing part being close to the trailing edge and being bent upwards relative to the blade tip base part. An angle of attack of a chord of the blade tip trailing part is greater than an angle of attack of a chord of the blade tip base part, wherein the angle of attack is an acute included angle between the chord and the normal plane. The blade of the present application can provide a large air volume, and has higher static pressure and higher efficiency.