Blade Trailing-Edge Orientation Structures for Drag and Noise Reduction

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Solution Overview

Problem

Existing blade designs for propellers and fans do not effectively enhance efficiency and lack a method to verify the performance of orientation structures.

Innovation Solution

A design method for blades with orientation structures involves cutting and stretching to form orientation awls and grooves, utilizing chordwise and thickness direction stretching coefficients, and a performance test method to evaluate the modified blades.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Productivity

If orientation structures are added to the blade, then the aerodynamic performance and efficiency are improved, but the manufacturing complexity increases

Engineering Contradiction:

Improveaerodynamic efficiencyVSAvoidblade structure complexity

Core Design Contradiction:

ProductivityVSDevice complexity

Solution Approach 1:

The blade trailing edge is segmented into multiple sections with different stretching coefficients, creating multiple orientation awls at different radial positions. Each awl is formed by independently controlling the stretching and cutting process in its specific radial zone, allowing optimized orientation structures without excessive overall complexity

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Different radial zones of the blade are assigned different chordwise stretching coefficients (first stretching coefficient for inner zone, second stretching coefficient for outer zone). This local differentiation creates orientation awls with varying geometric characteristics suited to local aerodynamic requirements, improving overall efficiency while keeping each local region's manufacturing relatively simple

Inventive Principle:

Principle #3Local quality

2Productivity

If the blade is stretched in chord direction to form orientation awls, then the orientation structure performance is enhanced, but the blade area is reduced

Engineering Contradiction:

Improveorientation structure efficiencyVSAvoidblade pressure surface area

Core Design Contradiction:

ProductivityVSArea of moving object

Solution Approach 1:

The patent applies different stretching coefficients to different radial zones: a first stretching coefficient for the inner zone and a second stretching coefficient for the outer zone. By carefully selecting these parameters, the blade area is reduced sufficiently to create effective orientation awls while maintaining acceptable overall blade size and performance

Inventive Principle:

Principle #35Parameter changes

Solution Approach 2:

Instead of uniformly stretching the entire blade, the patent applies stretching partially - only to the trailing edge regions where orientation awls are needed. The stretching is applied selectively in different radial zones with different coefficients, creating the necessary orientation structures without excessively reducing the total blade area

Inventive Principle:

Principle #16Partial or excessive action

3Object-affected harmful factors

If multiple orientation awls are created at different radial positions, then the drag reduction and noise control are improved, but the manufacturing precision requirements increase

Engineering Contradiction:

Improvedrag and noiseVSAvoidawl geometry precision

Core Design Contradiction:

Object-affected harmful factorsVSManufacturing precision

Solution Approach 1:

The manufacturing process is segmented into distinct stages: first stretching the blade in the chord direction, then cutting the trailing edge, and finally forming the orientation awls by stretching and cutting in the thickness direction. This segmentation allows each operation to be optimized independently, reducing the overall precision burden compared to a single complex operation

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The blade is stretched in the chord direction before cutting and awl formation. This preliminary stretching creates the geometric foundation for the orientation awls, establishing the basic shape and positioning before the more precise thickness-direction operations are performed, thereby facilitating subsequent manufacturing

Inventive Principle:

Principle #10Preliminary action

Data Source

PatentUS20260057127A1Design method for blade with orientation structures, blade and performance test method for blade

Publication Date: 2026.02.26 LIU PINLIANG

AI summary

A design method for a blade with orientation structures, a blade and a performance test method for a blade are provided, which relate to the technical field of blade design, and are universal to blades whose parameters are completely or partially known. In the design method, orientation awls are provided at a trailing edge of a blade from a variable-pitch propeller; orientation awls are provided at a trailing edge of a blade from a fixed-pitch propeller or a fan blade from a jet engine, and orientation grooves are provided on a back of the blade. Meanwhile, during providing orientation awls for either blade, the blade is stretched in a chord direction to ensure that an area of a pressure surface of a modified blade is equal to an area of a pressure surface of its original.