Compressor Blade Dihedral Angle Optimization
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Optimizing the aerodynamic performance of compressor blades in high-pressure compressors while maintaining mechanical strength is challenging, particularly in the stacking of cuts, which affects both efficiency and structural integrity.
Innovation Solution
The compressor blades are designed with a unique profile defined by a sweep angle and dihedral angle, featuring a zone with a strictly positive leading edge dihedral angle near the root and a strictly negative dihedral angle near the tip, optimizing the operability without imposing mechanical constraints, and allowing for improved aerodynamic performance without degrading mechanical strength.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the stacking of cuts is optimized for aerodynamic performance, then the pumping margin and output are improved, but the mechanical strength of the blade may be degraded
Solution Approach 1:
The patent applies local quality by defining different dihedral angle characteristics in different zones of the blade. The first portion (near root) has a strictly positive leading edge dihedral angle while the second portion (near tip) has a strictly negative leading edge dihedral angle. This localized differentiation allows optimization of aerodynamic performance in specific regions without compromising the mechanical strength of other regions, thereby resolving the contradiction between productivity improvement and strength maintenance.
2Ease of operation
If the dihedral angle is optimized for aerodynamic performance, then the operability of the compressor is improved, but mechanical constraints and consumption may increase
Solution Approach 1:
The patent applies parameter changes by specifically defining the dihedral angle parameters in different blade portions. The first portion has a strictly positive leading edge dihedral angle and the second portion has a strictly negative leading edge dihedral angle, with the maximum angle zone positioned between r=0.25h and r=0.65h. These parameter specifications optimize the aerodynamic performance and operability while controlling mechanical constraints and energy consumption through precise geometric control.
Data Source
AI summary
The invention relates to a compressor blade, defined at each one of the points of its surface by a sweep angle and a dihedral angle, comprising: a root, a tip, the distance between the root and the tip, measured along an axis referred to as the radial axis, perpendicular to an axis of rotation of the compressor, being referred to as radial height (h), a zone, between the root and the tip, of which a first portion has a strictly positive leading edge dihedral angle, and a second portion has a strictly negative leading edge dihedral angle, the zone of maximum dihedral angle being, along the radial axis, between r=0.25 h and r=0.7 h.