Compressor Vane Surface Irregularity for Corner Stall Reduction
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing designs for turbomachine compressor blades fail to optimize aerodynamic efficiency due to aerodynamic losses caused by interferences and secondary phenomena such as tip leakage vortex and corner stall, despite contouring and protrusion designs.
Innovation Solution
Incorporating a single irregularity in the form of a protrusion or recess on the blade surfaces, oriented parallel to the leading edge, with varying thickness or depth, positioned between 25-75% of the blade height, and forming an angle of 0-20° or 45-90° with the leading edge, to guide airflow efficiently.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional blade designs are used, then manufacturing is simple, but aerodynamic losses occur due to interferences and secondary phenomena
Solution Approach 1:
The patent applies local quality by introducing a specific irregularity (protrusion or recess) at a localized region of the blade surface rather than modifying the entire blade. This localized modification targets the specific area where secondary phenomena occur, improving aerodynamic performance without requiring complex global geometric changes.
Solution Approach 2:
The patent introduces a new dimensional aspect to blade design by adding surface irregularities that extend in a direction substantially perpendicular to the main flow direction. This additional dimensional feature (the irregularity with its specific orientation and dimensions) creates new flow control mechanisms that reduce aerodynamic losses without significantly increasing overall blade complexity.
2Productivity
If blade contouring with multiple protrusions is implemented, then aerodynamic performance improves, but manufacturing complexity increases
Solution Approach 1:
The patent extracts the essential feature from complex multi-protrusion designs by identifying that a single strategically positioned irregularity can provide the necessary flow control. This simplification removes unnecessary geometric features while retaining the core aerodynamic benefit, making manufacturing easier while maintaining compressor efficiency.
Solution Approach 2:
Instead of adding multiple protrusions to control flow, the patent explores the inverted approach of using a recess or a single simplified irregularity shape. This inversion reduces manufacturing complexity while achieving similar or superior aerodynamic performance by fundamentally changing the geometric approach from additive to subtractive or simplified forms.
3Reliability
If blade irregularities are added to reduce secondary phenomena, then aerodynamic efficiency improves, but blade structural complexity increases
Solution Approach 1:
The patent applies parameter changes by carefully controlling the dimensions, position, and orientation of the blade irregularity within specific ranges (e.g., depth between 1-15% of blade thickness, orientation angle between 0-20 degrees). These parameter optimizations ensure that the irregularity provides flow stability benefits while maintaining structural simplicity and avoiding excessive complexity.
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
The irregularity design enhances airflow reshaping, reduces separation, increases flow rate, and improves mechanical and aerodynamic stability while being lightweight and cost-effective.
Implementation Method 1
the irregularity is capable of forming an air-guiding surface
Data Source
Figure 1~2
Figure 3~4
Figure 5A~6
AI summary
The invention relates to a turbojet compressor blade (26), the blade (26) comprising a leading edge (40), a trailing edge (42), an upper surface (44), and an lower surface (46), notable in that it includes at least one irregularity (52) in the form of a protrusion projecting from the upper surface (44) or the lower surface (46), or in the form of a recess embedded in the upper surface (44) or the lower surface (46). The irregularity (52) may have a larger dimension substantially parallel to the leading edge (40) or substantially axial. The invention also relates to a method for manufacturing such a blade, to a compressor equipped with such a blade, and to an axial turbomachine.