Compressor Blade Leading Edge Inclination for Shock Wave Suppression
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Solution Overview
Problem
Centrifugal compressors experience performance degradation due to shock wave development during high-speed operation, primarily caused by the leading edge shape of the main blade.
Innovation Solution
The compressor design features a leading edge of the main blades that is inclined at least 50% of the blade length in the radial direction, with a maximum inclination angle of 3 to 20 degrees, to suppress shock wave generation and enhance performance in high-speed rotation regions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the leading edge of the main blade is designed with a conventional shape, then the compressor structure is simple and easy to manufacture, but shock waves are generated during high-speed operation causing performance degradation
Solution Approach 1:
The leading edge of the main blade is designed with a specific inclination angle (3 to 20 degrees) in the radial direction outward, creating a localized geometric feature that suppresses shock wave generation during high-speed operation. This local modification to the blade geometry improves compressor performance in the high-speed rotation region without fundamentally changing the overall blade structure
Solution Approach 2:
The leading edge is designed with a curved inclination rather than a straight edge, creating a smooth transitional surface that reduces shock wave formation. The curved geometry allows for gradual flow adaptation during high-speed rotation, improving aerodynamic performance while maintaining manufacturing feasibility
2Productivity
If the leading edge is inclined at a large angle to suppress shock waves, then high-speed performance improves, but stress concentration at the blade root increases
Solution Approach 1:
The inclination angle of the leading edge is optimized within a specific range (3 to 20 degrees) to balance two competing requirements: suppressing shock wave generation for improved high-speed performance while limiting stress concentration at the blade root. This parameter optimization achieves the best compromise between aerodynamic performance and structural integrity
3Productivity
If the leading edge is inclined to suppress shock waves, then high-speed performance improves, but vibration at the blade tip increases
Solution Approach 1:
The leading edge inclination angle is optimized within a specific range (3 to 20 degrees) to simultaneously address multiple performance aspects: suppressing shock waves for improved compression performance while limiting excessive blade tip vibration. This parameter control achieves balanced performance across different operational criteria
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 effectively reduces shock wave development and improves compressor performance in high-speed rotation regions by maintaining a long connection length between the blade and hub, reducing stress concentration, and enhancing tip rigidity and vibration suppression.
Implementation Method 1
a shock wave is developed during high-speed operation of an impeller caused by a leading edge shape of a main blade
Data Source
Figure 1~2
Figure 3(a)~3(b)
Figure 4
AI summary
A compressor (1) that compresses a gas that flows in from the axial direction and discharges the gas in the radial direction or in a direction that is diagonal with respect to the axial direction includes: a rotating shaft (2); an impeller (3) that rotates together with the rotating shaft; and a compressor housing (6) that rotatably accommodates the impeller. The impeller includes: a hub (4) that is fixed to the rotating shaft and a plurality of main blades (5) that are provided so as to protrude from the hub. A leading edge (5b) of each of the main blades, when the impeller is viewed from the axial direction, at a position that is at least 50% of the length (L) of the blades that extend outward in the radial direction, is inclined to a rotation direction side with respect to the radial direction outward in the radial direction.