Turbocharger Compressor Cover Groove Alignment
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Solution Overview
Problem
Traditional turbocharger designs suffer from inefficiencies due to turbulence and leakage, which hinder the conversion of exhaust heat energy into rotational power and air compression efficiency.
Innovation Solution
A turbocharger compressor cover with a circumferential groove and edge relief, such as a 45-degree chamfer, is designed to improve the alignment of the compressor wheel blades, reducing flow separation and noise, and enhancing pressure ratio characteristics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If traditional turbocharger compressor designs are used, then the structure is simple, but turbulence and leakage occur reducing efficiency
Solution Approach 1:
The patent applies local quality by introducing a circumferential groove with specific geometric features (trailing edge alignment, edge relief chamfer) at the critical inlet passage location. This localized modification optimizes flow conditions specifically where air enters the compressor wheel, improving overall compressor efficiency without requiring complex changes throughout the entire compressor structure.
Solution Approach 2:
The circumferential groove is segmented into distinct geometric features: the groove itself, the trailing edge alignment portion, and the edge relief chamfer. This segmentation allows each feature to address specific flow issues independently - the groove controls flow separation, the trailing edge alignment reduces turbulence, and the chamfer minimizes leakage, collectively improving compressor efficiency.
2Object-affected harmful factors
If traditional inlet passage design is used, then manufacturing is simple, but flow separation and noise occur
Solution Approach 1:
The circumferential groove with trailing edge alignment and edge relief chamfer performs preliminary flow conditioning before air enters the compressor wheel. By pre-aligning the flow and preventing separation at the inlet passage, the groove reduces downstream turbulence and noise without requiring complex active control systems or post-processing adjustments.
Solution Approach 2:
The patent modifies geometric parameters of the inlet passage by introducing a circumferential groove with specific dimensions - the groove depth, width, and chamfer angle (e.g., 45 degrees). These parameter changes optimize flow characteristics, reducing flow separation and noise while remaining compatible with standard manufacturing processes for metal forming and machining.
Data Source
AI summary
A turbocharger compressor cover (114) including an inner shroud contour (122) configured to receive a compressor wheel (118) having a plurality of blades (140). Each blade (140) includes a leading edge (142), a contour edge (144), and a trailing edge (146). An inlet passage (124) leads to the inner shroud contour (122) and a circumferential groove (130) is formed around the inlet passage (124). The groove (130) includes a trailing edge (136) that is aligned with the outboard end (148) of the leading edge (142) of the blades. The compressor cover (114) includes an edge relief (138) formed along the groove trailing edge (136), such as a 45 degree chamfer. The circumferential groove (130) has a width and a depth, wherein the width and depth are approximately equal. The chamfer intersects the groove (130) approximately half the depth from the bottom of the groove (130).