Turbofan Fan Blade Circumferential Offset for Compact High-Pressure Design
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Solution Overview
Problem
Modern turbofan engines face challenges in achieving higher overall pressure ratio (OPR) and reducing the number of booster stages to enhance efficiency and compactness.
Innovation Solution
The turbofan engine design features circumferentially mounted main blades and spinner blades, with each spinner blade offset to a corresponding main blade, optimizing the radius ratio and axial chord ratio to improve aerodynamic performance and airflow efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If the number of booster stages is reduced to achieve a more compact turbofan engine, then the engine size and complexity are reduced, but the overall pressure ratio (OPR) and airflow efficiency may deteriorate
Solution Approach 1:
The fan assembly is segmented into two distinct blade rows: spinner blades positioned forward of the main blades. This segmentation allows each blade row to perform specialized functions, with the spinner blades pre-conditioning the airflow before it reaches the main blades, thereby achieving high pressure ratio with fewer overall stages
Solution Approach 2:
The invention introduces a new spatial dimension by placing spinner blades axially forward of the main blades, creating a multi-row configuration along the axial direction. This dimensional arrangement enables progressive compression through multiple blade rows without increasing the radial or circumferential complexity of the engine
2Length of moving object
If the fan diameter is reduced to achieve a more compact engine configuration, then the engine size is reduced, but the airflow capacity and power generation may deteriorate
Solution Approach 1:
The spinner blades are designed with specific local geometric properties including optimized chord lengths and airfoil sections tailored for their position forward of the main blades. This local optimization of blade geometry enables efficient airflow conditioning and pressure rise within a compact fan diameter
Solution Approach 2:
The dual-row blade configuration creates a composite aerodynamic structure where spinner blades and main blades work together as an integrated system. The combination of these two blade rows produces synergistic effects that enhance total airflow capacity and pressure ratio beyond what a single blade row could achieve alone
Data Source
AI summary
A turbofan engine includes a compressor rotor, a plurality of main blades circumferentially mounted on the compressor rotor, and a plurality of spinner blades circumferentially mounted on the compressor rotor. Each of the spinner blades is located forward of a leading edge of a corresponding one of the main blades. Each of the spinner blades is circumferentially offset to the corresponding one of the main blades.