Gas Turbine Airfoil Camber Optimization for Geared Compressor Efficiency
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Solution Overview
Problem
Gas turbine engine compressor sections with geared architectures face challenges due to significantly different compressor speeds, leading to unsuitable aerodynamics and increased downstream turbulence, which complicates the identification and adjustment of design factors to reduce losses.
Innovation Solution
The airfoil camber angle is optimized to be less than 30° at 30% span with a generally linear positive slope from 40% to 60% or 80% span, addressing the aerodynamic challenges by improving the compressor operation in geared architecture engines.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the compressor section uses a geared architecture to enable higher rotational speeds, then the overall efficiency of the engine is improved, but the aerodynamics of the airfoils become unsuitable and downstream turbulence increases
Solution Approach 1:
The patent applies parameter changes by modifying the airfoil geometry parameters (camber angle distribution, thickness distribution, leading edge radius) to suit the higher rotational speeds enabled by geared architecture. Specifically, the camber angle is optimized to be less than 30° at 30% span with a generally linear positive slope from 40% to 60% or 80% span, which reduces downstream turbulence while maintaining the efficiency benefits of high-speed operation.
2Productivity
If the compressor section uses a geared architecture to enable higher rotational speeds, then the overall efficiency of the engine is improved, but the aerodynamics of the airfoils become unsuitable
Solution Approach 1:
The patent modifies airfoil geometric parameters including camber angle distribution (less than 30° at 30% span with linear positive slope from 40% to 60% or 80% span), thickness distribution, and leading edge radius to ensure suitable aerodynamics for high-speed operation in geared architecture engines, thereby maintaining reliability while achieving improved efficiency.
Solution Approach 2:
The patent applies local quality by optimizing different regions of the airfoil with different geometric characteristics. The camber angle distribution varies along the span, with specific values at different span positions (less than 30° at 30% span, linear positive slope from 40% to 60% or 80% span), allowing each region to perform optimally under the high-speed conditions created by geared architecture.
3Ease of manufacture
If prior compressor airfoil geometries are used in geared architecture engines, then manufacturing simplicity is maintained, but the significantly different speeds make the aerodynamics unsuitable
Solution Approach 1:
The patent changes the aerodynamic parameters of the airfoil geometry (camber angle, thickness distribution, leading edge radius) to suit the significantly different speeds in geared architecture engines. These parameter changes maintain manufacturability while ensuring the airfoils perform suitable aerodynamics at the higher rotational speeds.
Data Source
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AI summary
An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with the camber angle having a positive slope from 0% span to 100% span.