Gas Turbine Fan Blade Channel Variations
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine engines face inefficiencies due to flow discontinuities and weight-related issues in the fan section, which affect overall engine performance and fuel consumption.
Innovation Solution
The design includes a rotor hub with airfoils that have varying channel widths and solidity ratios along the span, featuring converging and diverging channels, and stagger angles to optimize aerodynamic efficiency and reduce weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If the fan blades are designed with conventional channel widths and solidity ratios, then the structural simplicity is maintained, but aerodynamic efficiency is reduced due to flow discontinuities and shocks
Solution Approach 1:
The patent applies local quality by varying the channel width and solidity ratio at different span positions along the fan blade. Specifically, the channel width is adjusted to be narrower near the blade root and wider toward the tip, with different solidity ratios applied to different blade sections. This localized optimization reduces flow discontinuities and shocks in specific regions, thereby minimizing aerodynamic losses without requiring complete redesign of the entire blade structure.
Solution Approach 2:
The patent implements parameter changes by systematically modifying geometric parameters including channel width, solidity ratio, and stagger angle along the span of the fan blade. These parameter variations are designed to optimize flow characteristics at different radial positions, reducing flow discontinuities and improving aerodynamic efficiency while maintaining structural feasibility.
2Loss of energy
If the fan section uses higher solidity ratios to improve aerodynamic performance, then efficiency increases, but the weight of the fan blades increases
Solution Approach 1:
The patent applies local quality by using different solidity ratios at different span positions rather than a uniform solidity ratio throughout the blade. This allows higher solidity ratios to be used only where aerodynamic performance benefits are most critical, while maintaining lower solidity ratios in other regions, thereby reducing overall blade weight while still achieving improved aerodynamic efficiency.
Solution Approach 2:
The patent applies partial action by implementing solidity ratio variations only in specific span regions where they provide the greatest benefit, rather than uniformly across the entire blade. This selective application optimizes the trade-off between weight and aerodynamic performance by concentrating structural enhancements where they are most needed.
3Loss of energy
If the channel width is kept uniform along the span, then manufacturing is simplified, but flow continuity is disrupted causing increased aerodynamic losses
Solution Approach 1:
The patent applies local quality by implementing specific channel width variations at different span positions to optimize flow continuity. The channel width is carefully controlled to be narrower near the root and wider toward the tip, with transition regions designed to maintain smooth flow. While this increases geometric complexity, the patent provides detailed guidance on implementing these variations, balancing manufacturing feasibility with aerodynamic performance.
Solution Approach 2:
The patent applies the dynamics principle by designing channel width that varies continuously along the span rather than remaining uniform. This dynamic geometric adaptation allows the blade to better accommodate flow conditions at different radial positions, improving flow continuity and reducing discontinuities while maintaining manufacturing capability through systematic design approaches.
4Productivity
If the fan blades are designed with optimized channel widths and solidity ratios, then aerodynamic efficiency is improved, but the design complexity and manufacturing precision requirements increase
Solution Approach 1:
The patent applies local quality by focusing precision requirements on specific critical regions of the blade rather than uniformly across the entire structure. Channel width and solidity ratio variations are implemented with appropriate tolerance specifications tailored to each span position, allowing optimized aerodynamic performance while managing manufacturing complexity through localized precision control.
Solution Approach 2:
The patent implements parameter changes with systematic variation of channel width, solidity ratio, and stagger angle along the span. These parameter changes are designed to provide clear manufacturing guidance while achieving improved engine efficiency. The patent specifies parameter ranges and transition characteristics that balance aerodynamic optimization with manufacturability, reducing the need for excessive manufacturing precision while maintaining performance benefits.
Data Source
AI summary
A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor including a rotor hub and an array of blades circumferentially spaced about the rotor hub, a geared architecture, a compressor section and a turbine section. Each blade includes pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, adjacent blades in the array of blades including a first blade and a second blade, a facing pressure side of the first blade and a facing suction side of the second blade defining a channel having a width that varies in a chordwise direction between the facing pressure and suction sides at a given span position of the first and second blades. The width at each pressure side location of the first blade along the channel is defined as a minimum distance from the respective pressure side location to a location along the suction side of the second blade, and the width of the channel converges in the chordwise direction to establish a throat.