Fan Blade Pre-Compression Design for Bird Impact Resistance
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Solution Overview
Problem
Gas turbine engine blades and vanes, particularly those made of ceramic matrix composites, are susceptible to damage from bird impacts, and modifications to enhance impact resistance cannot have a negative effect on aerodynamic performance.
Innovation Solution
A fan blade design with tailored thickness and camber distributions, including a pre-compression region and axisymmetric airfoil sections, to improve bird impact capability while maintaining aerodynamic efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If ceramic matrix composites are used for fan blades or vanes, then weight is reduced and temperature resistance is improved, but bird impact resistance deteriorates
Solution Approach 1:
The patent applies local quality by modifying only the leading edge region of the fan blade or vane with a bird impact mitigation feature, while keeping the rest of the blade made of ceramic matrix composite material. This localized modification provides impact resistance where needed without compromising the overall weight and temperature resistance benefits of the CMC material throughout the entire blade structure.
2Object-affected harmful factors
If modifications are made to fan blades or vanes to mitigate bird impact damage, then bird impact resistance is improved, but aerodynamic performance deteriorates
Solution Approach 1:
The patent applies partial action by implementing a bird impact mitigation feature that modifies only a portion of the leading edge surface area. The feature is designed to provide adequate bird impact protection while minimizing the disruption to airflow over the blade surface, thereby maintaining acceptable aerodynamic performance.
Solution Approach 2:
The patent applies parameter changes by carefully controlling the geometric parameters of the bird impact mitigation feature, including its height, width, and curvature radius. These parameters are optimized to balance impact resistance with aerodynamic performance, ensuring the feature provides protection while minimizing negative effects on airflow characteristics.
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
The design enhances bird impact resistance while minimizing negative aerodynamic effects, ensuring high efficiency and performance of the fan blades.
Implementation Method 1
a pre-compression region is defined in the throat region ahead of the passage throat
Data Source
AI summary
A gas turbine engine is provided and includes a first fan blade including a suction surface, a second fan blade comprising a pressure surface and neighboring the first fan blade and a throat region interposed between the suction surface of the first fan blade and the pressure surface of the second fan blade. The throat region includes a passage throat located at a minimum distance between the pressure and suction surfaces. The first and second fan blades are configured such that a pre-compression region is defined in the throat region ahead of the passage throat. Each of the first and second fan blades includes a mean camber line defining a flattened suction surface.