Morphing Fan Inlet Guide Vanes for Non-Uniform Airflow Control
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Solution Overview
Problem
Existing gas turbine engine vanes lack the ability to dynamically adjust their shape in response to varying operating conditions, leading to suboptimal air direction and efficiency.
Innovation Solution
A vane system with a synchronization ring, bell-crank mechanism, and morphable airfoil structure that allows individual segments to pivot and change shape independently, enabling non-axisymmetric configurations to adapt to varying inlet conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If variable vanes are provided with an actuator to deflect a monolithic flap, then the fan blade incident angle can be changed, but the angular change is uniform across the span which limits adaptability to non-uniform inlet conditions
Solution Approach 1:
The monolithic flap is divided into multiple independent segments along the span of the vane. Each segment can be actuated independently by its own actuator, allowing different angular changes at different span locations. This segmentation enables the vane to adapt to non-uniform inlet conditions while maintaining a manageable structural complexity through modular design.
Solution Approach 2:
The vane structure transitions from a static monolithic flap to a dynamic segmented configuration where each segment can change its angle independently in real-time. This dynamic capability allows the system to adapt to varying operating conditions and non-uniform inlet conditions, resolving the contradiction between adaptability and complexity.
2Adaptability or versatility
If a monolithic flap is used to change the trailing edge angle, then the structure is simple, but it cannot adapt to non-uniform inlet conditions across different span locations
Solution Approach 1:
The flap is segmented into multiple independently actuable sections along the span. Each segment can be manufactured as a separate component with standardized interfaces, making the manufacturing process more manageable despite the increased functional complexity. This segmentation enables adaptation to non-uniform inlet conditions while maintaining ease of manufacture through modular assembly.
Solution Approach 2:
Each segment of the flap can have locally optimized characteristics and actuation mechanisms tailored to specific inlet conditions at different span locations. This local quality approach allows the vane to address non-uniform inlet conditions effectively while using standardized manufacturing techniques for each segment, balancing adaptability with manufacturing simplicity.
3Productivity
If variable vanes deflect the trailing edge uniformly, then the actuation mechanism is simple, but air direction optimization is limited under varying operating conditions
Solution Approach 1:
The actuation system is divided into multiple independent actuators, each controlling a specific segment of the flap. This segmentation allows each actuator to be relatively simple in design while collectively providing sophisticated air direction control. The modular actuation system improves productivity by enabling precise optimization of air direction for each span location without requiring a monolithic complex actuation mechanism.
Solution Approach 2:
The actuation system transitions from uniform static deflection to dynamic independent control of each segment. This dynamic capability allows the system to optimize air direction efficiency for varying operating conditions and non-uniform inlet conditions, resolving the contradiction between productivity and device complexity through real-time adaptive control.
Data Source
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AI summary
A gas turbine engine (10) includes a fan section (12), a compressor section (14), and a turbine section (18). The fan section (12) has a plurality of vane assemblies (64) spaced circumferentially about an engine axis (A) and each including an airfoil (66) extending between a leading edge (66a) and a trailing edge (66b), a control rod (68) extending through the airfoil (66), and a mechanism driven by the control rod (68) to change the shape of the airfoil (66).