Adjustable Fan Inlets for Distortion-Tolerant Airflow Distribution
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Solution Overview
Problem
Gas turbine engines experience high distortion due to pressure gradients and swirl, leading to engine stall or undesirable aeromechanical behavior.
Innovation Solution
A duct system with multiple inlet ducts and an inlet flow regulation system that includes an inlet flow regulator and a control unit to mechanically adjust the shape of the inlet ducts, ensuring a uniform air flow distribution to the fan, managed by a control unit that receives inputs from sensors and adjusts the inlet flow regulator to mitigate differential pressures and flows.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If multiple inlet ducts are used to increase air intake capacity, then the air flow quantity increases, but the flow distribution becomes non-uniform causing distortion
Solution Approach 1:
The patent applies dynamics by making the inlet ducts adjustable through flow regulation means that can change the duct geometry in real-time. The inlet ducts transition from fixed structures to dynamic components that can adapt their shape and opening area based on operational requirements, allowing the system to maintain uniform flow distribution while maximizing air intake capacity.
Solution Approach 2:
The patent changes physical parameters of the inlet ducts by using flow regulation means that can modify the duct geometry, opening area, and shape. These parameter changes enable the system to adjust the flow characteristics of each inlet duct independently, ensuring uniform distribution across all inlet ducts while maintaining high overall air flow quantity.
2Device complexity
If the inlet duct geometry is fixed to simplify the structure, then the device complexity is reduced, but the ability to adapt to distortion patterns is limited
Solution Approach 1:
The patent transforms the fixed inlet duct geometry into a dynamic structure with adjustable components. The flow regulation means enable the ducts to change their shape and configuration in response to operational conditions, providing adaptability to distortion patterns while maintaining a relatively simple base structure that can be modified as needed.
Solution Approach 2:
The patent segments the inlet duct system into multiple independently controllable ducts, each with its own flow regulation means. This segmentation allows individual ducts to be adjusted separately to compensate for distortion patterns, providing versatility without requiring complete redesign of the entire inlet system.
3Stability of the object's composition
If flow regulation means are added to uniformize flow distribution, then the flow uniformity improves, but the device complexity increases
Solution Approach 1:
The patent designs the flow regulation means to serve multiple functions: they uniformize flow distribution, adapt to distortion patterns, and can be adjusted for different operational conditions. This multi-functionality reduces the need for separate components for each function, thereby limiting the increase in device complexity while achieving improved flow uniformity.
Solution Approach 2:
The patent incorporates sensors and control systems that provide feedback on flow distribution and distortion conditions. This feedback mechanism enables the flow regulation means to automatically adjust and maintain uniform flow distribution, reducing the need for complex manual control systems and minimizing overall device complexity.
Data Source
AI summary
An aircraft includes a duct system, a gas turbine engine, and an inlet flow regulation system. The duct system includes a main duct, a first inlet duct in fluid communication with the main duct, and a second inlet duct in fluid communication with the main duct. The inlet flow regulation system includes an inlet flow regulator configured to manage different flow characteristics of a flow of air entering the first and second inlet ducts to form a substantially uniform flow distribution through the main duct and into the gas turbine engine and a control unit in communication with the inlet flow regulator and configured to selectively move the inlet flow regulator.