Distributed Electric Fan Array for Turbofan Distortion Tolerance
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Solution Overview
Problem
Gas turbine engines experience high distortion in the form of pressure gradients and swirl, leading to engine stall and undesirable aeromechanical behavior, which existing mitigation systems are unable to effectively address.
Innovation Solution
The implementation of an auxiliary fan system with a plurality of electric fans and a control unit that varies the rotation speed of each fan in response to pressure differentials and preprogrammed aircraft maneuvers to minimize pressure and swirl distortions, allowing for individual control of airflow around the circumference of the engine.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a single primary fan is used to provide thrust, then the engine structure is simple, but the engine cannot effectively mitigate pressure and swirl distortions during flight maneuvers
Solution Approach 1:
The fan system is segmented into multiple independent electric fans arranged in an array, allowing each fan to be controlled independently. This segmentation enables the system to address distortion issues by adjusting individual fan speeds and orientations, transforming a single-point control system into a distributed control system that can mitigate pressure and swirl distortions effectively.
Solution Approach 2:
The system transitions from a static fan configuration to a dynamic one where each electric fan can vary its rotation speed and orientation independently. The control unit dynamically adjusts fan parameters in real-time based on detected distortion conditions, enabling the fan array to adapt to changing flight conditions and distortion patterns.
2Reliability
If existing mitigation systems are used, then the engine structure remains relatively simple, but they are unable to effectively address pressure and swirl distortions
Solution Approach 1:
The system incorporates sensors that continuously monitor pressure and swirl distortions in the airflow. The control unit receives real-time feedback from these sensors and adjusts the rotation speeds and orientations of the electric fans accordingly. This closed-loop feedback mechanism enables effective distortion mitigation by continuously adapting fan operation to actual distortion conditions.
Solution Approach 2:
The system changes operational parameters (rotation speed and orientation) of the electric fans to mitigate distortions. By varying these parameters dynamically, the system can counteract pressure and swirl distortions, improving stability during flight maneuvers while maintaining effective distortion mitigation capability.
3Reliability
If multiple electric fans are added to mitigate distortions, then distortion mitigation capability improves, but the device complexity increases
Solution Approach 1:
The multiple electric fans in the auxiliary fan array serve multiple functions: they mitigate pressure and swirl distortions, provide additional thrust when needed, and can operate independently or in coordination with the primary fan. This multi-functionality justifies the increased device complexity by delivering versatile performance benefits beyond simple distortion mitigation.
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
This solution effectively mitigates pressure and swirl distortions, enabling the gas turbine engine to maintain performance and stability during various flight maneuvers by dynamically adjusting fan speeds and orientations, thereby preventing engine stall and optimizing aeromechanical behavior.
Implementation Method 1
The plurality of electric fans may each be configured to rotate about a fan axis
Data Source
AI summary
A gas turbine engine comprises a primary fan and an engine core. The primary fan is mounted for rotation about an axis of the gas turbine engine to provide thrust. The engine core is coupled to the primary fan and configured to drive the primary fan about the axis to cause the fan to push air to provide thrust for the gas turbine engine.