Aero-Engine Start Control Using ADRC and N-Dot Acceleration Feedback
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing aero-engine starting control methods face challenges in ensuring time consistency and high reliability, with traditional open-loop control leading to issues like overtemperature and suspension, while closed-loop PI control has long response times and limited practicality.
Innovation Solution
A control design method combining an active disturbance rejection controller (ADRC) with a competitive particle swarm optimization (CSO) algorithm to optimize the fuel-air ratio, ensuring rapid and consistent engine acceleration without surging or overtemperature.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If traditional open-loop fuel supply adjustment scheme is used, then the control system is simple, but starting overtemperature or suspension occurs and starting performance is inconsistent
Solution Approach 1:
The patent implements closed-loop feedback control by using rotor acceleration as feedback signal to adjust fuel supply in real-time. The control system continuously monitors the actual acceleration and compares it with the target acceleration, then adjusts the fuel supply rate accordingly to maintain consistent starting performance across different engines and life stages.
2Reliability
If closed-loop PI control strategy is used, then acceleration performance consistency is improved, but response time becomes long
Solution Approach 1:
The patent changes the control parameter from traditional speed-based control to rotor acceleration-based control (N-dot control). By using acceleration as the control variable and implementing closed-loop feedback, the system achieves both fast response and consistent acceleration performance across different engines and operational conditions.
3Productivity
If fuel supply rate is increased to shorten starting time, then productivity improves, but overtemperature and surging occur
Solution Approach 1:
The control system uses rotor acceleration feedback to dynamically adjust fuel supply rate. When acceleration exceeds the target rate, the system automatically reduces fuel supply to prevent overtemperature and surging. When acceleration is below target, it increases fuel supply to maintain fast starting performance, thus achieving both high productivity and safety.
Data Source
AI summary
The present invention provides a quick response control design method for an aero-engine starting process and belongs to the field of engine control. With an N-dot control plan, an intelligent optimization algorithm is used to optimize an acceleration target curve, then a controller is designed based on an active disturbance rejection control theory, and finally, the time of the engine starting process is minimized to complete quick response. The present invention can solve the problem that a traditional control method is difficult to ensure time consistency and has low reliability for the transient state of an aero-engine, is a control design method for quick response to the transient state of an aero-engine based on active disturbance rejection control (ADRC) under the N-dot control plan, and can shorten the transient state adjusting time on the premise of achieving stable operation of the aero-engine.