Aviation Compressor Disturbance Compensation for Stall and Surge Stability
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Solution Overview
Problem
Existing aviation compressor stabilization control methods struggle to maintain stability under external disturbances, often leading to aerodynamic instability phenomena like rotating stall and surge, and are limited by model errors and conservative design strategies.
Innovation Solution
An active stabilization control method based on disturbance observation and compensation, which establishes partial differential models of the compressor, converts them to ordinary differential models using the Galerkin projection method, and designs sub-controllers to compensate for disturbances and model errors, ensuring simultaneous stabilization of rotating stall and surge.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a sufficient surge margin is maintained between the design operating point and the surge line, then the compressor can maintain stable operation under external disturbances, but the compressor performance deteriorates due to the over-conservative strategy
Solution Approach 1:
The patent implements active stabilization control using feedback mechanisms that continuously monitor compressor operating conditions and adjust control inputs in real-time. The controller uses state feedback from the compressor system to actively counteract disturbances and maintain stability, allowing operation closer to the surge line without sacrificing reliability. This dynamic feedback approach replaces the static conservative surge margin strategy, enabling both high performance and stability through continuous adaptation to changing conditions.
2Reliability
If the compressor operating point is kept far away from the surge line to ensure stability, then the compressor avoids aerodynamic instability phenomena, but the compressor performance is reduced
Solution Approach 1:
The patent transforms the static conservative operating strategy into a dynamic active control system. By implementing real-time stabilization control that adapts to changing operating conditions and disturbances, the system can safely operate closer to the surge line while maintaining stability. The dynamic nature of the control allows the compressor to exploit the full performance envelope without risking aerodynamic instability, thus resolving the trade-off between reliability and productivity.
3Reliability
If the compressor is subjected to external disturbances, then the compressor may experience rotating stall or surge, but maintaining stable operation requires complex control systems
Solution Approach 1:
The patent implements a self-service active stabilization control system where the controller autonomously monitors compressor state, detects disturbances, and applies appropriate control actions without external intervention. The system uses built-in sensing and actuation to self-regulate and maintain stability against rotating stall and surge. This self-service capability handles the complexity internally, providing robust disturbance rejection while keeping the overall system architecture relatively simple and manageable.
4Ease of manufacture
If simplified ordinary differential models are used instead of partial differential models, then mature control technologies can be applied, but model errors lead to controller failure in some operating conditions
Solution Approach 1:
The patent employs parameter changes by transforming the partial differential compressor models into ordinary differential models through coordinate transformations and variable substitutions. This transformation preserves the essential dynamic characteristics while making the system amenable to standard control design techniques. By carefully selecting transformation parameters and maintaining the physical meaning of variables, the approach achieves both ease of implementation and robustness across various operating conditions, resolving the contradiction between manufacturability and reliability.
Data Source
AI summary
The present invention belongs to the field of aviation compressor control, and relates to an aviation compressor active stabilization control method based on disturbance observation and compensation. Modeling errors and external disturbances of models used in design of a controller are observed, and sub-controllers are individually designed for state variables of interest to compensate for the disturbances, thus to simultaneously solve the problems of rotating stall and surge of an aviation compressor in a variety of complex situations. Partial differential model of the compressor is converted to an ordinary differential equation by Galerkin projection method, partial differential characteristics of the compressor are reserved in the form of disturbances during conversion, and an active stabilization controller of the aviation compressor is designed in combination with disturbance observation and compensation technology, thus to ensure that the models used in the design of the controller have higher accuracy, high robustness and high reliability.