Aircraft Engine Fuel Flow Regulation Using Thrust Feedback
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Solution Overview
Problem
Existing aircraft engine control methods optimize fuel flow regulation based on average engine models, neglecting individual engine variations due to aging and manufacturing tolerances, leading to uncertainties in engine speed and thrust relationships, which can result in suboptimal energy consumption and wear.
Innovation Solution
A device that calculates a fuel flow rate set value based on both the pilot's thrust set value and actual engine thrust measurement, using a comparator to adjust the fuel flow rate and engine speed set values, allowing for real-time or isolated thrust measurements to refine engine control, thereby accounting for engine-specific wear and dispersion factors.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a general engine model is used for fuel flow regulation, then the regulation is optimized for the engine family, but it is not optimized for each individual engine due to variations from aging and manufacturing tolerances
Solution Approach 1:
The system continuously measures actual engine thrust and compares it with the target thrust value. Based on this feedback, the controller adjusts the fuel flow rate set value to compensate for deviations caused by engine variations, aging, and manufacturing tolerances. This closed-loop feedback mechanism enables the system to adapt to individual engine characteristics while maintaining family-wide optimization.
Solution Approach 2:
The system dynamically adjusts the fuel flow rate set value based on the difference between actual and target thrust measurements. By changing the fuel flow parameter in response to measured thrust deviations, the system compensates for engine-specific variations and maintains optimal performance for each individual engine while preserving the general model's effectiveness.
2Measurement precision
If the model is modified to account for wear parameters and engine dispersions, then individual engine optimization is achieved, but the complexity of the model increases significantly
Solution Approach 1:
Instead of incorporating complex wear parameters and dispersion models into the engine model, the system extracts the actual thrust measurement from the physical engine operation. This measured thrust value directly reflects the engine's actual state, eliminating the need for complex predictive models while achieving individual engine optimization.
Solution Approach 2:
The engine system uses its own actual thrust measurement to self-correct and optimize its performance. By measuring its own thrust output and comparing it with the target value, the system automatically adjusts fuel flow without requiring external complex modeling or prediction of wear and dispersion effects.
3Loss of energy
If finer regulation of the engine is implemented, then energy consumption and wear are reduced, but the system becomes more sensitive to measurement uncertainties and measurement losses
Solution Approach 1:
The system incorporates a minimum fuel flow rate set value that prevents excessive reduction of fuel flow. This cushioning mechanism ensures that even when measurement uncertainties or temporary measurement losses occur, the fuel flow remains within safe operational limits, maintaining system robustness while enabling finer regulation to reduce energy consumption and wear.
Data Source
AI summary
A device for regulating the flow rate of fuel supplied to an aircraft engine, configured to produce a fuel flow rate set value according to a thrust set value supplied by a gas control lever and a measurement of actual thrust of the engine. It extends to a control system including the regulation device and a device for measuring the actual thrust of the engine, to an engine equipped with such a control system, to a regulation method and to a computer program for implementing the method.