Turboshaft Engine Icing Detection via Power Difference
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current methods for detecting icing conditions in aircraft turboshaft engines rely heavily on pilot observation and active monitoring, which can be inadequate for automatic detection, and existing systems are not effective in determining icing presence without human intervention.
Innovation Solution
A method and device that utilize a processor unit to calculate the power difference between real and theoretical engine power, combined with temperature thresholds, to automatically detect icing conditions by measuring torque and rotation speed, and trigger warnings when specific criteria are met.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If ice sensors are installed on the air inlet grid to detect icing conditions, then detection capability is improved, but the device complexity and difficulty of sensor placement increase
Solution Approach 1:
The patent replaces mechanical ice sensors with an indirect detection method using existing engine performance parameters (torque, power, temperature). Instead of physically sensing ice accumulation on the grid, the system detects icing conditions by monitoring deviations in engine performance that occur when ice obstructs the air inlet, thereby eliminating the need for complex sensor placement while maintaining detection capability
Solution Approach 2:
The patent uses engine performance parameters as intermediaries to detect icing conditions. Rather than directly sensing ice on the air inlet grid, the system measures torque, power, and temperature as intermediary indicators that reflect the presence of ice obstruction, simplifying the detection system while providing reliable icing condition identification
2Extent of automation
If pilot observation of windshield or external probes is used to detect icing, then no additional equipment is needed, but automation level and response time are reduced
Solution Approach 1:
The patent implements continuous automated feedback monitoring of engine performance parameters (torque, power, temperature) to detect icing conditions. The system continuously compares actual engine performance against expected performance, and when deviations indicate icing, it automatically triggers an alert, providing both automation and timely response without relying on pilot observation
Solution Approach 2:
The system uses the engine's own performance data to detect icing conditions affecting the engine. By monitoring how the engine performs under various conditions and identifying anomalies consistent with ice obstruction, the system enables the engine to essentially self-diagnose icing conditions, achieving automation without additional external sensing equipment
3Reliability
If temperature measurement alone is used to determine icing conditions, then device complexity is reduced, but measurement precision and reliability are insufficient
Solution Approach 1:
The patent merges multiple existing engine performance measurements (torque, power, temperature) into a unified icing detection system. By combining these parameters and analyzing their relationships, the system achieves reliable icing condition determination without adding separate dedicated sensors, thereby improving accuracy while maintaining simplicity
Solution Approach 2:
The patent monitors changes in engine performance parameters (torque, power, temperature) to detect icing conditions. Instead of relying on a single temperature threshold, the system detects deviations in the relationship between these parameters that occur when ice obstructs the air inlet, providing more reliable detection while using only existing measurement systems
Data Source
AI summary
A method of detecting that an aircraft is flying in icing conditions. A processor unit determines a real power developed by the turboshaft engine and a theoretical power that the engine can develop in theory, the theoretical power being determined using a theoretical model supplying a power as a function at least of a speed of rotation of a gas generator of the engine. The processor unit determines a difference between the real power and the theoretical power. The processor unit generates a warning to indicate the presence of icing conditions when the power difference is greater than a predetermined power threshold for a length of time longer than a time threshold, and when a temperature outside the aircraft lies between a low temperature threshold and a high temperature threshold.