Aircraft Radar Component Failure Detection
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Solution Overview
Problem
Existing systems for detecting mechanical failures in gas turbine engines, such as burst ducts and combustor burn-throughs, often fail to detect issues until they are substantial, leaving undetected conditions that can lead to engine damage.
Innovation Solution
A method and system utilizing radar sensing elements to transmit and detect radio waves, determining property values indicative of component characteristics like size, shape, and vibration, and employing artificial intelligence to identify changes indicative of mechanical failures, allowing for early and reliable detection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If traditional detection systems are used to monitor mechanical failures, then the system structure remains simple, but the detection precision is insufficient and failures are only detected when substantial
Solution Approach 1:
The patent replaces traditional mechanical or thermal detection systems with radar technology. The radar sensing element transmits electromagnetic waves and analyzes reflected signals to detect mechanical failures, substituting physical contact or thermal sensing methods with non-contact electromagnetic field interaction for enhanced precision without mechanical wear or thermal interference
Solution Approach 2:
The patent utilizes changes in radar signal parameters (amplitude, phase, frequency, time delay) caused by mechanical failures to detect component states. By monitoring parameter variations in the reflected radio waves, the system achieves high-precision detection of subtle mechanical changes that traditional systems cannot detect
2Reliability
If radar technology is used to detect mechanical failures, then the detection precision improves, but the device complexity increases
Solution Approach 1:
The radar sensing element serves multiple functions: it transmits radio waves, receives reflected signals, determines property values of components, and detects various types of mechanical failures (burst ducts, combustor burn-throughs, blade tip clearance changes). This multi-functionality reduces the need for separate detection systems for different failure modes, thereby limiting overall system complexity while maintaining high reliability
Solution Approach 2:
The patent introduces a control unit as an intermediary between the radar sensing element and the analysis system. This control unit processes radar signals, determines property values, and identifies mechanical failures, acting as a mediator that simplifies the interface between the complex radar technology and the monitoring system, making the overall system more manageable despite the advanced radar component
3Loss of time
If traditional detection methods are used, then the system is easier to operate, but the detection occurs only at substantial failure stages
Solution Approach 1:
The radar-based system performs preliminary detection of mechanical failures by continuously monitoring property values of engine components before substantial damage occurs. The system detects early-stage anomalies such as small duct breaches or initial combustor burn-throughs, enabling preventive action before failures become critical, thus reducing loss of time from failure onset to detection
Solution Approach 2:
The system implements continuous feedback by repeatedly transmitting radio waves, analyzing reflected signals, and comparing current property values with baseline values. This feedback mechanism automatically updates the detection status and alerts operators to developing failures, reducing the time to detect issues while maintaining ease of operation through automated monitoring rather than manual inspection
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
Enables the early detection of mechanical failures in gas turbine engines, preventing damage by identifying subtle changes in component properties, thereby enhancing the reliability of propulsion system design.
Implementation Method 1
providing a radar sensing element installed within a portion of the aircraft that is configured to transmit and detect radio waves
Implementation Method 2
detecting the waves reflected from the component
Implementation Method 3
If a Doppler radar is used, which is the case in embodiments, vibrations, and changes in the vibration frequency in a component may be monitored as well
Data Source
AI summary
A gas turbine engine for an aircraft that includes a nacelle, a fan, an engine core, a bypass duct extending between the engine core and the nacelle and guiding a bypass airflow through the bypass duct, and at least one non-structural strut extending in the radial direction within the bypass duct, wherein the non-structural strut includes an outside wall acting as a heat exchanger, and wherein the outside wall includes first transport means configured to transport in the outside wall at least one fluid to be cooled. It is provided that the non-structural strut further includes second transport means configured to transport a fluid to be heated, wherein the first transport means and the second transport means are configured such that the fluid to be heated is heated by the at least one fluid to be cooled and the at least one fluid to be cooled is cooled both by the bypass airflow and the fluid to be heated.