Passive RF Pressure Sensor for Aircraft Engine Fan Blades
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Solution Overview
Problem
Existing pressure sensors used in aircraft engines face challenges in operating effectively at elevated temperatures, with internal electronics failing to function and optical-based sensors being expensive and difficult to package, limiting their placement.
Innovation Solution
A pressure sensor assembly comprising receive and transmit antenna arrays operating at different frequencies, coupled with a diode to generate a difference frequency signal, and integrated into a substrate with cavities and vent channels, allowing for wireless operation and robust temperature resistance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If internal electronics are used in pressure sensors, then signal processing capability is improved, but temperature resistance deteriorates
Solution Approach 1:
The patent extracts the electronics from the sensor assembly by using a wireless architecture where the sensor is a simple passive RF tag that receives RF energy and modulates its response based on pressure, while all signal processing is performed by an external interrogator. This separation allows the sensor to operate in high-temperature environments without internal electronics.
Solution Approach 2:
The patent replaces electronic signal processing with electromagnetic field-based communication. Instead of using electronic circuits to process signals, the system uses RF energy transfer and electromagnetic modulation, allowing the sensor to be purely passive and temperature-resistant while still achieving sophisticated signal processing externally.
2Temperature
If optical-based microphones are used, then temperature resistance is improved, but cost and packaging difficulty increase
Solution Approach 1:
The patent uses a simple, inexpensive passive RF tag design that can be easily manufactured and packaged. Instead of complex optical-based systems, the sensor is a simple resonant structure that can be made from conventional materials and assembled using standard techniques, significantly reducing packaging complexity and cost.
Solution Approach 2:
The patent replaces optical-based detection with electromagnetic RF-based detection. The sensor uses RF resonance and modulation principles rather than optical components, eliminating the need for complex optical packaging and alignment procedures while maintaining temperature resistance.
3Temperature
If optical-based microphones are used, then temperature resistance is improved, but placement flexibility deteriorates
Solution Approach 1:
The patent creates a universal sensor design that can be placed on various surfaces and integrated into different engine components. The passive RF tag architecture with simple resonant structure can be mounted on fan blades, casings, or any surface where pressure needs to be measured, providing maximum placement flexibility without the constraints of optical fiber routing.
Solution Approach 2:
The patent replaces optical fiber-based systems with wireless RF-based communication. This eliminates the need for physical fiber connections and routing, allowing the sensor to be placed in locations that would be impossible or extremely difficult to access with optical systems, thereby maximizing placement flexibility.
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
The solution enables efficient and cost-effective pressure sensing within aircraft engines, capable of withstanding high temperatures and harsh environments, while minimizing power loss and maintaining accuracy.
Implementation Method 1
a diode configured to receive the first signal at the first frequency and the second signal at the second frequency and output a third signal at a third frequency that is a difference between the first frequency and the second frequency
Implementation Method 2
a first receive antenna array configured to receive a first signal at a first frequency, and a second receive antenna array configured to receive a second signal at a second frequency
Data Source
AI summary
A pressure sensing system and method for an engine of an aircraft include a transceiver assembly coupled to a portion of the engine, and a pressure sensor assembly coupled to a fan blade of the engine. The transceiver assembly is configured to transmit a first signal at a first frequency and a second signal at a second frequency that differs from the first frequency. The pressure sensor assembly is configured to receive the first signal and the second signal and transmit a third signal at a third frequency that is a difference between the first frequency of the first signal and the second frequency of the second signal. The transceiver assembly is configured to receive the third signal at the third frequency. A pressure in relation to the engine is determined based on the third signal.