Pneumatic Heated Gas Probe for Aircraft Engine Pressure Measurement
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Solution Overview
Problem
Existing instrumentation systems for aircraft gas turbine engines face challenges with icing and fluid ingestion, which hinder accurate measurement of fluid parameters, and the introduction of electrical heating systems adds complexity and requires extensive wiring.
Innovation Solution
A measurement system for aircraft gas turbine engines that includes a probe with heated-gas channels and a heated-gas source, which supplies a heated gas flow to the probe to prevent icing and fluid ingestion, while minimizing electrical complexity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conductive or inductive heating systems are introduced to prevent icing, then the reliability of sensor measurements is improved, but the device complexity increases due to additional electrical wiring and shielding requirements
Solution Approach 1:
The patent replaces electrical heating systems with a pneumatic heating system that uses heated gas flow through channels in the probe structure. This substitution eliminates the need for electrical wiring, conductive/inductive heating elements, and associated shielding, thereby reducing device complexity while maintaining the anti-icing function that ensures measurement reliability
Solution Approach 2:
The patent utilizes pneumatic principles by introducing heated gas flow through channels formed within the probe body and probe conduits. The heated gas serves both to prevent icing on sensor surfaces and to provide a controlled flow environment, replacing the need for electrical heating mechanisms and reducing overall system complexity
2Reliability
If physical shielding is added to prevent fluid ingestion, then the reliability of sensor measurements is improved, but the device complexity increases
Solution Approach 1:
The patent replaces physical shielding structures with a controlled heated gas flow system that actively prevents fluid ingestion. The heated gas flow creates a protective barrier around sensor inlet ports through pneumatic pressure and flow dynamics, eliminating the need for complex physical shields while maintaining measurement reliability
3Reliability
If electrical wiring is routed through extensive portions of the gas turbine engine, then the reliability of heating systems is improved, but the ease of manufacture decreases due to installation complexity
Solution Approach 1:
The patent eliminates electrical wiring entirely by substituting it with a pneumatic heating system that delivers heated gas through channels integrated into the probe structure. This substitution dramatically simplifies manufacturing and installation, as the probe can be assembled with pre-formed channels and connected to a heated gas source without requiring extensive wiring routing through the engine
Solution Approach 2:
The heated gas flow serves multiple functions simultaneously: it prevents icing on sensor surfaces, prevents fluid ingestion at sensor ports, and provides a controlled environment for measurements. This multi-functionality eliminates the need for separate electrical heating systems and complex wiring, simplifying both manufacturing and installation while maintaining reliability
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 system effectively prevents icing and fluid ingestion, ensuring accurate fluid parameter measurements without the need for extensive electrical wiring, thus reducing complexity and improving reliability.
Implementation Method 1
The heated-gas source is configured to supply a heated gas flow to one or both of: the plurality of sensor inlet ports via the plurality of probe conduits and an interior of the probe body outside of the plurality of probe conduits
Data Source
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AI summary
A measurement system for an aircraft gas turbine engine includes a probe (202) and a heated-gas source (228) in fluid communication with the pressure probe. The probe includes a probe body (204) defining an internal cavity (208) of the probe. The probe further includes a plurality of sensor inlet ports (210) extending through the probe body and configured to receive a sensed fluid flow. The probe further includes a plurality of probe conduits (222). Each probe conduit of the plurality of probe conduits is coupled to a respective sensor inlet port of the plurality of sensor inlet ports and extending from the respective sensor inlet port to an exterior of the probe body. The heated-gas source is configured to supply a heated gas flow to one or both of: the plurality of sensor inlet ports via the plurality of probe conduits and an interior of the probe body outside of the plurality of probe conduits.