Gas Turbine Inlet Icing Detection Using Temperature Differential
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Solution Overview
Problem
Gas turbine engines face challenges in accurately detecting icing conditions, which can lead to reduced performance and potential damage from accumulated ice, despite existing anti-icing systems that may impose operational limitations and efficiency reductions.
Innovation Solution
A system using temperature sensors at upstream and downstream points in the engine inlet to measure temperature differentials, correlated with atmospheric and operational conditions, to determine the likelihood of icing and trigger corrective actions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If anti-icing systems are continuously activated to prevent ice accumulation, then reliability is improved, but loss of energy increases and productivity decreases
Solution Approach 1:
The system performs preliminary detection of icing conditions by measuring temperature differentials between upstream and downstream points in the inlet airflow path. By identifying icing conditions before significant ice accumulation occurs, the system can activate anti-icing measures only when necessary, rather than continuously, thus maintaining reliability while reducing energy loss and preserving engine efficiency
Solution Approach 2:
The control system continuously monitors temperature differentials between upstream and downstream temperature sensors in the inlet airflow path. When the differential exceeds a threshold indicating icing conditions, the system activates anti-icing measures. This feedback mechanism ensures anti-icing systems operate only when needed, improving reliability while minimizing energy consumption and maintaining productivity
2Measurement precision
If temperature sensors are positioned to accurately detect icing conditions, then measurement precision is improved, but device complexity increases
Solution Approach 1:
The system uses the inlet airflow path itself as an intermediary medium to detect icing conditions. By measuring temperature differentials between upstream and downstream points in the airflow path, the system leverages the airflow as a carrier of thermal information, achieving accurate icing detection without requiring complex sensor arrays or sophisticated measurement systems
Solution Approach 2:
The inlet airflow path is segmented into upstream and downstream measurement zones with separate temperature sensors. This segmentation allows the system to measure temperature differentials across distinct regions, improving measurement precision for icing detection while keeping each sensor simple and the overall device complexity manageable
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 precise identification of icing conditions, allowing optimal engine operation and minimizing risks by activating anti-icing measures only when necessary, thus maintaining efficiency.
Implementation Method 1
a first temperature sensor for sensing a first temperature of the aircraft fluid at a first upstream point
Implementation Method 2
a second temperature sensor for sensing a second temperature of the aircraft fluid at a second downstream point where the aircraft fluid has been exposed to the inlet air
Implementation Method 3
the aircraft fluid has been exposed to the inlet air for a period of time
Data Source
Figure 1
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Figure 5
AI summary
A gas turbine engine (20) includes a propulsor for providing air into a core engine housing and propulsion air radially outwardly of the core engine housing. The core engine housing surrounds a compressor section. A combustor is positioned downstream of the compressor section and a turbine section is positioned downstream of the combustor. An aircraft fluid moves within an inlet (32) to the gas turbine engine (20), and is exposed to inlet air (C) at the inlet (32). There is a first temperature sensor (56) for sensing a first temperature of the aircraft at a first upstream point and a second temperature sensor (54) for sensing a second temperature of the aircraft fluid at a second downstream point where the aircraft fluid has been exposed to the inlet air (C) for a period of time. A control (100) determines a temperature differential between first and second temperatures sensed by the first and second temperature sensors (56, 54). The temperature differential is associated with a likelihood that an icing condition will occur, and the control (100) is programmed to take a corrective action should an icing condition be identified.