Aircraft Thrust Reverser Locking System Injection Cooling
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Solution Overview
Problem
Thrust reverser locking systems in aircraft engines are exposed to high temperatures, exceeding their operational limits, which can lead to performance degradation and failure, especially during high-ambient temperatures.
Innovation Solution
An injection cooling system is implemented, which fluidly couples the thrust reverser locking system to a pre-cooler, using bleed air from the turbine engine to cool the system, and an air supply duct to transfer hot ambient air from the locking system to the pre-cooler, effectively reducing the temperature within operational parameters.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If the thrust reverser locking system is exposed to high ambient temperatures, then the system operates in realistic environmental conditions, but the temperature exceeds operational limits causing performance degradation and failure
Solution Approach 1:
A cooling system acts as an intermediary between the hot ambient environment and the thrust reverser locking system. The cooling system includes a cooling air source, a cooling air passage, and a cooling air outlet that directs cooled air to the locking system, thereby mediating the thermal interaction and maintaining reliable operation.
Solution Approach 2:
The invention changes the temperature parameter of the ambient air by introducing a cooling mechanism. The cooling system modifies the thermal state of the air before it reaches the thrust reverser locking system, transforming the high-temperature environment into a suitable operating condition.
2Temperature
If a cooling system is added to reduce temperature, then the temperature is maintained within operational limits, but the device complexity increases
Solution Approach 1:
The cooling system is designed to serve multiple functions: it cools the thrust reverser locking system, utilizes available ambient air resources, and integrates with the existing engine structure. The cooling air passage and outlet are positioned to efficiently deliver cooled air while maintaining structural integrity.
Solution Approach 2:
The cooling system utilizes ambient air that is naturally available in the environment, eliminating the need for additional active cooling components. The system passively draws in and directs cooling air, reducing complexity while maintaining effective temperature control.
3Temperature
If cooling air is supplied to the thrust reverser locking system, then the temperature is reduced, but reverse airflow may cause ineffective cooling
Solution Approach 1:
Instead of trying to prevent reverse airflow, the invention positions the cooling air outlet and passage to utilize the natural reverse airflow pattern. The cooling system is configured so that the outlet directs air in a direction that aligns with the expected reverse flow, ensuring effective cooling regardless of flow direction.
Solution Approach 2:
The cooling system design incorporates feedback by positioning the outlet and passage to respond to the natural airflow patterns in the engine environment. The configuration ensures that cooling air is delivered effectively under various operating conditions, maintaining temperature control through adaptive positioning.
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 efficiently cools the thrust reverser locking system, preventing performance degradation and ensuring reliable operation even at high temperatures, with minimal weight addition and no risk of reverse airflow, while meeting clearance requirements.
Implementation Method 1
a pre-cooler fluidly coupled to the at least one compressor of the turbine engine to bleed air from the at least one compressor and cool the bleed air
Implementation Method 2
an injection cooling system fluidly coupled to the thrust reverser locking system and the pre-cooler and configured to transfer hot ambient air from the thrust reverser locking system to the pre-cooler
Data Source
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AI summary
An aircraft with aturbofan engine assembly having at least one compressor, a nacelle surrounding the turbine engine and defining an annular bypass duct between the nacelle and the turbine engine, a thrust reverser having at least one moveable control surface, a thrust reverser locking system configured to selectively lock the thrust reverserand an injection cooling system