Integrated Turbocompressor for Aircraft Environmental Control
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Solution Overview
Problem
Environmental control systems for aircraft face inefficiencies due to the need for additional conduits and reduced engine efficiency when diverting airflow from the core flowpath for cooling and buffer systems, which increases structural complexity and reduces overall performance.
Innovation Solution
An environmental control system that utilizes a turbocompressor with a compressor section driven by a turbine, drawing air from both high and low pressure locations, and includes a buffer system that provides pressurized air to bearing compartments without additional engine openings, using a heat exchanger to condition airflow for temperature and pressure requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If airflow is diverted from core flowpath for cooling and buffer systems, then cooling and buffer air supply is improved, but structural complexity increases and engine efficiency decreases
Solution Approach 1:
The patent combines the environmental control system and buffer air system into a single integrated turbocompressor unit. The compressor section provides compressed air to both the environmental control system (for cooling) and the buffer air system (for bearing compartments) through a unified structure, eliminating the need for separate conduits and engine openings, thereby reducing structural complexity while maintaining improved cooling air supply
Solution Approach 2:
The turbocompressor is designed as a multi-functional device that simultaneously serves multiple purposes: it provides compressed air for environmental control (cooling), buffer air for engine bearings, and maintains engine efficiency. This universal device replaces multiple separate systems, reducing overall structural complexity while achieving improved cooling and buffer air supply
2Quantity of substance
If additional conduits are added for buffer system airflow, then buffer air supply is improved, but structural complexity increases
Solution Approach 1:
The patent merges the buffer air supply function into the integrated turbocompressor structure. The compressor section directly provides compressed buffer air to bearing compartments through the unified device structure, eliminating the need for additional separate conduits and engine openings, thereby maintaining improved buffer air supply while reducing structural complexity
3Quantity of substance
If engine taps are added for airflow diversion, then air supply for systems is improved, but engine efficiency decreases
Solution Approach 1:
The integrated turbocompressor serves itself by utilizing engine exhaust gas energy to drive the turbine, which in turn drives the compressor section to provide compressed air for environmental control and buffer systems. This self-service mechanism reduces the need for additional engine taps and minimizes energy loss by efficiently utilizing waste exhaust energy
4Stress or pressure
If high pressure air is used directly from compressor, then pressure requirement is met, but temperature is too high for aircraft systems
Solution Approach 1:
The patent extracts high pressure air from the compressor section of the integrated turbocompressor and directs it through a heat exchanger that utilizes engine exhaust gas to cool the compressed air. This separation of compression and cooling functions maintains the required high pressure while reducing the temperature to suitable levels for aircraft environmental control systems
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
This solution reduces structural complexity and maintains engine efficiency by eliminating the need for additional engine taps and providing conditioned airflow for both high and low pressure applications within the aircraft, enhancing power density and operational performance.
Implementation Method 1
An intercooler or heat exchanger is therefore required
Data Source
Figure 1
Figure 2~3
Figure 4~5
AI summary
An environmental control system (62) for an aircraft includes a higher pressure tap (72) to be associated with a higher compression location and a lower pressure tap (74) to be associated with a lower pressure location in the main compressor section associated with the aircraft engine. The lower pressure tap (74) communicates to a first passage leading to a downstream outlet, and has a second passage leading into a compressor section (80) of a turbocompressor (78). The higher pressure tap (72) leads into a turbine section (82) of the turbocompressor (78) such that air in the higher pressure tap (72) drives the turbine section (82) to in turn drive the compressor section (80) of the turbocompressor (78). A turbine outlet (86) receives airflow exhausted from the turbine section (82). A compressor outlet (84) receives airflow exhausted from the compressor section (80). A combined outlet (90) receives airflow from the turbine outlet (86) and the compressor outlet (84) intermixing airflow and passing the mixed airflow downstream to be delivered to an aircraft. A buffer air outlet (112) communicates airflow to an engine buffer air system (66) and receives airflow supplied to the turbocompressor (78).