Aircraft Environmental Control Turbocompressor Airflow Management
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Solution Overview
Problem
Gas turbine engines face inefficiencies due to high-pressure airflow diversion for aircraft environmental control systems, which increases engine temperature and reduces overall efficiency, and existing cooling solutions require additional space and weight for rare operating conditions.
Innovation Solution
A diverter valve and control valves are implemented to manage airflow based on temperature and cooling capacity, allowing for efficient use of high and low-pressure air, with a heat exchanger and buffer air passage to optimize airflow distribution and reduce engine load.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stress or pressure
If high pressure air is tapped from the higher pressure compressor location for aircraft systems, then the air pressure requirement is met, but the engine efficiency deteriorates due to diverting compressed air from core flowpath
Solution Approach 1:
The system segments the air supply into two separate sources: high-pressure air from the higher pressure compressor location and low-pressure air from the lower pressure location. This allows selective use of each source based on system needs, optimizing both pressure delivery and engine efficiency by avoiding unnecessary diversion of high-pressure core flow air.
Solution Approach 2:
The system changes the parameters of the air supply by using a turbocompressor to compress low-pressure air to the required pressure level. This alternative approach allows meeting pressure requirements without diverting high-pressure air from the core flowpath, thereby maintaining engine efficiency while achieving the desired air pressure for aircraft systems.
2Stress or pressure
If high pressure air is tapped from the higher pressure compressor location, then the air pressure requirement is met, but the air temperature becomes higher than needed requiring additional cooling
Solution Approach 1:
The system segments the air supply sources and selectively uses low-pressure air from the lower pressure location, which has more suitable temperature characteristics. This avoids the temperature penalty associated with tapping high-pressure air from the higher pressure compressor location while still meeting pressure requirements through turbocompressor operation.
Solution Approach 2:
The turbocompressor acts as an intermediary device that takes low-pressure, temperature-appropriate air from the lower pressure location and compresses it to the required pressure level. This intermediary process delivers both the necessary pressure and maintains more favorable temperature characteristics compared to direct high-pressure air extraction.
3Temperature
If a heat exchanger is added to cool the high pressure air, then the air temperature is reduced to acceptable levels, but the system complexity and weight increase
Solution Approach 1:
The system extracts and utilizes the low-pressure air stream from the lower pressure location, which inherently has more suitable temperature characteristics. By taking out this alternative air source and processing it through the turbocompressor, the system avoids the need for additional heat exchanger equipment that would be required if high-pressure air were used.
4Reliability
If excessive cooling capacity is provided for rare operating conditions, then temperature control is ensured under all conditions, but the system weight and size increase
Solution Approach 1:
The system dynamically adapts to different operating conditions by using control valves that selectively direct air from either the high-pressure or low-pressure locations based on real-time system needs. This dynamic operation allows the system to maintain reliable temperature and pressure control without requiring excessive cooling capacity designed for rare conditions, thereby reducing overall system weight.
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 enhances engine efficiency by optimizing airflow distribution, maintaining desired temperatures and pressures for aircraft systems while minimizing the need for excessive cooling capacity and reducing engine load, thus improving overall system performance.
Implementation Method 1
a heat exchanger within the common conduit downstream of the second control valve to cool the airflow through the common conduit
Implementation Method 2
The lower pressure airflow is intermixed with the higher pressure airflow in a common conduit to form intermixed airflow
Data Source
Figure 1
Figure 2~3
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 having 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 diverter valve (88) controls airflow from the turbine outlet (86) into the combined outlet (90) for controlling a temperature of airflow in the combined outlet (90).