Turbocompressor Air Tap for Engine Efficiency
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Solution Overview
Problem
Existing environmental control systems for aircraft face inefficiencies due to the high temperature and pressure of higher pressure compressed air, which requires cooling and can decrease engine efficiency when diverted, and often necessitate the use of additional heat exchangers.
Innovation Solution
A gas turbine engine design incorporating a turbocompressor system with a higher pressure tap leading into the turbine section and a lower pressure tap leading into the compressor section of the turbocompressor, utilizing a double wall tube for leakage protection and a gearbox with gear reduction, allowing for efficient air distribution and temperature management without a separate heat exchanger.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If higher pressure compressed air is tapped from the compressor section, then the air can be used for aircraft environmental control, but the engine efficiency decreases due to diversion of compressed air
Solution Approach 1:
A turbocompressor is introduced as an intermediary device between the engine compressor and the environmental control system. The turbocompressor receives high-pressure air from the engine compressor, compresses it further, and delivers it to the environmental control system. This mediator allows the engine to maintain its operating efficiency while providing the required compressed air for environmental control through the turbocompressor's compression capability.
Solution Approach 2:
The air supply system is segmented into multiple independent sources: the engine compressor provides air for engine operation, while the turbocompressor provides additional compressed air for environmental control. This segmentation allows independent optimization of each subsystem, enabling the engine to operate at peak efficiency while the turbocompressor handles the environmental control air supply requirements.
2Quantity of substance
If higher pressure compressed air is tapped at high temperature, then the air is available for use, but additional cooling systems and heat exchangers are required
Solution Approach 1:
The turbocompressor acts as an intermediary that receives hot high-pressure air from the engine compressor and delivers compressed air to the environmental control system. The turbocompressor's compression process and subsequent cooling arrangement provide the necessary temperature management, eliminating or reducing the need for separate heat exchangers and cooling systems that would otherwise be required to handle the high-temperature air.
3Reliability
If a double wall tube is used for the higher pressure tap, then leakage protection is improved, but the device complexity increases
Solution Approach 1:
The double wall tube structure implements the nesting principle by placing one tube inside another. The inner tube carries the high-pressure air flow, while the outer tube provides a protective barrier and containment structure. This nested configuration provides redundant leakage protection where the outer tube can contain any leaks from the inner tube, enhancing reliability without requiring complex external monitoring or containment 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 configuration enhances engine efficiency by reducing the need for additional cooling systems and minimizing the diversion of high-pressure air, while ensuring safe operation by detecting potential leaks and controlling airflow to maintain optimal temperature and pressure for aircraft use.
Implementation Method 1
air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor
Implementation Method 2
the compressor section compresses air and delivers air into a combustion section
Implementation Method 3
The tap includes a double wall configuration above the plane for preventing leakage from impinging on portions of the pylon
Data Source
AI summary
A disclosed gas turbine engine includes a fan section delivering air into a compressor section. An environmental control system includes a higher pressure tap at a higher pressure location in the compressor section, and a lower pressure tap at a lower pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use.