Shaft-Coupled Turbine Compressor Cooling With Depressed Outlet Pressure
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Solution Overview
Problem
Conventional aircraft air conditioning systems do not effectively utilize the potential for increased cooling by depressing the turbine outlet pressure below ambient, leading to suboptimal cooling performance and requiring power sources, which limits their application in remote aircraft locations.
Innovation Solution
A unique configuration with a turbine and compressor mounted on the same shaft, where the turbine is upstream of the compressor, and a heat exchanger positioned between them, allowing ram air to create a vacuum and enhance cooling efficiency without the need for external power or air seals, resulting in increased cooling and reliability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If the turbine outlet pressure is not depressed below ambient pressure, then the system construction is simpler, but the cooling efficiency is reduced
Solution Approach 1:
The patent combines the turbine and compressor into a single integrated unit sharing a common shaft, eliminating the need for separate sealed enclosures and complex air sealing systems. This merging allows the turbine outlet to naturally depress below ambient pressure without requiring additional complexity, thereby achieving both improved cooling efficiency and simplified construction.
Solution Approach 2:
The system uses the pressure differential created by the turbine-compressor configuration to automatically draw ram air through the heat exchanger without requiring external power sources or complex control systems. The depressed turbine outlet pressure self-regulates the air flow, achieving efficient cooling while maintaining simple construction.
2Temperature
If air seals are used to maintain pressure differentials, then the system can operate with depressed turbine outlet pressure, but the reliability is reduced and manufacturing cost increases
Solution Approach 1:
The patent extracts and eliminates the air sealing system entirely from the design. By reconfiguring the turbine-compressor arrangement and accepting the depressed turbine outlet pressure, the system achieves effective cooling without requiring any air seals, thereby improving reliability and reducing manufacturing complexity.
3Adaptability or versatility
If external power sources are used, then the system can operate in various locations, but the adaptability to remote locations without power is reduced
Solution Approach 1:
The system is designed to be completely self-powered, using the ram air flow and pressure differentials generated during aircraft operation to drive the turbine-compressor unit. This eliminates all external power requirements, enabling installation in any remote location on the aircraft without electrical infrastructure.
4Temperature
If the turbine and compressor are mounted on the same shaft with heat exchanger between them, then the cooling efficiency increases, but the device complexity increases
Solution Approach 1:
The patent merges the turbine and compressor into a single integrated assembly sharing a common shaft, with the heat exchanger positioned between them. This consolidation reduces the overall number of separate components and eliminates the need for complex interconnections and sealing systems, achieving improved cooling efficiency while maintaining simple construction.
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 achieves greater cooling efficiency, eliminates the need for power sources, simplifies construction, and allows operation in remote aircraft locations, providing effective air conditioning across various flight conditions without the need for external power or complex sealing.
Implementation Method 1
The air supplied from the engine (engine bleed air) is typically cooled by passing it through a heat exchanger which uses ram air to remove the heat from the bleed air
Implementation Method 2
That high pressure air is then cooled as it passes through a second heat exchanger which also utilizes ram air to remove the heat of compression. The cooled high pressure air then enters the turbine, where it expands while performing work that powers the compressor rotor. As it expands and performs work, the temperature of the air is reduced
Implementation Method 3
That cooled air then enters the compressor, where it is pressurized to a higher level
Data Source
AI summary
An air conditioning apparatus that includes a turbine and a compressor with rotors mounted on and fixed to a common rotatable shaft with a heat exchanger located between the turbine and the compressor. The air conditioning apparatus turbine has an inlet that is connected to a source of air such as aircraft ram air the outlet from the turbine and is positioned to direct outlet air from the turbine to the heat exchanger. The compressor which is located adjacent to and downstream from the heat exchanger has an inlet that is positioned to receive air exiting from the heat exchanger. In one embodiment, no external power is necessary to obtain cooling of liquid coolant located within the heat exchanger that is integral with the air conditioning apparatus and another embodiment includes test equipment.