Mixed-Flow Turbine Pressurization for Supersonic Thermal Loads
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Solution Overview
Problem
Existing nonintegrated pressurization systems in vehicles, such as aircraft, face inefficiencies due to high ram air temperatures at supersonic speeds, which hinder effective heat removal from loads.
Innovation Solution
A mixed-flow turbine system is integrated into the pressurization system, allowing for parallel inlet configurations and energy extraction from both compressor and turbine, combined with a cooling heat exchanger to manage thermal loads efficiently.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If ram air is used for cooling at supersonic speeds, then the cooling capacity is reduced due to high temperature, but using alternative cooling methods increases system weight and complexity
Solution Approach 1:
The patent combines the compressor and turbine into a single integrated pressurization system with shared housing and coupled rotors, merging previously separate cooling functions into one unified device that handles both compression and expansion processes
Solution Approach 2:
The integrated pressurization system performs multiple functions simultaneously: compressing air for pressurization, expanding air for cooling, and managing thermal loads, replacing the need for separate dedicated cooling systems
2Temperature
If separate pressurization systems are used for different regions, then temperature control is improved, but system complexity and power requirements increase
Solution Approach 1:
The system provides differentiated temperature control to various regions (cabin areas and galley chillers) through a single integrated pressurization system, segmenting the thermal output to serve multiple zones with different requirements
Solution Approach 2:
The integrated pressurization system serves multiple functions including cabin pressurization, cabin temperature control, and galley chiller operation, replacing multiple separate systems with one multi-functional device
3Temperature
If dedicated galley chiller system is used, then refrigeration performance is improved, but overall aircraft efficiency decreases due to additional weight and power
Solution Approach 1:
The galley chiller function is merged with the main pressurization system, sharing the compressor, turbine, and housing, thereby eliminating the need for a separate dedicated chiller system while maintaining refrigeration capability
Solution Approach 2:
The integrated pressurization system provides universal service for both cabin environmental control and galley refrigeration needs, allowing the same device to perform multiple thermal management functions
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 system enhances thermal management by improving operating efficiency, reducing size and weight, and adapting to supersonic conditions, while maintaining effective heat removal.
Implementation Method 1
a turbine operably coupled to the compressor by a shaft, the turbine configured to receive the at least one medium from the compressor
Implementation Method 2
a cooling heat exchanger arranged downstream from the turbine relative to a flow of the at least one medium through the system, the cooling heat exchanger configured to receive the at least one medium from the turbine
Data Source
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AI summary
A system for a vehicle includes at least one inlet (22) for receiving at least one medium and a device arranged in fluid communication with the at least one inlet. The device includes a shaft (30) rotatable about a shaft axis, a compressor (26) connected to the shaft, and a turbine (28) connected to the shaft and also configured to drive the compressor upon receipt of the at least one medium. The turbine is a mixed-flow turbine.