Ultra-High-Temperature Turbo Generator for Hypersonic Cooling
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Solution Overview
Problem
Existing aircraft pressurization systems are inefficient and power-intensive, and at supersonic or hypersonic speeds, air temperature exceeds the cooling capacity of these systems, necessitating improved thermal management solutions.
Innovation Solution
A thermodynamic device comprising a turbine and compressor coupled via a shaft, with an electric generator, and a heat exchanger positioned either upstream or downstream to manage high-temperature air, utilizing fuel as a heat sink to cool the air and generate electricity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional pressurization systems are used for thermal management, then system simplicity is maintained, but cooling capacity is insufficient at hypersonic speeds due to excessive air temperature
Solution Approach 1:
The patent replaces conventional mechanical cooling systems with a thermodynamic cycle system that uses heat exchangers and expanders to convert thermal energy into mechanical work and electricity, enabling effective cooling at hypersonic speeds where conventional systems fail due to excessive temperatures
2Ease of operation
If nonintegrated pressurization systems are used for temperature control, then regional temperature control is achieved, but overall aircraft efficiency decreases due to significant weight and power requirements
Solution Approach 1:
The patent merges the pressurization system and thermal management system into a single integrated architecture where the expander serves dual purposes: driving the compressor for pressurization and generating electricity for aircraft systems, thereby eliminating redundant components and reducing overall power requirements
Solution Approach 2:
The expander component performs multiple functions simultaneously: it drives the compressor for air supply, generates electrical power through the generator, and provides cooling capacity through the thermodynamic cycle, making the system highly versatile and efficient
3Temperature
If heat exchanger is positioned upstream from the turbine, then cooling effectiveness is improved, but system complexity increases
Solution Approach 1:
The patent segments the thermodynamic cycle into distinct functional components with clearly defined temperature and pressure zones, allowing the heat exchanger to be positioned upstream of the turbine in a modular configuration that improves cooling effectiveness while maintaining manageable system complexity through functional separation
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 effectively cools high-temperature air to manageable levels, reducing energy consumption and enhancing aircraft efficiency by integrating energy extraction and thermal management.
Implementation Method 1
extracting energy from the first medium in a turbine to form an expanded first medium
Implementation Method 2
The first medium at the inlet has a temperature of at least 1000° F.
Implementation Method 3
compressing at least a portion of the expanded first medium via a compressor
Implementation Method 4
generating energy via an electric generator. The compressor is driven by energy extracted from the first medium within the turbine and the electric generator is driven by energy extracted from the first medium within the turbine
Implementation Method 5
A cooling system for an aircraft capable of travelling at hypersonic speeds includes an inlet configured to receive a first medium and a thermodynamic device fluidly connected to the inlet
Implementation Method 6
utilizing fuel as a heat sink to cool the air
Data Source
AI summary
A cooling system for an aircraft capable of travelling at hypersonic speeds includes an inlet configured to receive a first medium and a thermodynamic device fluidly connected to the inlet. The thermodynamic device includes at least one turbine and a compressor operably coupled via a shaft. An outlet of the at least one turbine is directly fluidly connected to an inlet of the compressor. An electric generator is operably coupled to the at least one turbine.