Chilled working fluid generation and separation for an aircraft
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Solution Overview
Problem
Current aircraft systems face inefficiencies in propulsion and thermal management due to constraints on gas turbine engine design, limited air intake, and the need for effective cooling and oxygen supply systems, which are not adequately addressed by existing technologies.
Innovation Solution
A system and method for generating and separating chilled working fluids, specifically using a cryogenic cooling system to produce liquid air and separate gaseous nitrogen and liquid oxygen on an aircraft, utilizing an engine bleed air flow, and providing these as supplies for various aircraft systems and components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a gas turbine engine is designed with material property constraints, then the engine can operate reliably, but the design becomes less efficient due to thermodynamic losses
Solution Approach 1:
The patent changes the temperature parameter of the cooling air by chilling it to sub-ambient temperatures before introduction into the combustor. This parameter change allows the cooling air to contribute positively to combustion efficiency rather than representing a thermal loss, thereby reducing overall thermodynamic losses while maintaining engine reliability
Solution Approach 2:
The patent converts the harmful effect of cold cooling air (which would normally represent a thermodynamic loss) into a beneficial contribution to combustion. By chilling the cooling air and introducing it to the combustor, the system transforms what was previously a waste stream into a useful component that enhances combustion efficiency and reduces overall energy losses
2Ease of manufacture
If separate systems are used for propulsion and thermal management, then each system can be optimized independently, but the overall aircraft system complexity increases
Solution Approach 1:
The patent merges the propulsion system and thermal management system by integrating the cooling air chilling and utilization process directly into the gas turbine engine operation. The same engine that provides propulsion also generates and utilizes chilled air for thermal management, combining previously separate functions into a unified system that reduces overall complexity
Solution Approach 2:
The gas turbine engine is designed to serve multiple functions simultaneously: it provides propulsion through power generation and also provides thermal management through chilling and utilization of cooling air. This multi-functionality eliminates the need for separate dedicated thermal management systems, thereby reducing aircraft system complexity while maintaining independent optimization capabilities
3Productivity
If cooling air is introduced into the combustor without chilling, then the engine can operate, but work is lost due to thermodynamic inefficiencies
Solution Approach 1:
The patent changes the temperature parameter of the cooling air from ambient or hot temperatures to sub-ambient chilled temperatures before introduction into the combustor. This parameter change ensures that the cooling air contributes positively to the combustion process rather than representing a thermodynamic loss, thereby maintaining engine productivity while eliminating work loss
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 aircraft efficiency by providing a reliable and efficient cooling system, improving propulsion and thermal management, and reducing the need for onboard oxygen and nitrogen generation, thereby enhancing performance and reducing weight and complexity.
Implementation Method 1
a compressor operable to further compress the engine bleed air flow as compressed air
Implementation Method 2
at least one turbine operable to expand and cool the compressed air as the chilled working fluid
Implementation Method 3
an impact plate positioned proximate to an input port to alter a flow direction of the chilled working fluid
Implementation Method 4
separating gaseous nitrogen from the chilled working fluid as a gaseous nitrogen supply and separating liquid oxygen from the chilled working fluid as a liquid oxygen supply
Data Source
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AI summary
A system for an aircraft (100) includes an engine bleed source (251) of a gas turbine engine (20). The system also includes a means for chilling an engine bleed air flow (252) from the engine bleed source (251) to produce a chilled working fluid. The system further includes a means for providing the chilled working fluid for an aircraft use.