Cryogenic Bleed Air Separation for Aircraft Cooling and Oxygen Supply
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Solution Overview
Problem
Gas turbine engines in aircraft face inefficiencies due to material constraints, leading to reduced performance in propulsion and power generation, and existing cooling systems struggle to effectively chill engine bleed air while separating oxygen and nitrogen for on-board use.
Innovation Solution
A cryogenic cooling system that chills engine bleed air to produce a chilled working fluid at a temperature below oxygen's boiling point and above nitrogen's, using a compressor and turbine to compress and expand the air, and a separator to isolate gaseous nitrogen and liquid oxygen for specific aircraft uses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If gas turbine engines operate with balanced thermodynamic cycles, then material constraints are satisfied, but work efficiency is reduced due to cooling air losses
Solution Approach 1:
The patent changes the thermodynamic parameters of the cooling air by chilling it to cryogenic temperatures (below oxygen boiling point) before reintroduction. This parameter change allows the cooling air to provide both cooling and work contribution, resolving the contradiction between material constraint satisfaction and energy loss
Solution Approach 2:
The patent converts the harmful effect of cooling air losses into a beneficial effect by chilling the cooling air to produce a chilled working fluid that can be separated into oxygen and nitrogen supplies. The previously wasted cooling air now provides multiple benefits: cooling, work generation, and oxygen supply for combustion enhancement
2Temperature
If cooling air is bled from the engine, then thermal management is achieved, but propulsion efficiency is reduced
Solution Approach 1:
The patent makes the cooling air serve multiple functions simultaneously: thermal management of engine components, work generation through expansion, and oxygen supply for combustion. This multi-functionality resolves the contradiction between achieving thermal management and maintaining propulsion efficiency
Solution Approach 2:
By changing the temperature parameter of the bled cooling air to cryogenic levels, the system enables the cooling air to contribute to propulsion through work generation and combustion enhancement, thereby resolving the efficiency loss
3Temperature
If engine bleed air is used for cooling, then component temperature is reduced, but available thrust is decreased
Solution Approach 1:
The patent converts the thrust-reducing effect of bleed air into a thrust-enhancing effect by chilling the bleed air and reintroducing it as a chilled working fluid. The chilled oxygen-enriched air provides both cooling and combustion enhancement, thereby increasing available thrust
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 aircraft performance by providing efficient cooling for components, increasing airflow, and isolating oxygen and nitrogen supplies for improved propulsion and power generation.
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
Data Source
AI summary
A system for an aircraft includes an engine bleed source of a gas turbine engine. The system also includes a means for chilling an engine bleed air flow from the engine bleed source to produce a chilled working fluid. The system further includes a means for providing the chilled working fluid for an aircraft use.