Cryogenic cooling system for an aircraft
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Solution Overview
Problem
Existing aircraft systems face inefficiencies in gas turbine engine design due to material constraints, leading to reduced performance and limited placement options, and electric propulsion motors are limited by power density and heating effects, necessitating improved thermal management solutions.
Innovation Solution
A cryogenic cooling system for aircraft that includes a compressor and turbine to chill engine bleed air, separating gaseous nitrogen and liquid oxygen for various aircraft uses, including fuel system inerting and cabin oxygen supply, enhancing thermodynamic efficiency and reducing combustion risks.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If gas turbine engines operate at higher temperatures and pressures to improve efficiency, then propulsion performance improves, but material constraints are exceeded and component reliability deteriorates
Solution Approach 1:
The patent changes the temperature parameter of the cooling air by implementing a two-stage cooling process. The first stage cools air to intermediate temperatures, and the second stage (cryogenic cooling) further reduces it to very low temperatures. This parameter transformation allows the cooling air to absorb more heat from engine components, enabling the engine to operate at higher temperatures without exceeding material limits, thus improving propulsion performance while maintaining component reliability.
Solution Approach 2:
The patent utilizes phase transitions of nitrogen and oxygen in air during cryogenic cooling. By cooling air to temperatures where nitrogen and oxygen approach their boiling points, the system achieves extreme cooling effects. This phase transition approach allows the cooling air to dramatically increase its heat absorption capacity, protecting engine components from thermal damage while enabling higher operating temperatures for improved propulsion efficiency.
2Temperature
If cooling air is extracted from the gas turbine engine to cool components, then thermal management improves, but work is lost and thermodynamic efficiency deteriorates
Solution Approach 1:
The patent replaces the conventional mechanical compression system with a cryogenic cooling system that uses phase transitions and heat exchange. Instead of mechanically compressing cooling air and dissipating it, the system uses cryogenic temperatures achieved through phase transitions to cool engine components. This substitution eliminates the need for additional compression work and mechanical drive systems, thereby reducing work loss while improving thermal management effectiveness.
Solution Approach 2:
The patent transforms the temperature parameter of the cooling air from moderate to cryogenic levels. This extreme temperature change increases the heat absorption capacity of the cooling air dramatically, allowing it to remove more heat from engine components without requiring large volumes of air extraction. Consequently, less work is lost due to reduced air extraction while maintaining effective thermal management.
3Power
If electric propulsion motors are used to drive rotating elements, then propulsion efficiency improves, but power density constraints and heating effects limit their application
Solution Approach 1:
The patent employs phase transitions of nitrogen and oxygen in air during cryogenic cooling. By cooling air to temperatures where nitrogen and oxygen approach their boiling points, the system achieves extreme cooling effects. This phase transition approach allows the cooling air to dramatically increase its heat absorption capacity, protecting engine components from thermal damage while enabling higher operating temperatures for improved propulsion efficiency.
Solution Approach 2:
The patent utilizes nitrogen, an inert gas, as the primary cooling medium. Nitrogen's inert properties prevent combustion and chemical reactions with hot engine components, creating a safe cooling environment. The system extracts nitrogen from air, cools it to cryogenic temperatures, and uses it to cool engine components. This inert atmosphere approach effectively manages heating effects in electric propulsion motors while maintaining propulsion efficiency.
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 provides efficient thermal management, increases airflow to critical components, and enhances propulsion efficiency by utilizing cryogenic temperatures for cooling and oxygen enrichment, improving overall aircraft performance and safety.
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
An engine-driven cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for condensing a chilled air stream into liquid air for an aircraft use. The first air cycle machine includes a plurality of components operably coupled to a gearbox of a gas turbine engine and configured to produce a cooling air stream based on a first engine bleed source of the gas turbine engine. The second air cycle machine is operable to output the chilled air stream at a cryogenic temperature based on a second engine bleed source cooled by the cooling air stream of the first air cycle machine.