Rotating Detonation Engine Cooling With Supercritical Water
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Solution Overview
Problem
Existing rocket engines face challenges in efficiently managing heat and maintaining structural integrity due to high combustion temperatures, particularly in detonation-based engines like rotating detonation engines, which require effective cooling systems to enhance performance and reliability.
Innovation Solution
A rocket engine system utilizing a coolant source that is heated to a supercritical, sub-supercritical, or above-supercritical state to provide film cooling and secondary combustion, with water as a preferred coolant, enhancing cooling efficiency through convective heat transfer and reducing reaction kinetics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional coolants are used in rocket engines, then cooling function is provided, but the system becomes more complex and expensive
Solution Approach 1:
The patent applies multi-functionality by using water as a coolant that serves multiple purposes: it cools the combustion chamber through convective heat transfer, reduces reaction kinetics to improve mixing, and can be used as a propellant component. This eliminates the need for separate conventional cooling systems, reducing complexity while maintaining cooling efficiency.
Solution Approach 2:
The patent changes the physical state parameters of water by heating it to supercritical, sub-supercritical, or above-supercritical states. This parameter change enables water to achieve superior cooling performance compared to conventional coolants while simplifying the overall system architecture.
2Reliability
If conventional coolants are used in rocket engines, then cooling function is provided, but the system becomes more expensive
Solution Approach 1:
The patent replaces expensive conventional coolants with water, which is significantly cheaper and more readily available. Water serves as an inexpensive coolant that maintains cooling efficiency without the high cost associated with traditional cooling systems in rocket engines.
Solution Approach 2:
By changing water to supercritical or sub-supercritical states through parameter changes in temperature and pressure, the system achieves enhanced cooling performance that justifies the simplicity and low cost of using water instead of expensive conventional coolants.
3Power
If high combustion temperatures are used in detonation engines, then thrust performance is improved, but structural integrity is compromised
Solution Approach 1:
The patent uses supercritical or sub-supercritical water to change the thermal management parameters of the combustion system. This allows the engine to operate at high combustion temperatures for improved thrust performance while the supercritical water cooling system maintains structural integrity by efficiently removing heat from critical components.
Solution Approach 2:
Supercritical water acts as an intermediary cooling medium between the high-temperature combustion zone and the structural components. It absorbs excess heat through convective heat transfer and phase changes, protecting the structure from thermal damage while allowing high-power operation.
4Power
If reaction kinetics are increased for faster combustion, then power output is improved, but mixing efficiency is reduced
Solution Approach 1:
The patent uses supercritical or sub-supercritical water to change the physical and chemical parameters of the combustion environment. This parameter change reduces reaction kinetics, allowing fuel and oxidizer to mix more efficiently while still achieving high power output through the controlled combustion process.
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 achieves improved cooling efficiency, increased specific impulse, and extended engine life by using water as a coolant, which is more readily available, less toxic, and less expensive than conventional coolants, while reducing reaction kinetics for more efficient fuel and oxidizer mixing.
Implementation Method 1
enhancing cooling efficiency through convective heat transfer
Implementation Method 2
the coolant is heated to a temperature and pressure such that the coolant is at a supercritical state
Implementation Method 3
reducing reaction kinetics for more efficient fuel and oxidizer mixing
Data Source
AI summary
A rotating detonation rocket engine system including a fuel source containing a fuel. A liquid peroxide source providing liquid peroxide within a rotating detonation engine such that a first surface of a wall partially defining the combustion chamber of the rotating detonation engine is cooled. A monitor configured to control a flow of the fuel and a flow of the liquid peroxide. The monitor is configured to ensure that a stoichiometry of a combination of the fuel and the liquid peroxide is appropriate for generating a combustion of the combination of the fuel and the liquid peroxide.