Rocket Engine Cooling via Supercritical Coolant Heat Transfer
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing rocket engine cooling systems face inefficiencies in heat transfer and specific impulse due to the limitations of conventional coolants, which often result in reduced performance and increased maintenance needs.
Innovation Solution
The proposed rocket engine system employs a cooling system that utilizes a coolant source, a propellant source, a pressurization system, and a heat exchanger to heat the coolant to a supercritical state, enhancing convective heat transfer and improving specific impulse.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional coolants are used in rocket engine cooling systems, then the system structure is simple, but heat transfer efficiency is low and specific impulse is reduced
Solution Approach 1:
The patent applies parameter changes by heating the coolant to supercritical conditions (above critical temperature and pressure) to fundamentally alter its physical properties. This transformation enables the coolant to achieve dramatically higher heat transfer coefficients and lower viscosity, directly resolving the heat transfer efficiency limitation of conventional subcritical coolants while maintaining the basic cooling system architecture
Solution Approach 2:
The patent utilizes the phase transition of the coolant from subcritical liquid/gas state to supercritical state through controlled heating and pressurization. This phase transition enables the coolant to exhibit enhanced thermal conductivity and heat capacity, thereby significantly improving convective heat transfer efficiency without requiring complex system modifications
2Productivity
If conventional coolants are used, then maintenance requirements are reduced, but specific impulse and performance are increased
Solution Approach 1:
By changing the coolant operating parameters to supercritical conditions, the system achieves higher specific impulse through improved heat transfer efficiency. The supercritical coolant's enhanced thermal properties allow for more effective energy extraction from the combustion chamber, directly boosting rocket performance while the parameter change is achieved through standard heat exchanger and pressurization system operations
3Productivity
If coolant is heated to supercritical state, then convective heat transfer is increased, but energy input requirements are increased
Solution Approach 1:
The patent exploits the phase transition to supercritical state where the coolant undergoes dramatic improvements in heat transfer properties. Although energy input is required to achieve supercritical conditions, the resulting convective heat transfer efficiency gains far exceed the energy investment, as the supercritical coolant can extract heat much more effectively from the combustion chamber walls
Solution Approach 2:
The patent converts the high energy input requirement into a benefit by utilizing it to transform the coolant into a supercritical state with superior heat transfer capabilities. The energy investment in heating and pressurizing the coolant is repaid many times over through the dramatically enhanced heat extraction efficiency, turning what appears to be a disadvantage into a performance advantage
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 approach significantly increases convective heat transfer due to the lower viscosity and higher conductivity of the coolant in a supercritical state, leading to more effective cooling and improved rocket engine performance, including increased specific impulse and reduced maintenance requirements.
Implementation Method 1
the coolant is heated to a temperature and pressure such that the coolant is at a supercritical state
Implementation Method 2
This approach significantly increases convective heat transfer due to the lower viscosity and higher conductivity of the coolant in a supercritical state
Implementation Method 3
a pressurization system... such that the coolant can be pressurized and then heated by a heat exchanger
Implementation Method 4
the coolant after the coolant has powered the pressurization system... which is cooled by the coolant
Data Source
AI summary
A rocket engine system including a thrust chamber including walls that define an interior surface and a combustion section which is fluidically coupled to an output section. A coolant source containing a coolant. A means of heating the coolant. At least one port configured to apply the coolant to the interior surface to achieve a film cooling of the interior surface and wherein the coolant source is fluidically coupled to the means of heating and the at least one port.