Supercritical Coolant Heat Transfer in Rocket Engines
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Solution Overview
Problem
Current rocket engine cooling systems are inefficient in managing heat transfer due to limitations in coolant properties, particularly in achieving a supercritical state that enhances convective heat transfer.
Innovation Solution
The implementation of a rocket engine system utilizing a supercritical coolant, which includes a coolant source, propellant source, and a heat exchanger to pressurize and heat the coolant to a supercritical state, integrated with a pressurization system and aerospike nozzle for efficient cooling of engine components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional coolant is used in rocket engine cooling systems, then the system structure is simple, but convective heat transfer efficiency is insufficient
Solution Approach 1:
The patent applies parameter changes by transforming the coolant from subcritical to supercritical state through pressure and temperature adjustments. The coolant is pressurized above its critical pressure and heated above its critical temperature, fundamentally changing its physical properties to achieve superior heat transfer coefficients while managing the increased system complexity through integrated heat exchanger design
Solution Approach 2:
The patent utilizes phase transitions by operating the coolant across its critical point where distinct liquid and gas phases merge into a supercritical fluid. This phase transition enables the coolant to exhibit both liquid-like density and gas-like diffusivity, maximizing convective heat transfer efficiency in the cooling channels
2Temperature
If coolant is pressurized and heated to supercritical state, then convective heat transfer increases, but energy consumption increases
Solution Approach 1:
The patent merges the cooling function with power generation by using the supercritical coolant to drive a turbine or expander after heat exchange. The high-energy coolant that has absorbed heat from the engine components is directed through a turbine to generate mechanical work, thereby recovering energy that would otherwise be wasted and offsetting the energy required for pressurization and heating
Solution Approach 2:
The patent converts the high-temperature, high-pressure coolant (which represents thermal energy that must be managed) into a beneficial resource by using it to drive a turbine. The waste heat and pressure energy are transformed into useful mechanical work, turning a potential loss into a gain that reduces overall system energy consumption
3Temperature
If supercritical coolant is used, then thermal conductivity increases, but system pressure requirements increase
Solution Approach 1:
The patent applies preliminary action by pressurizing the coolant to supercritical conditions before it enters the cooling channels. The pressurization system prepares the coolant in advance, ensuring it reaches the required pressure and temperature state before contacting the hot engine components, thereby optimizing heat transfer from the outset
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 by lowering viscosity and increasing thermal conductivity of the coolant, leading to more effective and efficient cooling of rocket engine components.
Implementation Method 1
the coolant is pressurized and then heated by a heat exchanger to a supercritical state
Implementation Method 2
a heat exchanger to pressurize and heat the coolant to a supercritical state
Implementation Method 3
significantly increases convective heat transfer by lowering viscosity and increasing thermal conductivity of the coolant
Data Source
AI summary
A rocket engine system comprising a rocket engine, coolant and a coolant source, propellant and a propellant source, a turbopump, and a heat source. The coolant is pressurized and then heated through a heat source to a supercritical state for augmented heat transfer. The heat source may be a heat exchanger with returning coolant, or a preburner. The rocket engine system may further comprise at least one additional rocket engine with a pump to provide pressure for multiple engine. The rocket engine system may further comprise multiple turbopump shafts for independent control of propellants.