Rocket Propellant Supply Heat Exchanger Pressure Control
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Solution Overview
Problem
Rocket engine liquid propellant supply systems face challenges in maintaining internal tank pressure during emptying without excessive pressure rise, which can lead to cavitation in pumps and potential tank rupture, especially with cryogenic propellants, and existing solutions either increase mass or complexity.
Innovation Solution
A propellant supply system with a first tank and a second tank connected by a supply circuit that includes a heat exchanger to cool the second propellant, allowing it to transfer heat to the first propellant, causing it to vaporize and maintain tank pressure, while also cooling the second propellant to prevent cavitation in pumps, with optional bypass valves for pressure regulation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stress or pressure
If thermal insulation of tanks is increased to prevent evaporation and pressure rise, then pressure control is improved, but mass increases significantly
Solution Approach 1:
The system uses the cold propellant itself as the cooling medium to prevent evaporation in the tank. The circulating propellant absorbs heat through the heat exchanger, creating a self-service cooling system that eliminates the need for additional thermal insulation mass.
Solution Approach 2:
A heat exchanger is introduced as an intermediary component between the propellant and the tank walls. This heat exchanger facilitates heat transfer from the tank to the circulating propellant, enabling active temperature control without requiring massive passive insulation.
2Stress or pressure
If propellant temperature increases due to heating, then pressure control becomes difficult, but pump cavitation risk increases
Solution Approach 1:
The system establishes a feedback loop where temperature and pressure sensors monitor the propellant state, and the circulation pump adjusts its operation accordingly. When temperature rises, the pump increases circulation through the heat exchanger to maintain pressure stability and prevent cavitation.
Solution Approach 2:
The propellant circulation through the heat exchanger operates continuously during tank emptying, providing ongoing cooling to maintain constant temperature and pressure. This continuous action prevents the temperature rise that would lead to cavitation in the pump.
3Stress or pressure
If simple pressurization methods are used during tank emptying, then pressure maintenance is achieved, but system complexity and mass increase
Solution Approach 1:
The circulating propellant system serves multiple functions simultaneously: it cools the tank to prevent evaporation, maintains pressure during emptying, and prevents cavitation in the pump. This multi-functionality eliminates the need for separate pressurization systems, reducing overall complexity.
Solution Approach 2:
The cooling and pressurization functions are merged into a single integrated system. The heat exchanger and circulation loop that provide cooling also generate the pressure needed for tank emptying, combining what would traditionally be separate systems into one unified approach.
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 solution effectively maintains tank pressure and prevents cavitation, reducing the risk of rupture and pump failure while minimizing mass and complexity, and allows for precise pressure control.
Implementation Method 1
transfer heat from the second propellant to the first propellant
Implementation Method 2
pass the first propellant derived through the branch into a gaseous state
Implementation Method 3
cooling the second propellant
Implementation Method 4
contribute, in the gaseous state, to maintaining the internal pressure of the first tank during its emptying
Implementation Method 5
The cooling of the second propellant in the second tank thanks to the first heat exchanger helps to avoid cavitation phenomena in this pump of the second supply circuit
Data Source
Figure 1
Figure 2~4
Figure 3
AI summary
The invention relates to the field of rocket engines and, more specifically, a system for supplying a rocket engine (2) with propellant, said system comprising a first tank (3), a second tank (4), a first supply circuit (6) connected to the first tank (3), and a second supply circuit (7) connected to the second tank (4). In order to cool the propellant contained in the second tank (4), the first circuit (6) comprises a branch (12) that extends through a first heat exchanger (14) built into the second tank (4). The invention also relates to a method for supplying the rocket engine (2).