Rocket Engine Independent Gas Generator for Startup Power
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Solution Overview
Problem
Rocket engines of the expander type face challenges in generating electricity, particularly during startup phases, as existing solutions like electric generators on turbopump shafts are unusable during non-rotation periods and alternative solutions like fuel cells or batteries increase complexity and mass.
Innovation Solution
A rocket engine design featuring a gas generator driven by combustion gases, an alternator coupled to a power generation turbine, and pressurization pumps that allow independent operation of the electric generator, enabling electricity production regardless of turbopump rotation, with options for auxiliary nozzles to manage gas flow and energy recovery.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If an electric generator is arranged on the shaft of the turbine of the turbopump, then electricity can be produced during operation, but the generator remains unusable during start-up phases when the turbopump is not rotating
Solution Approach 1:
The invention separates the electricity generation function from the propellant pumping function by creating an independent gas generator system. This segmentation allows the electric generator to operate independently of the turbopump rotation, providing electricity during both start-up and operational phases.
Solution Approach 2:
The gas generator system serves multiple functions: it generates electricity through the electric generator during all flight phases, and its combustion gases can be directed to the main combustion chamber to supplement thrust. This multi-functionality resolves the contradiction by making the system adaptable to different operational requirements.
2Reliability
If fuel cells or batteries are integrated into the rocket engine to provide electricity during start-up, then electricity availability is improved, but device complexity and mass increase
Solution Approach 1:
The gas generator system provides multiple functions using a single integrated design: electricity generation through the alternator, thrust supplementation by directing gases to the main combustion chamber, and potential heat recovery. This eliminates the need for separate battery or fuel cell systems, reducing overall system complexity.
Solution Approach 2:
The system uses the rocket engine's own propellant supply to fuel the gas generator, making it self-sufficient. The combustion gases produced can be reused in the main combustion chamber, creating a self-contained system that doesn't require external power sources like batteries or fuel cells.
3Power
If combustion gases from the gas generator are discharged separately, then electricity generation is maximized, but energy recovery efficiency decreases
Solution Approach 1:
The invention recovers the energy from combustion gases by directing them to the main combustion chamber where they supplement the main propellant combustion. This recovery process converts what would be wasted energy into useful thrust, simultaneously maintaining electricity generation capability.
Solution Approach 2:
The gas generator system serves dual purposes: generating electricity through the alternator and providing supplemental thrust by injecting combustion gases into the main combustion chamber. This multi-functionality allows the system to maximize both electricity generation and energy recovery without compromise.
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 configuration provides a flexible and reliable source of electricity throughout all flight phases, including startup, by decoupling the electric generator's operation from turbopump rotation and propellant supply, reducing complexity and mass while ensuring continuous power availability.
Implementation Method 1
a gas generator configured to be supplied with a mixture of propellants to cause combustion
Implementation Method 2
an alternator mechanically coupled to a shaft of the electricity generating turbine
Implementation Method 3
two pressurization pumps to pressurize the propellant tanks used to supply the engine
Data Source
Figure 1
Figure 2
Figure 3
AI summary
The invention relates to a rocket engine (1) including a main combustion chamber (5) and a main nozzle; two propellant supply pumps (8a, 13) arranged on propellant supply circuits of the engine to supply the main combustion chamber; two pressurisation pumps (10, 11) for pressurising the propellant; and an electricity generator (20). The electricity generator (20) comprises a gas generator (22), an electricity generation turbine (24), and an alternator (26) coupled with the turbine shaft. The rocket engine is configured to allow the gas generator to be supplied with propellant by the two pressurisation pumps (10, 11). The supply of the electricity generator (24) is independent from the rotation of the supply pumps (8a, 13).