Hybrid Liquid-Propellant Engine Gas Turbine Generator Electric Pump
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Conventional liquid-propellant engines face challenges with weight due to large batteries required for electrically driven pumps, and difficulty in controlling or throttling gas turbine geared pumps.
Innovation Solution
A liquid-propellant engine combining a gas turbine, generator, electric pump, and power management system, which provides continuous electrical power to the pumps, reducing the need for heavy batteries and allowing for easier control of the engine.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If electrically driven pumps are used, then ease of control and throttling is improved, but weight increases due to large batteries
Solution Approach 1:
The patent combines the gas turbine engine with a generator to create a hybrid system where the gas turbine drives the generator to produce electrical power for the pumps. This merging eliminates the need for separate large batteries while maintaining electric pump control advantages.
Solution Approach 2:
The gas turbine engine serves dual purposes: providing mechanical thrust and generating electrical power through the generator for the pump system. This self-service approach eliminates the need for external battery power sources.
2Weight of moving object
If gas turbine geared pumps are used, then weight is reduced, but ease of control and throttling deteriorates
Solution Approach 1:
The patent replaces the mechanical geared pump system with an electric pump system driven by a generator. This substitution maintains the weight advantages of gas turbine-driven systems while providing the control advantages of electric motors through electronic throttle control.
3Ease of operation
If large batteries are used to power electric pumps, then ease of control is improved, but productivity decreases due to more fuel and oxidizer required
Solution Approach 1:
The gas turbine engine generates its own electrical power through the generator, eliminating the need for separate battery power sources. This self-service approach improves productivity by reducing the total fuel and oxidizer required compared to battery-powered systems.
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 solution reduces the weight associated with electric pump fed engines while maintaining easier control and throttling than traditional gas turbine engines, enabling more efficient propulsion of rockets.
Implementation Method 1
the gas turbine and generator are configured for providing power to an electric motor for operating a fuel pump and/or an oxidizer pump
Implementation Method 2
gas turbine geared pumps utilized in rocket engines
Implementation Method 3
a generator, an electric pump fed engine, and a power management system. When in use, the gas turbine and generator are configured for providing power to an electric motor
Implementation Method 4
providing power to an electric motor for operating a fuel pump and/or an oxidizer pump
Implementation Method 5
to pump fuel and oxidizer from individual tanks into a combustion chamber for mixture and combustion
Implementation Method 6
into a combustion chamber for mixture and combustion. The combustion of the fuel and oxidizer is configured for providing thrust
Data Source
AI summary
An improved liquid-propellant engine utilizing a combination of a gas turbine, a generator, an electric pump fed engine, and a power management system. When in use, the gas turbine and generator are configured for providing power to an electric motor for operating a fuel pump and an oxidizer pump to pump fuel and oxidizer from individual tanks into a combustion chamber for mixture and combustion. The combustion of the fuel and oxidizer is configured for providing thrust from the base of a rocket to propel it. The generator of the present invention provides continuous electrical power to the electric pump(s) to continue the supply of fuel and oxidizer to the combustion chamber. The power management system of the present invention is electrically connected to the generator, the electric motor(s) configured for operating the fuel and oxidizer pumps, a flight computer, and fuel and oxidizer valves.