Rocket Engine Auxiliary Power Generation via Gas Turbine Coupling
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Solution Overview
Problem
Rocket engine powered aircraft lack a reliable onboard system to generate electrical energy efficiently, relying on energy storage devices that may not meet high-power demands or sustain long-duration operations.
Innovation Solution
An integral propulsion and auxiliary power generation system that includes a rocket engine, a liquid propellant supply system with a gas generator and gas turbine, a power generator, a transmission system, and an energy storage device, which collectively convert mechanical energy into electrical energy to power onboard systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If onboard energy storage devices (batteries) are used to supply electrical energy, then the aircraft can operate with simple propulsion system, but the operational duration is limited and cannot meet high-power auxiliary system demands
Solution Approach 1:
The patent merges the rocket engine propulsion system with an auxiliary power generation system by integrating a gas generator and gas turbine. The rocket engine burns liquid fuel and oxidizer to produce thrust, while a portion of the fuel and oxidizer is diverted to the gas generator to drive the gas turbine, which mechanically couples to an electromagnetic generator to produce electrical power for auxiliary systems.
Solution Approach 2:
The rocket engine serves dual functions: primary thrust generation and auxiliary electrical power generation. The same liquid fuel and oxidizer supply system supports both the main rocket engine and the gas generator-turbine-generator assembly, allowing the propulsion system to simultaneously provide mechanical thrust and electrical energy for extended operational duration.
2Power
If a gas turbine and power generator are integrated with the rocket engine, then high-power electrical energy can be generated, but the device complexity increases
Solution Approach 1:
The patent combines the auxiliary power generation components (gas generator, gas turbine, electromagnetic generator) with the existing rocket engine propulsion system. The gas generator utilizes the same liquid fuel and oxidizer resources as the main engine, and the transmission system mechanically couples the gas turbine to the electromagnetic generator, creating an integrated multi-functional system rather than separate additive components.
Solution Approach 2:
The liquid propellant supply system serves dual purposes: fueling the main rocket engine for thrust and supplying the gas generator for electrical power generation. The mechanical transmission system connects the gas turbine output to both the electromagnetic generator for electricity production and potentially back to the propellant supply pumps, creating a versatile system that handles both propulsion and power generation functions through shared components.
3Device complexity
If onboard batteries are used for auxiliary power, then the system remains simple for short-duration operations, but it cannot sustain high-power auxiliary systems beyond one hour
Solution Approach 1:
The patent integrates the electromagnetic generator with the gas turbine and rocket engine system, replacing or supplementing onboard batteries. The generator continuously converts mechanical energy from the gas turbine into electrical energy, providing sustained power for auxiliary systems throughout the flight duration rather than relying on limited battery capacity that would deplete after approximately one hour of operation.
Solution Approach 2:
The liquid propellant supply system provides fuel and oxidizer to both the main rocket engine and the gas generator simultaneously. This dual-use approach allows the same propellant resources to extend both thrust duration and electrical power generation duration, enabling the aircraft to operate high-power auxiliary systems for the entire flight mission rather than being constrained by battery limitations.
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 system enables the generation of high-power electrical energy onboard rocket engine powered aircraft, efficiently meeting the demands of high-power auxiliary electrical systems and extending operational duration beyond what is possible with energy storage devices alone.
Implementation Method 1
The gas generator is configured to burn a mixture of the liquid fuel and the liquid oxidizer to generate a combustion gas stream
Implementation Method 2
The gas turbine is in fluid communication with the gas generator and is configured to convert the kinetic energy of the combustion gas stream into mechanical energy
Implementation Method 3
The power generator is configured to convert mechanical energy into electrical energy
Data Source
AI summary
An integral propulsion and auxiliary power generation system includes a rocket engine, a liquid propellant supply system, an auxiliary electrical system, and a transmission system. The liquid propellant supply system is configured to supply a liquid fuel and a liquid oxidizer to the rocket engine. The liquid propellant supply system includes a gas generator configured to burn a mixture of the liquid fuel and the liquid oxidizer to generate a combustion gas stream, and a gas turbine configured to convert the kinetic energy of the combustion gas stream into mechanical energy. The auxiliary electrical system includes a power generator configured to convert mechanical energy into electrical energy and an electric load device electrically coupled to the power generator. The transmission system is configured to mechanically couple the gas turbine and the power generator to selectively transfer mechanical energy between the gas turbine and the power generator.