Turbineless Jet Engine External Electric Drive
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Solution Overview
Problem
Conventional jet engines with internal turbines to drive compressors face high design and material demands due to high temperatures, increasing production and maintenance costs, and complexity.
Innovation Solution
A jet engine with an externally driven compressor using an electrical drive and energy storage, eliminating the need for an internal turbine, allowing for reduced complexity and increased thrust with a single combustion chamber and energy storage for extended operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If an internal turbine is used to drive the compressor in conventional jet engines, then the compressor can be driven using exhaust gas energy, but the thrust energy is reduced and the design complexity increases due to high temperature requirements
Solution Approach 1:
The turbine is extracted from the jet engine system and replaced by an external electric drive. This removes the complex high-temperature turbine components while maintaining the ability to drive the compressor, thereby reducing device complexity without sacrificing energy utilization capability
Solution Approach 2:
The mechanical turbine-driven compressor system is replaced by an electrically driven compressor system. The electric motor converts electrical energy to mechanical energy to drive the compressor, eliminating the need for a mechanical turbine and associated high-temperature material requirements
2Use of energy by moving object
If an internal turbine is used to drive the compressor, then the compressor can be driven using exhaust gas energy, but manufacturing and maintenance costs increase due to high temperature material requirements
Solution Approach 1:
The patent describes a disposable missile system where the entire propulsion system including the electric drive and battery is designed as a single-use component. This eliminates the need for expensive, maintenance-free high-temperature turbine components, as the entire system is replaced after one use rather than requiring durable materials for repeated operation
Solution Approach 2:
Replacing the mechanical turbine system with an electric drive system uses materials and manufacturing processes that are less costly and easier to manufacture, particularly for single-use applications where the complex high-temperature alloy requirements for turbines are eliminated
3Use of energy by moving object
If an internal turbine is used to drive the compressor, then the compressor can be driven using exhaust gas energy, but the thrust energy is reduced by the amount of diverted energy
Solution Approach 1:
The energy sources are segmented into separate functions: the battery provides electrical energy for the compressor drive, while the exhaust gas energy is fully available for thrust generation. This segmentation allows both energy utilization for compression and maximum energy availability for thrust without the trade-off inherent in turbine systems
4Temperature
If turbines with cooling devices and flow modulation systems are used, then temperature and flow can be controlled, but the device complexity increases
Solution Approach 1:
The turbine and its associated cooling and flow modulation systems are extracted from the design. Temperature control is achieved passively by designing the combustion chamber to operate at optimal temperatures, eliminating the need for active cooling devices and complex flow modulation systems
Solution Approach 2:
The system uses the natural properties of the exhaust gas and combustion process to achieve temperature control without additional active components. The combustion chamber and nozzle geometry are designed to provide inherent temperature and flow control
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 reduces manufacturing and maintenance costs while enabling efficient and controlled thrust, suitable for applications like disposable rockets, with temperatures up to 1500°C and extended operational periods.
Implementation Method 1
a compressor for compressing an inlet gas before it enters at least one combustion chamber of the jet engine
Implementation Method 2
an electric drive for driving the compressor, wherein the electric drive is arranged outside a jet of the jet engine
Implementation Method 3
at least one combustion chamber of the jet engine... the exhaust gas has an average temperature of at least 1500°C upon exiting the at least one combustion chamber
Implementation Method 4
the drive module comprises an energy storage device for storing electrical energy to operate the electric drive, preferably a battery with a service life of at least 10, preferably 15, and even more preferably 20 years
Data Source
Figure 1
Figure 2
AI summary
Propulsion module with a jet engine, wherein the propulsion module comprises: a compressor for compressing an inlet gas prior to its entry into at least one combustion chamber of the jet engine and an electric drive for driving the compressor, wherein the electric drive is arranged outside a jet of the jet engine.