Integrated Electro-Aero-Thermal Engine With Electric Power Assist
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Solution Overview
Problem
Existing gas turbine engines primarily rely on converting high-energy exhaust gas flow into mechanical power, limiting efficiency improvements, and integrating electric motors and generators can enhance engine performance.
Innovation Solution
Integration of electric generators and motors into a hybrid electro-aero-thermal turbine engine, combining fuel and electro-chemical power to increase kinetic energy through the engine, with a geared architecture and split compressor sections to optimize power distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If electric motors and generators are integrated into the turbine engine, then engine efficiency and power production are improved, but device complexity increases
Solution Approach 1:
The patent combines electric motors and generators into an integrated electro-aero-thermal system where the electric motor drives the compressor section and the turbine drives the generator, creating a hybrid power system that improves overall engine efficiency while managing complexity through functional integration
Solution Approach 2:
The electric motor-generator system serves multiple functions: the motor acts as a compressor driver during ground operations and startup, the generator provides electrical power during flight, and both components contribute to overall thrust production, allowing a single integrated system to perform multiple roles
2Use of energy by moving object
If a hybrid electro-aero-thermal system is implemented, then fuel consumption is reduced, but device complexity increases
Solution Approach 1:
The patent divides the compressor section into two independent sections: a first compressor section driven by the high-pressure turbine and a second compressor section driven by the electric motor. This segmentation allows each compressor section to operate optimally under different conditions, reducing overall fuel consumption while managing system complexity through modular design
Solution Approach 2:
The system dynamically switches between different power sources and operational modes based on flight conditions. The electric motor can independently drive the second compressor section or operate in conjunction with the turbine-driven first compressor section, allowing the system to adapt to varying thrust requirements and optimize fuel efficiency across different operating regimes
3Power
If split compressor sections are used, then power distribution is optimized, but device complexity increases
Solution Approach 1:
The compressor is divided into two independent sections with separate drive mechanisms: the first compressor section is driven by the high-pressure turbine through a first shaft, while the second compressor section is driven by the electric motor through a second shaft. This segmentation enables independent control and optimization of power distribution to match varying operational requirements
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
Enhances engine efficiency by reducing fuel consumption and load on high-pressure turbines, allowing faster reaction to throttle changes and variable thrust levels.
Implementation Method 1
An electro-chemical potential of energy stored in a battery is converted to mechanical power by electric motors to increase kinetic energy of engine flows
Implementation Method 2
The high energy gas flow is converted to mechanical energy as it expands through a turbine section
Implementation Method 3
fuel and electricity are converted to mechanical power to increase kinetic energy of flows through the engine. Conversion of fuel to mechanical power is accomplished by combining the fuel with high pressure air and igniting the mixture to produce a high energy gas flow
Data Source
Figure 1A~1B
Figure 2
Figure 3~4
AI summary
A turbine engine (20) includes integrated electric machines in the compressor section (24) and the turbine section (28) to supplement power produced from fuel with electric power. The example compressor section (24) includes a compressor electric motor (74) that is coupled to a compressor generator (76). The example turbine section (28) includes a turbine electric motor (94) that is coupled to a geared architecture (48) to supplement power driving a fan section (22). A turbine generator (96) provides electric power to the turbine electric motor (94).