Hybrid-Electric Aircraft Propulsion for Wide Thrust Range
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Solution Overview
Problem
Existing aircraft propulsion systems face challenges in achieving an acceptable operating band that accommodates both low and high thrust operations while balancing performance and weight, particularly with internal combustion engines that have varying RPM bands and weight compared to gas turbine engines.
Innovation Solution
A hybrid-electric propulsion system integrating an electric generator, compressor, internal combustion engine, turbine, electric power storage unit, and electric motor, with mechanical and electric power management devices to optimize power distribution and provide motive force, allowing for flexible operation across different thrust requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If IC engines are used as power source, then fuel efficiency is improved, but weight increases
Solution Approach 1:
The patent combines an IC engine with a gas turbine engine into a hybrid propulsion system. The IC engine and gas turbine are integrated to work together, where the IC engine can operate at efficient RPM ranges while the gas turbine provides additional thrust capability. This merging allows the system to achieve fuel efficiency similar to IC engines while maintaining the weight advantages of gas turbines for aircraft applications.
Solution Approach 2:
The hybrid system is designed to perform multiple functions: the IC engine can operate independently for fuel-efficient cruising, the gas turbine can provide high-thrust takeoff power, and both can work together. This multi-functionality allows the propulsion system to accommodate both low thrust operation (IC engine mode) and high thrust operation (gas turbine mode), resolving the contradiction between fuel efficiency and weight by providing context-appropriate power delivery.
2Use of energy by moving object
If IC engine RPM operating band is restricted, then fuel efficiency is improved, but adaptability to different thrust requirements deteriorates
Solution Approach 1:
The hybrid propulsion system dynamically adjusts between IC engine operation and gas turbine operation based on thrust requirements. The system can transition between different operational modes: IC engine-only for fuel-efficient cruising, gas turbine augmentation for intermediate thrust, and gas turbine-only for high-thrust takeoff. This dynamic adaptability allows the system to maintain optimal IC engine RPM for fuel efficiency while providing a wide thrust operation range through gas turbine supplementation.
Solution Approach 2:
The propulsion system uses a composite architecture combining two different engine types (IC engine and gas turbine) with complementary characteristics. The IC engine provides fuel efficiency at specific RPM bands, while the gas turbine provides broad thrust range and high-power capability. This composite approach creates a propulsion system that achieves both fuel efficiency and adaptability to different thrust requirements by leveraging the strengths of each engine type.
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 system achieves efficient and adaptable thrust operation by combining IC engines with electric components, enhancing performance and efficiency by adjusting power distribution and accommodating varying flight conditions.
Implementation Method 1
The turbine is powered by the exhaust gas flow
Implementation Method 2
The electric generator is configured to produce electrical power
Implementation Method 3
The electric motor is powered by the electrical power produced by the electric generator
Implementation Method 4
The IC engine is configured to selectively intake the flow of compressor air during operation and produce an exhaust gas flow during operation
Data Source
AI summary
A propulsion system for an aircraft is provided that includes an electric generator, a compressor, an internal combustion (IC) engine, a turbine, an electric power storage unit, and an electric motor. The compressor is configured to selectively produce a flow of compressor air at an air pressure greater than an ambient air pressure. The IC engine is configured to selectively intake compressor air during operation and produce an exhaust gas flow during operation. The turbine, powered by exhaust gas flow, is in communication with and configured to power the compressor and the electric generator. The electric power storage unit is in communication with the electric generator. The electric motor is in communication with the IC engine. The electric motor is powered by the electrical power produced by the electric generator, and the electric motor is configured to selectively provide motive force to the IC engine.