Parallel Hybrid Propulsion System Engine Wear Reduction
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Solution Overview
Problem
Current parallel hybrid propulsion systems face issues such as wear and tear on engine components due to high temperatures during take-off and climb, and they also contribute to noise and emissions, as they often operate at or near their temperature limitations to optimize efficiency.
Innovation Solution
A parallel hybrid propulsion system that includes a gas turbine engine and an electrical system, where the electrical system supplements the gas turbine engine's power output during take-off and climb, allowing the engine to operate at lower temperatures and reducing wear, while also providing a mechanical power threshold for propulsion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the gas turbine engine operates at high temperatures to optimize efficiency during take-off and climb, then the mechanical power output is sufficient, but the wear and tear on engine components increases
Solution Approach 1:
The propulsion system is segmented into two independent power sources: a gas turbine engine and an electrical motor system. This segmentation allows each component to operate in its optimal range - the gas turbine can be sized for efficiency while the electrical system provides supplemental power during high-demand phases, reducing the gas turbine's operational stress and wear.
Solution Approach 2:
The electrical motor system acts as an intermediary that supplements the gas turbine engine's output during take-off and climb. This intermediary system absorbs the extreme power demands, allowing the gas turbine to operate at lower, more durable temperatures while still meeting the mechanical power threshold through combined output.
2Power
If the gas turbine engine operates at high temperatures to meet power thresholds, then the mechanical power output is sufficient, but the noise and emissions increase
Solution Approach 1:
The power generation function is segmented between two systems, allowing the gas turbine to operate in a cleaner, quieter optimal range while the electrical motor handles peak power demands. This segmentation inherently reduces the harmful emissions and noise associated with high-temperature gas turbine operation during take-off and climb.
Solution Approach 2:
The electrical motor system replaces the mechanical combustion process during high-demand phases. By substituting electrical power for gas turbine combustion during take-off and climb, the system eliminates the noise and emissions that would otherwise be generated by high-temperature combustion while still achieving the required mechanical power output.
3Power
If the gas turbine engine is sized to meet the mechanical power threshold alone, then the power requirement is satisfied, but the engine operates at temperature limitations reducing efficiency
Solution Approach 1:
The system merges a gas turbine engine optimized for fuel efficiency with an electrical motor system. The gas turbine can be sized smaller than a conventional single-engine system because it only needs to meet a portion of the power threshold, allowing it to operate in its most efficient temperature range while the electrical system provides supplemental power when needed.
Solution Approach 2:
The gas turbine engine performs partial action by providing base power at optimal efficiency temperatures, while the electrical motor system provides excessive action during high-demand phases. This partial/excessive division allows the gas turbine to avoid operating at temperature limitations and maintain peak efficiency throughout all flight phases.
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 reduces engine component wear and noise emissions by maintaining lower engine temperatures and ensuring sufficient mechanical power for take-off and climb, thereby extending engine life and minimizing environmental impact.
Implementation Method 1
a turbine configured to be driven by the combustor and to produce a first mechanical power output for rotation of a drive shaft of the gas turbine engine
Implementation Method 2
an electrical system including an electrical motor, the electrical motor configured to produce a second mechanical power output for rotation of the drive shaft of the gas turbine engine
Data Source
AI summary
A method for operation of a hybrid propulsion system is provided that includes providing a hybrid propulsion system including a gas turbine engine, an electrical system, and a controller configured to cause the gas turbine engine to produce a first mechanical power output and to cause the electrical system to produce a second mechanical power output. The method further includes causing the gas turbine engine to produce the first mechanical power output and causing the electrical system to produce the second mechanical power output, which causes a drive shaft of the gas turbine engine to rotate. The method further includes decreasing production of the first mechanical power output when a combination of the first mechanical power output and the second mechanical power output for take-off or climb is a predetermined percentage of a predetermined parameter of the gas turbine engine.