Hybrid Aircraft Power Plant With Dual-Source Fan Gearbox
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Solution Overview
Problem
Hybrid electric aircraft propulsion systems face challenges in optimizing power distribution between thermal combustion engines and electric motors, leading to inefficiencies and oversizing of engines for take-off and climb, which affects weight and fuel consumption.
Innovation Solution
Aircraft power plants incorporating a gearbox that integrates a gas turbine engine and an electric motor, allowing for continuous power transfer and flexible operation modes, including generator and propelling modes, to optimize power distribution and reduce engine size and weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the gas turbine engine is oversized for take-off and climb phases, then sufficient power is available for all flight phases, but engine weight and fuel consumption increase
Solution Approach 1:
The power generation function is segmented between the gas turbine engine and the electric motor. The gas turbine engine is sized for cruise phase efficiency, while the electric motor provides supplemental power during take-off and climb, eliminating the need to oversize the gas turbine engine for peak power requirements.
Solution Approach 2:
The electric motor serves multiple functions: providing supplemental power during high-power phases (take-off, climb), acting as a generator during cruise to recover energy, and enabling flexible power distribution across different flight phases. This multi-functionality resolves the contradiction by allowing the gas turbine engine to be optimized for its most efficient operating point.
2Power
If the gas turbine engine is oversized for take-off and climb phases, then sufficient power is available for all flight phases, but fuel consumption increases
Solution Approach 1:
The power generation function is segmented between the gas turbine engine and the electric motor. The gas turbine engine is sized for cruise phase efficiency, while the electric motor provides supplemental power during take-off and climb, eliminating the need to oversize the gas turbine engine for peak power requirements.
Solution Approach 2:
The system dynamically changes the power contribution parameters of each propulsion source based on flight phase. During take-off and climb, the electric motor increases its power contribution; during cruise, the gas turbine engine operates at its most efficient parameter point while the electric motor may function as a generator to recover energy.
3Use of energy by moving object
If complex power distribution systems are used to optimize power between thermal and electric propulsion, then power efficiency improves, but system complexity increases
Solution Approach 1:
The gearbox merges the power outputs of the gas turbine engine and electric motor into a single unified drive system for the propeller. This mechanical integration simplifies the power distribution architecture compared to separate propulsion systems, reducing control complexity while maintaining the ability to optimize power distribution through the shared rotational interface.
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 solution enables efficient power management, reducing engine size and weight, improving aerodynamics, and enhancing fuel efficiency by allowing the electric motor to supplement the gas turbine engine, particularly during cruise phases.
Implementation Method 1
a gearbox located on a second axial side of the fan opposite the first axial side, the gearbox in driving engagement with the engine shaft, the motor shaft, and the fan, the gearbox defining a first load path between the gas turbine engine and the fan and a second load path between the electric motor to the fan
Implementation Method 2
a gas turbine engine having a compressor drivingly engaged by a turbine via an engine shaft
Implementation Method 3
the gas turbine engine driving both of the electric motor and the fan in the first configuration along the first load path and the second load path
Implementation Method 4
an electric motor powered by a power source, the electric motor driving a motor shaft
Implementation Method 5
a fan for providing power to an aircraft
Data Source
AI summary
An aircraft power plant, comprising: a fan for providing power to an aircraft; a gas turbine engine located on a first axial side of the fan, the gas turbine engine having a compressor drivingly engaged by a turbine via an engine shaft; an electric motor powered by a power source, the electric motor driving a motor shaft; and a gearbox located on a second axial side of the fan opposite the first axial side, the gearbox in driving engagement with the engine shaft, the motor shaft, and the fan, the gearbox defining a first load path between the gas turbine engine and the fan and a second load path between the electric motor to the fan, the fan in continuous driving engagement with both of the gas turbine engine and the electric motor along the first load path and the second load path.