Rear Fuselage Propulsion System Electrical Drive Integration
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Solution Overview
Problem
Aircraft propulsion systems integrated into the rear fuselage face challenges in maintaining minimum thrust and robustness, particularly in the event of system failures, while also needing to reduce polluting emissions from fossil fuel combustion.
Innovation Solution
The integration of an electrical drive device that transforms energy from gas generators into electrical power to assist turbine rotors, providing a combination of aerodynamic and electrical energy, which enhances robustness and reduces fossil fuel use, including the use of electric energy storage for extended flight phases and emergency power.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the propulsion system uses only aerodynamic energy from gas generators, then the system structure is simple, but the minimum thrust level cannot be maintained and robustness is reduced in case of failure
Solution Approach 1:
The patent combines aerodynamic energy from gas generators with electrical energy from an electrical drive device to rotate the turbine rotor. This merging of two energy sources (aerodynamic and electrical) ensures that the propulsion system can maintain minimum thrust levels and achieve robust operation even when one energy source is insufficient or unavailable, thereby resolving the contradiction between reliability and device complexity.
Solution Approach 2:
The turbine rotor is designed to be capable of rotating through multiple mechanisms: aerodynamic action from gas generator flow, electrical drive from the electrical drive device, or a combination of both. This multi-functionality allows the system to adapt to different operational conditions and maintain reliability while managing complexity through a unified rotor design.
2Object-generated harmful factors
If the propulsion system relies solely on fossil fuel combustion, then the system is simple to operate, but polluting emissions increase
Solution Approach 1:
The patent changes the energy parameter by introducing electrical energy as a supplement or alternative to fossil fuel combustion. The electrical drive device can rotate the turbine rotor without requiring fossil fuel combustion, thereby reducing or eliminating polluting emissions while maintaining the energy consumption needed for propulsion.
Solution Approach 2:
The patent substitutes part of the mechanical/aerodynamic energy conversion system with an electrical drive system. Instead of relying entirely on fossil fuel combustion to drive the turbine rotor, an electrical motor can directly rotate the rotor, replacing the combustion-based mechanical energy conversion and thereby reducing harmful emissions.
3Force
If the turbine rotor rotates only through aerodynamic action from gas generators, then the system is simpler, but minimum thrust level and robustness are compromised
Solution Approach 1:
The patent merges aerodynamic action from gas generators with electrical drive action to rotate the turbine rotor. This combination of two rotation mechanisms ensures that the turbine rotor can achieve and maintain the necessary rotational speed for minimum thrust levels, while the unified rotor design manages the complexity of accommodating multiple drive mechanisms.
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 solution maintains minimum thrust levels, improves propulsion system robustness, and significantly reduces polluting emissions by utilizing electrical assistance and energy storage to support turbine operation during various flight phases and in case of system failures.
Implementation Method 1
at least one electrical generator configured to transform a part of the energy of the flow coming from the gas generators into electrical power
Implementation Method 2
an electric motor supplied by said electrical generator and capable of rotating at least one of the turbine rotors
Data Source
AI summary
The invention relates to an aircraft propulsion system (100) intended for being built into the rear of an aircraft fuselage, the propulsion system comprising at least two gas generators (102a, 102b) supplying a power turbine (104) having two counter-rotating turbine rotors (104a, 104b) for driving two fans (112a, 12b), and separate air inlets (106a, 106b) for supplying each gas generator, characterised in that it comprises an electrical drive device (140) configured to rotate at least one of the turbine rotors, at least one electrical generator (142a, 142b) configured to transform part of the energy of the flow from the gas generators into electrical power and an electric motor (146) supplied by said electrical generator and capable of rotating at least one of the turbine rotors, said electrical generator being installed on one of said gas generators, and in that said turbine rotor is capable of being rotated simultaneously by a flow from said gas generators and by the electrical drive device.