Aircraft Propulsion Control for Contrail Mitigation
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Solution Overview
Problem
Aircraft propulsion systems, particularly those with distributed propulsion, tend to have a higher propensity for contrail formation due to high water-vapour partial pressure in exhaust, leading to significant climate warming impacts, necessitating a method to manage contrail formation effectively.
Innovation Solution
An aircraft propulsion system incorporating an engine core with a compressor and turbine, an electric motor to drive the propulsive fan and engine core compressor, and a controller that adjusts the mass flow ratio of air to combustion products to mitigate contrail formation by reducing combustion product flow and increasing electric motor power during contrail mitigation, while monitoring ambient conditions and operational variables.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If distributed propulsion units with high bypass ratio are used, then fuel efficiency and noise reduction are improved, but contrail formation propensity increases due to high water-vapour partial pressure in exhaust
Solution Approach 1:
The system dynamically adjusts engine operating parameters (thrust demand, ambient conditions) to modify the contrail factor by changing the ratio of mass flow of air to flow of combustion products, thereby reducing contrail formation propensity while maintaining fuel efficiency
Solution Approach 2:
The propulsion system uses variable geometry components and adjustable parameters to dynamically control exhaust characteristics, allowing optimization of both fuel efficiency and contrail suppression based on real-time operating conditions
2Object-generated harmful factors
If techniques for contrail suppression are implemented, then climate warming impact is reduced, but weight and energy penalties are incurred due to additional equipment
Solution Approach 1:
The control system integrates contrail mitigation functionality into the existing engine control architecture, allowing the same system to perform both conventional thrust control and contrail suppression without requiring separate dedicated equipment
Solution Approach 2:
The system uses the engine's own operational parameters and existing components to achieve contrail suppression, rather than requiring external or additional specialized equipment, thereby minimizing weight penalties
3Object-generated harmful factors
If mass flow ratio of air to combustion products is altered to mitigate contrails, then contrail formation is reduced, but power distribution and engine performance must be carefully managed
Solution Approach 1:
The control system continuously monitors ambient conditions, engine operating parameters, and thrust demand to dynamically adjust the mass flow ratio, using feedback loops to maintain optimal contrail mitigation while managing engine performance
Solution Approach 2:
The system proactively adjusts engine parameters before contrail formation occurs by predicting contrail risk based on ambient conditions and preemptively modifying the mass flow ratio to prevent contrail formation
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 effectively reduces contrail formation and climate warming impact by altering the mass flow ratio and power distribution between the propulsive fan and engine core, thereby minimizing the range of ambient conditions conducive to contrail formation and reducing the contrail factor.
Implementation Method 1
at least one electric motor arranged to drive the propulsive fan and the engine core compressor
Implementation Method 2
a combustor and a turbine driven by a flow of combustion products of the combustor
Implementation Method 3
a turbine driven by a flow of combustion products of the combustor
Data Source
AI summary
This invention concerns an aircraft propulsion system in which an engine has an engine core comprising a compressor, a combustor and a turbine driven by a flow of combustion products of the combustor. At least one propulsive fan generates a mass flow of air to propel the aircraft. An electrical energy store is provided on board the aircraft. At least one electric motor is arranged to drive the propulsive fan and the engine core compressor. A controller controls the at least one electric motor to mitigate the creation of a contrail caused by the engine combustion products by altering the ratio of the mass flow of air by the propulsive fan to the flow of combustion products of the combustor. The at least one electric motor is controlled so as to selectively drive both the propulsive fan and engine core compressor.