Aircraft Turbine Fuel Precipitate Separation for Contrail Mitigation
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Solution Overview
Problem
Turbine engines in aircraft produce combustion gases that form contrails due to water vapor condensation, which is promoted by particles in the exhaust, leading to persistent contrails that can affect climate and engine performance.
Innovation Solution
A contrail mitigation system that generates fuel precipitates like coke particles by heating hydrocarbon fuel to specific temperatures and removes them before combustion, using a heater and separator to reduce particulate matter in the exhaust.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If particles are present in exhaust gases, then water vapor condensation is promoted and contrail formation increases, but engine performance is maintained
Solution Approach 1:
The patent extracts and removes particles from the exhaust gas stream using a particulate removal system that includes a separator positioned in the exhaust path. This separation process eliminates the harmful particles that promote water vapor condensation and contrail formation, while the cleaned exhaust continues to maintain engine performance characteristics.
Solution Approach 2:
The patent changes the physical and chemical parameters of the exhaust gas by controlling the temperature, pressure, and composition through the particulate removal system. By adjusting these parameters, the system prevents water vapor condensation while maintaining the energy content and thrust characteristics of the exhaust.
2Object-generated harmful factors
If fuel precipitates are generated by heating hydrocarbon fuel, then particulate matter in exhaust is reduced, but additional energy consumption occurs
Solution Approach 1:
The patent applies preliminary action by heating the hydrocarbon fuel before combustion to generate fuel precipitates that can be removed from the fuel stream. This pre-treatment of the fuel prevents particulate matter formation during combustion, reducing the need for more energy-intensive post-combustion filtration systems.
Solution Approach 2:
The patent converts the potentially harmful effect of heating fuel (which could increase energy consumption) into a beneficial process by using the heat to precipitate and remove particles from the fuel. This transforms what would be wasted energy into a useful separation mechanism that reduces exhaust particulate matter.
3Reliability
If fuel precipitates are removed before combustion, then carbonaceous deposits are prevented, but device complexity increases
Solution Approach 1:
The patent merges the particulate removal function with existing engine components and systems. The separator is integrated into the exhaust system, and the heating function is combined with the fuel delivery system, eliminating the need for completely separate, standalone systems and reducing overall device complexity.
Solution Approach 2:
The patent designs the particulate removal system to serve multiple functions: it removes particles from exhaust gases, prevents carbonaceous deposits in the combustor, and can be controlled based on various engine operating conditions. This multi-functionality reduces the need for additional specialized components.
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
Reduces contrail formation by minimizing particles in the exhaust gases, preventing persistent contrails and maintaining engine efficiency by avoiding carbonaceous deposits.
Implementation Method 1
a heater fluidly connected to the fuel delivery assembly upstream of the combustor and selectively operable to heat the hydrocarbon fuel and to generate fuel precipitates in the hydrocarbon fuel
Implementation Method 2
a fuel precipitate separator fluidly connected to the fuel delivery assembly upstream of the combustor and downstream of the heater to separate the fuel precipitates generated by the heater from the fuel
Implementation Method 3
the fuel and air mixture being combusted in the combustor to generate combustion gases
Implementation Method 4
a core air exhaust nozzle located downstream of the combustor to receive the combustion gases and to exhaust the combustion gases from the turbine engine
Data Source
AI summary
A turbine engine for an aircraft includes a fuel delivery assembly for a hydrocarbon fuel to flow therethrough, a combustor combusting the fuel to generate combustion gases, and a core air exhaust nozzle exhausting the combustion gases from the turbine engine. The turbine engine also includes a contrail mitigation system having a heater and a fuel precipitate separator. The heater is selectively operable to heat the hydrocarbon fuel and to generate fuel precipitates in the hydrocarbon fuel, and the fuel precipitate separator separates the fuel precipitates generated by the heater from the fuel. A controller is coupled to the heater to operate the heater to heat the hydrocarbon fuel and to generate fuel precipitates in the hydrocarbon fuel in response to a contrail mitigation input.