Aircraft Combustion Chamber with Constant Hydrogen, Variable Liquid Flow
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Solution Overview
Problem
Existing aircraft combustion systems optimized for dual fuel operation suffer from inefficiencies and increased pollutant emissions due to alternating use of gaseous and liquid fuels, particularly affecting efficiency and emissions such as particulates and nitrogen oxides (NOx).
Innovation Solution
The aircraft is designed for parallel operation with a constant flow of gaseous fuel, primarily hydrogen, and variable flow of liquid fuel, optimizing engine efficiency and emissions by maintaining a consistent gaseous fuel supply during ground operations and varying liquid fuel supply based on operating phases.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If the aircraft operates alternatively with gaseous fuel and liquid fuel in separate phases, then the combustion chamber system can be designed for single-fuel optimization, but the system quality loss occurs due to the need to accommodate both fuels independently
Solution Approach 1:
The patent merges gaseous fuel and liquid fuel delivery systems into a unified parallel operation mode, where both fuels are supplied simultaneously to the combustion chamber through integrated fuel nozzles and control systems, eliminating the need for separate single-fuel system designs and maintaining high system quality
Solution Approach 2:
The fuel delivery system is designed with universal capability to handle both gaseous and liquid fuels concurrently through multi-functional fuel nozzles and a unified control architecture that can operate in various fuel combinations, thereby avoiding system quality degradation
2Ease of manufacture
If the aircraft operates alternatively with gaseous fuel and liquid fuel, then the combustion chamber can be optimized for one fuel type, but efficiency and emissions performance deteriorate due to the need to burn both fuels independently
Solution Approach 1:
The patent combines gaseous and liquid fuel streams in parallel operation within the combustion chamber, allowing the chamber to be optimized for combined fuel combustion rather than alternating single-fuel modes, thereby maintaining high energy efficiency and reduced emissions
3Ease of manufacture
If the aircraft operates alternatively with gaseous fuel and liquid fuel, then the combustion chamber can be designed for single-fuel compliance, but pollutant emissions increase due to the need to meet safety regulations for both fuels
Solution Approach 1:
The patent merges gaseous and liquid fuel combustion in a unified parallel operation system with integrated emission control measures, allowing the combustion chamber to be designed for optimized combined fuel burning that inherently reduces particulate and NOx emissions while meeting safety regulations
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 approach enhances engine efficiency and reduces pollutant emissions, particularly particulate and NOx emissions, by leveraging hydrogen's better ignition properties and stable combustion, while maintaining efficient ground operations with reduced greenhouse gas emissions.
Implementation Method 1
the gaseous fuel and the liquid fuel are supplied in parallel or alternatively to each other to a combustion chamber of at least one engine of the aircraft
Data Source
AI summary
The invention relates to a method for operating an aircraft with a gaseous fuel, in particular hydrogen, and a liquid fuel, in particular a sustainable alternative fuel and/or kerosene, wherein the gaseous fuel and the liquid fuel are supplied in parallel or alternatively to each other to a combustion chamber of at least one engine of the aircraft. An optimized method with regard to efficiency and pollutant emissions is provided in that the aircraft is operated at least temporarily with a constant flow of gaseous fuel, while the liquid fuel flow is varied.