Radial Fuel Distributor for Hydrogen Turbine Combustion
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Solution Overview
Problem
Conventional gas turbine engines using hydrocarbon fuels face challenges in transitioning to non-carbon based fuels like hydrogen, requiring unconventional combustor and fuel injection arrangements to ensure stable combustion, desired turbine inlet temperature, and minimized emissions, while maintaining existing engine dimensions to avoid size and weight increases that impact aircraft design.
Innovation Solution
A fuel mixture distribution system for turbine engines featuring a combustor with a mixing chamber and fuel passages in an air conduit, where gaseous hydrogen fuel is mixed with air, and a secondary air inlet is introduced downstream of the fuel passages to induce a swirling airflow, preventing flashback and ensuring stable combustion across operating conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional liquid fuel atomization systems are used, then stable combustion is achieved, but the system cannot support non-carbon based fuels like hydrogen
Solution Approach 1:
The combustor is designed with a universal fuel injection system that can accommodate both conventional liquid hydrocarbon fuels and non-carbon based fuels like hydrogen. The fuel passages and mixing chambers are configured to work with different fuel types, eliminating the need for separate combustion systems for different fuel sources.
Solution Approach 2:
The system adjusts combustion parameters such as air-to-fuel ratio, injection timing, and mixing chamber geometry to optimize performance for different fuel types. By changing these parameters, the same combustor design can efficiently burn both liquid hydrocarbons and gaseous hydrogen.
2Adaptability or versatility
If existing engine dimensions are maintained, then aircraft design constraints are preserved, but fuel injection arrangements must be redesigned for hydrogen
Solution Approach 1:
The fuel injection system is nested within the existing combustor structure, with fuel passages integrated into the combustor walls and mixing chambers positioned within the existing combustion chamber volume. This nesting approach allows hydrogen fuel injection without increasing overall engine dimensions.
Solution Approach 2:
The design utilizes three-dimensional space efficiently by arranging fuel passages and mixing chambers in multiple dimensions within the existing combustor volume. This allows adequate mixing and combustion space without increasing the overall engine footprint.
3Object-generated harmful factors
If hydrogen fuel is used, then emissions are reduced, but stable combustion requires unconventional mixing arrangements
Solution Approach 1:
The mixing chamber is segmented into multiple regions with different air-to-fuel ratios, allowing precise control over combustion characteristics. This segmentation enables optimized mixing for hydrogen combustion while maintaining stability and reducing emissions.
Solution Approach 2:
A mixing chamber acts as an intermediary between the fuel injection system and the combustion chamber, where hydrogen fuel is thoroughly mixed with air before entering the combustion zone. This intermediary mixing region ensures stable combustion and reduces emissions without requiring complex direct injection arrangements.
4Device complexity
If fuel is introduced directly into the combustion chamber, then simplicity is maintained, but flashback prevention becomes difficult
Solution Approach 1:
Fuel is mixed with air in a dedicated mixing chamber before being introduced into the combustion chamber, preparing a controlled fuel-air mixture that reduces the risk of flashback. This preliminary mixing action ensures that fuel does not accumulate in the combustion chamber in a way that could cause flashback.
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 achieves stable combustion, improved durability, and reduced emissions when using hydrogen fuel, maintaining existing engine dimensions and enhancing propulsive efficiency.
Implementation Method 1
The air conduit shape is defined to achieve the desired mixing and prevent flashback at all operating conditions
Implementation Method 2
fuel flow is introduced and mixed with air in the mixing chamber
Implementation Method 3
a secondary air inlet where air is introduced into the mixing chamber downstream of the plurality of fuel passages
Data Source
AI summary
A fuel mixture distribution system for a turbine engine assembly includes a combustor that includes a combustion chamber, a fuel mixture distributor that includes an air conduit defining a mixing chamber between an air inlet and an exit opening to the combustion chamber, and a plurality of fuel passages that are disposed in the air conduit where a fuel flow is introduced and mixed with air in the mixing chamber prior to flowing through the exit opening into the combustion chamber. The air conduit shape is defined to achieve the desired mixing and prevent flashback at all operating conditions.