Gas Turbine Combustor Central Lance Fuel Distribution
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Solution Overview
Problem
Existing combustor arrangements for gas turbines face challenges in efficient fuel and air distribution, flame stabilization, and maintenance, particularly in two-staged combustors, which affect serviceability and operational efficiency.
Innovation Solution
A combustor arrangement featuring a central lance body with dual fuel ducts for gaseous and liquid fuel supply, axial swirlers, and a dilution air mixer with air injection from both the lance body and the housing, allowing for staged fuel injection and improved mixing, along with a retractable design for easier maintenance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a complex fuel distribution system is used to supply both gaseous and liquid fuel, then fuel distribution efficiency is improved, but device complexity increases
Solution Approach 1:
The patent combines gaseous and liquid fuel ducts into a single integrated lance body structure. The double line ducts are adapted within the lance body to transport both fuel types, merging what would otherwise be separate complex systems into one unified component that is easier to install and maintain while maintaining efficient fuel distribution to both burners.
Solution Approach 2:
The lance body serves multiple functions: it acts as both the gaseous fuel duct and the liquid fuel duct, and also provides structural support for both burners. This multi-functional design reduces the overall number of components needed while ensuring efficient fuel supply to the two-staged combustor system.
2Stability of the object's composition
If a fixed combustor design is used, then structural stability is improved, but ease of maintenance deteriorates
Solution Approach 1:
The combustor is divided into modular sections: the lance body can be independently removed from the combustor housing, and the burners can be accessed separately. This segmentation allows maintenance personnel to service the fuel delivery system and burners without dismantling the entire combustor structure, maintaining structural stability while improving maintainability.
3Device complexity
If air is injected only from the housing, then structural simplicity is improved, but mixing efficiency deteriorates
Solution Approach 1:
The air injection system uses a nested configuration where air supply elements are positioned both inside the lance body and on the outer housing. This nested arrangement creates multiple stages of mixing: initial mixing occurs near the fuel injection points within the lance, and further mixing occurs as gases pass through the housing air injection zones, significantly improving overall mixing efficiency without requiring a completely complex external system.
4Use of energy by moving object
If high temperature combustion is used, then energy efficiency is improved, but harmful emissions increase
Solution Approach 1:
The two-staged combustion system uses periodic action by sequencing the combustion process: first gaseous fuel is burned in the initial stage, then liquid fuel is burned in the second stage. This staged approach allows for better temperature control and more complete combustion, improving energy efficiency while reducing harmful emissions through the progressive combustion sequence.
Solution Approach 2:
The system changes combustion parameters by using different fuel types (gaseous then liquid) in sequential stages, and by controlling air injection timing and quantity at each stage. This parameter control enables optimized combustion that maximizes energy efficiency while minimizing pollutant formation through proper stoichiometric control at each combustion phase.
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 configuration enhances fuel distribution, improves mixing, stabilizes flames across a wide operating range, reduces temperature for the second burner stage, and allows for cost-effective, robust, and efficient operation with reduced pollutant emissions and simplified maintenance.
Implementation Method 1
a mixer for admixing a dilution gas to the hot gases leaving the first combustion chamber during operation
Implementation Method 2
improved mixing, along with a retractable design for easier maintenance
Data Source
Figure 1
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Figure 4
AI summary
A combustor arrangement (10) for a gas turbine comprises a first burner (20), a first combustion chamber (21), a mixer (30) for admixing a dilution gas to the gases leaving the first combustion chamber (21) during operation, a second burner (60), and a second combustion chamber (40) arranged sequentially in a fluid flow connection. These elements of the combustor arrangement (10) are arranged in a row to form a flow path (27) extending between the first combustion chamber (21) and the second burner (60). The combustor arrangement (10) comprises acentral lance body (50) arranged inside the flow path and extending from the first burner (20) through the first combustion chamber (20) into the mixer (30) and into the second burner (60), wherein the lance body (50) comprises a fuel duct (28, 128, 62, 162) for providing fuel for the first burner (20) and/or for the second burner (60).