Aerodynamic Peg for Multi-Fluid Combustor Injection
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Solution Overview
Problem
Inefficiencies in gas turbine engines arise from compressed air passing through gaps between combustion liners and flow sleeves, leading to performance issues due to discontinuities and turbulence caused by multiple structures injecting fluids.
Innovation Solution
A single aerodynamic peg with airfoil shape is used to inject multiple fluids, such as fuel and non-oxidant fluids, into the airflow between the combustion liner and flow sleeve, reducing structural discontinuities and turbulence by maintaining uniform airflow and preventing flame holding and flashback.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multiple structures are used to inject fluids into the combustor, then fluid injection functionality is achieved, but structural discontinuities and turbulence are created in the compressed air flow
Solution Approach 1:
The patent combines multiple fluid injection structures into a single integrated aerodynamic peg that extends through the combustion liner. This single structure incorporates multiple injection ports for different fluids (fuel, steam, air), eliminating the need for separate injection structures that would create multiple discontinuities in the air flow path.
Solution Approach 2:
The aerodynamic peg serves multiple functions simultaneously: it acts as a structural support element, provides structural support between the combustion liner and flow sleeve, and incorporates multiple fluid injection capabilities. This multi-functional design reduces the number of separate components needed while maintaining flow uniformity.
2Adaptability or versatility
If multiple separate injection structures are used, then various fluids can be injected, but device complexity and manufacturing difficulty increase
Solution Approach 1:
The patent merges multiple separate injection structures into a single aerodynamic peg component. This peg contains multiple injection ports for different fluids (fuel, steam, air) integrated within its structure, reducing the total number of components from multiple separate structures to one unified element.
Solution Approach 2:
The aerodynamic peg is designed as a universal component that performs multiple injection functions simultaneously. It includes ports for fuel injection, steam injection, and air injection, all integrated into a single structure that also provides mechanical support between the combustion liner and flow sleeve.
3Device complexity
If traditional gap flow configuration is used, then simple structure is maintained, but compressed air passes through gap creating inefficiencies and performance loss
Solution Approach 1:
The aerodynamic peg is positioned to extend into the gap between the combustion liner and flow sleeve before the compressed air reaches it. This preliminary positioning allows the peg to intercept and redirect the air flow, preventing it from passing directly through the gap where it would create inefficiencies, and channeling it through controlled injection ports instead.
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 solution enhances gas turbine engine reliability, power output, and reduces the risk of flame holding and flashback, while conserving materials and simplifying installation and manufacturing.
Implementation Method 1
A single aerodynamic peg with airfoil shape is used to inject multiple fluids, such as fuel and non-oxidant fluids, into the airflow between the combustion liner and flow sleeve, reducing structural discontinuities and turbulence by maintaining uniform airflow
Data Source
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AI summary
A system (10) includes a gas turbine combustor (16) configured to combust a fuel and an oxidant, such as O2 and O2 mixtures. The system also includes an aerodynamic peg (82) disposed in the gas turbine combustor. The aerodynamic peg includes a first passage (114) configured to convey a first fluid into the gas turbine combustor and a second passage (116) configured to convey a second fluid into the gas turbine combustor. The first fluid and second fluid are different from one another.