Annular Combustor Flow Path Architecture for Gas Turbine Pressure Loss Reduction
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Solution Overview
Problem
Gas turbine systems experience pressure losses and efficiency reductions due to flow path issues in the combustor section, including turning, separation, and cross-sectional area changes, which affect the flow of oxidant, fuel, and their mixture.
Innovation Solution
An annular combustor flow path architecture with a multi-stage diffuser system, including a gooseneck section and settling chamber, is designed to control pressure, velocity, and flow separation by redirecting air flow and stabilizing it before mixing with fuel, using a baffle and flow sleeves to facilitate efficient combustion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If the supply passage includes a turning portion that turns fluid flow from compressor discharge direction to upstream direction, then the annular combustor can be cooled effectively, but pressure losses increase due to flow turning
Solution Approach 1:
The supply passage is divided into multiple sections: a turning portion for directional change, a constant cross-sectional area portion for pressure maintenance, and a contraction portion for flow acceleration. Each segment performs a specific function to balance cooling effectiveness with pressure loss minimization.
Solution Approach 2:
The passage cross-sectional area is kept constant in the turning portion to maintain pressure, then contracted downstream to accelerate flow. This parameter change strategy allows the flow to turn effectively for cooling while recovering pressure through area reduction.
2Temperature
If flow is redirected through passages between liner wall and flow sleeves, then cooling efficiency improves, but flow separation occurs
Solution Approach 1:
Cooling passages are provided at specific locations where cooling is most needed, such as between the liner wall and flow sleeves. The passages are strategically positioned to cool critical areas without disrupting overall flow stability.
Solution Approach 2:
The flow sleeves and passages are designed with curved geometries that follow the natural flow patterns, reducing flow separation. The annular configuration and smooth curved surfaces help maintain attached flow while providing effective cooling.
3Speed
If the supply passage cross-sectional area is reduced to increase flow velocity, then cooling effectiveness improves, but pressure drop increases
Solution Approach 1:
The fluid flow is conditioned in advance through a constant cross-sectional area portion that stabilizes the flow before it enters the contraction portion. This preliminary action ensures uniform flow distribution, allowing the subsequent area reduction to accelerate flow efficiently with minimal pressure loss.
4Stability of the object's composition
If baffle with scoop is used to redirect flow, then flow distribution improves, but device complexity increases
Solution Approach 1:
The baffle with integrated scoop serves multiple functions: it redirects fluid flow from the turning portion, distributes flow uniformly to the combustion chamber, and supports the flow sleeves. This multi-functionality reduces the need for additional separate components, thereby limiting complexity increase.
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 solution reduces pressure drop, minimizes flow separation, and enhances combustion efficiency by maintaining constant pressure and stabilizing air flow, leading to improved performance and reduced emissions in gas turbine systems.
Implementation Method 1
A flow architecture may be utilized to direct an air flow to fuel nozzles of a combustor. The flow architecture may include a multi-stage diffuser configured to control at least one flow parameter of the air flow.
Implementation Method 2
The multi-stage diffuser configured to control at least one flow parameter of the air flow, such as pressure, velocity, and/or mixing.
Implementation Method 3
The combustor section receives and combusts a fuel with an oxidant (e.g., air) to generate hot combustion gases
Data Source
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AI summary
A system 10 including an annular combustor 12 having a first liner wall disposed circumferentially about an axis, a combustion chamber disposed circumferentially about the first liner wall, and a second liner wall disposed circumferentially about the combustion chamber. The annular combustor is configured to direct a combustion gas flow in a downstream direction through the combustion chamber away from a head end toward a turbine 28. The system also includes a supply passage configured to supply a fluid flow from a compressor 34 to the combustion chamber. The supply passage has a flow path architecture having a turning portion that turns the fluid flow from a compressor discharge direction to an upstream direction generally opposite the downstream direction of combustion gas flow.