Supercritical CO2 Gas Turbine Combustor Liners for Stable Flames
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Solution Overview
Problem
In supercritical CO2 gas turbines, the vertical silo-type combustor with a diffusion combustion system experiences unstable combustion due to interference between the flow fields of adjacent fuel-oxidant supply mechanisms, leading to increased concentrations of unburnt components and reduced combustion efficiency.
Innovation Solution
The design includes a combustor structure where each fuel-oxidant supply mechanism forms a stable flame in a separate combustor liner, with the fuel and oxidant being ejected through distinct channels to minimize interference, using a diffusion combustion system and incorporating a swirling component to promote stable mixing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If multiple fuel-oxidant supply mechanisms are arranged adjacently to secure required heat quantity, then the heat output is sufficient, but the flow fields of adjacent mechanisms interfere with each other causing unstable combustion
Solution Approach 1:
The invention divides the combustion system into multiple independent combustor liners, each housing a separate fuel-oxidant supply mechanism. This segmentation isolates the flow fields of adjacent mechanisms within their respective liners, preventing interference while maintaining sufficient total heat output through the combined capacity of multiple liners.
2Reliability
If a diffusion combustion system is adopted to prevent automatic ignition in premixed gas supply pipes, then safety is improved, but combustion efficiency decreases due to increased unburnt components
Solution Approach 1:
The invention introduces a swirling flow component locally at the fuel-oxidant supply outlets to enhance mixing and promote more complete combustion. This local modification of flow characteristics within the diffusion combustion system improves combustion efficiency by reducing unburnt components, while the overall diffusion combustion mode maintains safety by preventing automatic ignition in supply pipes.
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 stabilizes combustion, enhances combustion efficiency, and reduces the concentration of unburnt components, ensuring consistent operation and improved heat output.
Implementation Method 1
a fuel supply part which supplies the fuel and an oxidant supply part which supplies the oxidant from around the fuel supply part
Implementation Method 2
the fuel and an oxidant ejected from one fuel-oxidant supply mechanism are combusted in one space in one combustor liner
Implementation Method 3
incorporating a swirling component to promote stable mixing
Data Source
Figure 1
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AI summary
A combustor structure 1 of an embodiment is disposed to penetrate, from a direction perpendicular to an axial direction of a turbine rotor 97 in a suprecritical CO2 gas turbine which uses supercritical CO2 for a working fluid, a casing of the suprecritical CO2 gas turbine. The combustor structure 1 includes a plurality of combustors 50. Each of the combustors 50 includes: a combustor liner 51 in a cylindrical shape, which combusts fuel and an oxidant; a fuel supply part 52 which is provided at an upstream end of the combustor liner 51 and supplies the fuel into the combustor liner; and an oxidant supply part 53 which is provided at the upstream end of the combustor liner 51 and supplies the oxidant into the combustor liner.