Gas Turbine Combustor Inclined Component for Pressure Fluctuation Control
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Solution Overview
Problem
The operation of gas turbines using fuels with high hydrogen and carbon monoxide content, such as coke oven gas and coal-derived syngas, leads to pressure fluctuations during load transitions from part-load to base-load conditions, compromising the structure reliability and operational load range of the combustor.
Innovation Solution
A gas turbine combustor design featuring a cylindrical combustor liner, a combustion chamber, and a burner with inclined components at the junction between the air hole plate and the combustor liner, which prevents recirculation flows and attached flames, ensuring stable combustion and reduced pressure fluctuations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If gas fuel containing hydrogen and carbon monoxide is used to increase power output, then productivity is improved, but pressure fluctuation occurs during load transitions causing reliability to deteriorate
Solution Approach 1:
A connecting surface is introduced as an intermediary structure between the air hole plate and combustor liner. This connecting surface acts as a mediator that prevents direct communication between the combustion chamber and the space between the air hole plate and combustor liner, thereby eliminating the pressure fluctuation mechanism while allowing the high-power gas fuel operation to continue
Solution Approach 2:
The harmful recirculation flow path is extracted or removed from the system by blocking the junction between the air hole plate and combustor liner. The connecting surface effectively takes out the problematic communication path that allowed pressure fluctuations to develop during load transitions
2Temperature
If fuel is dispersed to ensure homogeneous combustion and prevent high temperature flame, then temperature distribution is improved, but device complexity increases due to additional components
Solution Approach 1:
The connecting surface merges multiple functions into a single structural element: it serves as both the junction between the air hole plate and combustor liner and as the blocking structure to prevent recirculation flows. This integration avoids adding separate components while achieving the temperature control objective
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 effectively prevents pressure fluctuations, enhancing the structural reliability and operational load range of the gas turbine by stabilizing combustion and reducing the risk of structural deterioration during load transitions.
Implementation Method 1
A junction between the air hole plate and the combustor liner is provided with an inclined component which covers the junction and has a connecting surface connecting the air hole plate and the combustor liner
Implementation Method 2
a burner including a plurality of fuel nozzles for injecting gas fuel into the combustion chamber
Implementation Method 3
an air hole plate with a plurality of air holes for guiding compressed air into the combustion chamber
Data Source
AI summary
A gas turbine combustor of the present invention includes a cylindrical combustor liner, a cylindrical combustion chamber inside the combustor liner, and a burner that includes a plurality of fuel nozzles for injecting the gas fuel into the combustion chamber and an air hole plate with a plurality of air holes for guiding the compressed air into the combustion chamber. The air hole plate joins the combustor liner and is disposed between the fuel nozzles and the combustion chamber. The junction between the air hole plate and the combustor liner is provided with an inclined component which covers the junction and has a connecting surface connecting the air hole plate and the combustor liner.