Gas Turbine Combustor Flame Stabilizer Air Flow Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
In gas turbines, unstable combustion can occur due to insufficient turbulence of the air-fuel mixture, leading to fluctuations in flame position, which may result in either unstable combustion or increased NOx emissions if the flame moves downstream or the risk of flashback if it moves upstream.
Innovation Solution
A gas turbine combustor design featuring a cylindrical combustion chamber with a pilot burner at its center, surrounded by main burners, a flame stabilizer with a tapered cylinder shape, and air ejection portions that adjust the air flow direction to maintain the flame at an optimal position, ensuring stable combustion by controlling the air-fuel mixture ignition.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If the flame position is not controlled properly, then combustion stability deteriorates, but adding control mechanisms increases device complexity
Solution Approach 1:
A change member is introduced as an intermediary component between the air supply system and the flame zone. This change member modifies the air flow direction to act on the flame position, providing a simple yet effective control mechanism without requiring complex active control systems
Solution Approach 2:
The invention controls flame position by changing the direction parameter of air flow through the change member. By adjusting the air flow direction angle, the flame position can be controlled to maintain optimal combustion stability without complex mechanical or electronic control systems
2Object-affected harmful factors
If air flow direction is not adjusted, then flame position fluctuates causing harmful effects, but adding adjustment mechanisms increases device complexity
Solution Approach 1:
The change member serves as a passive intermediary that redirects air flow to counteract flame position fluctuations. This simple geometric component prevents harmful effects like flashback and NOx emissions without requiring active sensing or control systems
Solution Approach 2:
The change member is positioned to preemptively counteract potential flame position deviations by directing air flow in advance. This preliminary anti-action prevents the flame from moving to positions that would cause flashback or excessive NOx emissions
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 design stabilizes combustion by adjusting the flame position, preventing fluctuations and reducing the risk of flashback or NOx emissions, thereby enhancing the overall performance of the gas turbine.
Implementation Method 1
a first air ejection portion (81) that ejects air (A1) toward a tip end portion side outside the main burners (45), a second air ejection portion (83, 84) that circulates air (A) toward a tip end portion side outside the flame stabilizer (62) and ejects air (A2) toward an outside in a radial direction
Data Source
AI summary
A gas turbine combustor and a gas turbine include a pilot burner, a plurality of main burners, and a flame stabilizer. A first air ejection portion is adapted to eject first air toward a tip end portion side between the main burners and the flame stabilizer, a second air ejection portion is adapted to circulate second air toward a tip end portion side outside the flame stabilizer and eject the second air toward a radially outward direction, and a change member is adapted to change an ejecting direction of the second air ejected through the second air ejection portion to an axial center direction of the flame stabilizer.