Transition Duct Struts for Uniform Combustor Cooling
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Solution Overview
Problem
In gas turbine combustors, the existing airflow distribution systems fail to provide uniform cooling to the combustion liner, leading to inefficient combustion and increased pressure drop due to adverse interactions between air flows from injection ports and the channel between the flow sleeve and combustion liner.
Innovation Solution
A reconfigured transition duct with an inlet ring, duct body, aft frame, bellmouth, and struts positioned between the bellmouth and inlet ring directs airflow through the bellmouth and between struts, eliminating the need for injection ports and enhancing airflow distribution to the combustion liner.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If injection ports are used to deliver cooling air to the combustion liner, then cooling air can be supplied to the combustion system, but adverse interactions occur between injection port air and channel air causing non-uniform cooling and increased pressure drop
Solution Approach 1:
The patent removes the injection ports from the flow sleeve and extracts the harmful cross-flow interaction mechanism. Instead of injecting air through ports that create adverse interactions, the system uses a reconfigured transition duct with struts that guide air flow smoothly through the combustion chamber without creating harmful flow patterns.
Solution Approach 2:
The struts serve as intermediary structures that mediate between the compressed air source and the combustion liner. These struts organize and direct the air flow in a controlled manner, preventing the adverse interactions that would occur with direct injection ports while ensuring uniform cooling distribution.
2Temperature
If compressed air is directed through injection ports in the flow sleeve, then cooling air reaches the combustion liner, but uniform airflow distribution along the combustion liner is not achieved
Solution Approach 1:
The transition duct is segmented into multiple sections with struts positioned at different locations. This segmentation allows the air flow to be divided and distributed uniformly along the length of the combustion liner, ensuring consistent cooling across all regions rather than concentrated cooling at injection port locations.
Solution Approach 2:
The struts act as intermediary flow directors that distribute air uniformly along the combustion liner. By positioning struts at specific intervals, the system achieves precise control over air distribution uniformity, effectively solving the manufacturing precision requirement for consistent cooling.
3Reliability
If injection ports are used for cooling air delivery, then the combustion system can operate, but device complexity increases due to the need for ports and tubes
Solution Approach 1:
The patent merges the cooling air delivery function into the transition duct structure itself. The struts and duct configuration that were previously separate components are integrated to form a unified air distribution system, eliminating the need for separate injection ports and tubes while maintaining reliable combustion system operation.
Solution Approach 2:
The transition duct is designed to serve multiple functions: it directs hot combustion gases to the turbine inlet, provides structural support, and distributes cooling air uniformly along the combustion liner. This multi-functionality eliminates the need for separate injection port systems, reducing device complexity while maintaining operational reliability.
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 ensures a more uniform and efficient airflow distribution along the combustion liner, improving combustion efficiency and reducing pressure drop by eliminating cross-flow interactions and enhancing cooling effectiveness.
Implementation Method 1
A reconfigured transition duct with an inlet ring, duct body, aft frame, bellmouth, and struts positioned between the bellmouth and inlet ring directs airflow through the bellmouth and between struts
Implementation Method 2
Compressed air passes between the flow sleeve and the combustion liner and along an exterior surface of the combustion liner prior to being mixed with fuel in the combustion liner. By directing compressed air over the combustion liner, the air cools the combustion liner and is pre-heated prior to combustion
Implementation Method 3
The compressed air is then directed to one or more combustors where it mixes with a fuel source to create a combustible mixture. This mixture is ignited in the one or more combustors to create a flow of hot combustion gases
Data Source
AI summary
A system for directing cooling air into a gas turbine combustor is provided. The system comprises a transition duct coupled to a flow sleeve, where air to be used for combustor cooling and in the combustion process enters a bellmouth of the transition duct, passes through a plurality of struts within the bellmouth, and is distributed to a passage located between the combustion liner and flow sleeve.