Combustor Liner Cooling with Opposing Flow Channels
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Solution Overview
Problem
Existing cooling systems for gas turbine combustor liners are inadequate in all conditions, failing to effectively manage heat generated by hot combustion gases.
Innovation Solution
A system featuring a combustor liner with axial cooling channels and film holes that divert air flow to provide both forced convection and film cooling, enhancing heat transfer and insulation from combustion gases.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If existing cooling systems are used for combustor liner, then the structure is simple, but the cooling effectiveness is insufficient under all conditions
Solution Approach 1:
The cooling system is segmented into multiple functional components: axial cooling channels for forced convection cooling, film holes for film cooling, and bypass openings for additional cooling air supply. This segmentation allows each component to perform a specific cooling function, achieving reliable cooling under all operating conditions while maintaining reasonable structural complexity
Solution Approach 2:
Different cooling mechanisms are applied to different regions and surfaces of the combustor liner: forced convection through axial channels for bulk cooling, film cooling through holes for surface protection, and bypass cooling for specific zones. This local quality approach ensures optimal cooling effectiveness in each region while managing overall system complexity
2Reliability
If cooling air flow is increased through the combustor liner, then the cooling efficiency improves, but the air flow management becomes more complex
Solution Approach 1:
The cooling air flow path is designed to serve multiple functions simultaneously: it provides forced convection cooling through axial channels, supplies film cooling air through film holes, and enables bypass cooling. This multi-functionality allows a single air flow system to achieve comprehensive cooling efficiency without requiring separate complex flow paths for each cooling mechanism
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 approach improves the cooling efficiency of the combustor liner, enhancing turbine performance and extending its lifespan by utilizing both forced convection and film cooling principles simultaneously.
Implementation Method 1
supplying an air flow in a first direction through an annular passage along an outer surface of the turbine combustor liner; diverting a portion of the air flow into each of a plurality of cooling channels... such that the flow of air through each of the cooling channels flows in a second direction opposite the first direction, and such that the air flowing through each of the plurality of cooling channels transfers heat away from the liner
Implementation Method 2
diverting a portion of the air flowing through each of the plurality of cooling channels through one or more film holes within each respective cooling channel to provide an insulating film of cooling air along an inner surface of the turbine combustor liner
Data Source
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AI summary
A system, in one embodiment, includes a turbine engine. The turbine engine includes a combustor that includes a hollow annular wall having a combustor liner (34). The turbine engine also includes first flow path (72) in a first direction through the hollow annular wall. The turbine engine further includes a second flow path (84) in a second direction that is opposite the first direction through the hollow annular wall. The second flow path may include one or more film holes (64) configured to supply a cooling film (86) to a downstream end portion (52) of the combustor liner (34).