Turbine Combustor Liner Aft End Cooling via Oblique Channels
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Solution Overview
Problem
Existing turbine engine combustor assemblies face challenges in effectively cooling the aft end of the combustor liner, leading to potential thermal cracking, thermal differential stresses, and damage due to inadequate cooling, which reduces the component's lifespan and increases maintenance costs.
Innovation Solution
A combustor assembly design featuring a combustor liner with obliquely aligned channels through its aft end and an annular sleeve that circumscribes the aft end, allowing a fluid to impinge and deflect within a cavity before entering the combustion chamber, thereby facilitating temperature reduction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling air is supplied to the combustor liner using conventional channels, then the forward and middle portions of the liner are cooled effectively, but the aft end of the liner remains inadequately cooled due to its radial inward position relative to the liner-transition piece interface
Solution Approach 1:
The cooling system is segmented into multiple independent cooling channels: first cooling channels in the forward portion, second cooling channels in the middle portion, and third cooling channels in the aft end. This segmentation allows each region to be cooled independently through optimized channel configurations, with the aft end channels specifically positioned to reach radially inward areas that were previously inaccessible.
Solution Approach 2:
The third cooling channels extend in multiple directions including radially inward from the outer surface toward the inner surface, utilizing three-dimensional spatial arrangement to access the aft end region. This multi-directional channel extension solves the problem of the aft end being radially inward of the interface by creating cooling paths from multiple spatial dimensions.
2Power
If the combustor liner is operated at high temperatures to maintain combustion efficiency, then energy output is maximized, but thermal differential stresses and thermal cracking increase due to inadequate cooling of the aft end
Solution Approach 1:
Different cooling strategies are applied to different regions of the combustor liner. The forward and middle portions use conventional cooling channels, while the aft end employs specifically configured third cooling channels that extend radially inward to provide localized cooling. This local quality approach ensures that each region receives appropriate cooling based on its thermal requirements, preventing thermal differential stresses while maintaining overall combustion efficiency.
3Ease of manufacture
If conventional cooling channel configurations are used, then the combustor assembly structure is simple and easy to manufacture, but the aft end of the combustor liner cannot be effectively cooled
Solution Approach 1:
The cooling system is divided into distinct segmented channels (first, second, and third cooling channels) that can be manufactured independently using conventional machining techniques. Each segment serves a specific region of the combustor liner, with the third channels specifically configured for the aft end. This segmentation maintains manufacturing simplicity while enabling effective cooling of previously inaccessible areas.
Solution Approach 2:
The third cooling channels are configured to extend in multiple dimensions including radially inward from the outer surface toward the inner surface of the combustor liner at the aft end. This multi-dimensional channel arrangement achieves effective cooling of the radially inward aft end region while still using conventional manufacturing methods to create the complex three-dimensional channel paths.
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 design effectively cools the aft end of the combustor liner, reducing the risk of thermal cracking and damage, and enhancing the overall operational reliability and longevity of the turbine engine.
Implementation Method 1
Cooling air flowing through the second channel cools an exterior portion of the combustor liner
Implementation Method 2
a fluid channeled through the at least one opening impinges against a surface of the aft end prior to the fluid being channeled into the combustion chamber
Implementation Method 3
Cooling air entering the cooling channel is then discharged downstream into a second channel defined between a combustor liner and a flowsleeve
Data Source
AI summary
A method of assembling a combustor assembly for use in a turbine engine is provided. A combustor liner that defines a combustion chamber therein is provided. The liner includes a forward end and an aft end, wherein the aft end includes at least one channel extending therethrough. The channel is aligned obliquely with respect to a centerline extending through the aft end. A plurality of fuel nozzles are coupled to the forward end such that the fuel nozzles extend through the forward end. An annular sleeve that includes at least one opening extending radially therethrough is coupled to the aft end, wherein the sleeve substantially circumscribes the aft end such that a cavity is defined therebetween and such that a fluid channeled through the at least one opening impinges against a surface of the aft end prior to the fluid being channeled into the combustion chamber.