Gas Turbine Combustor Cooling Chamber with Nested Protrusions
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Solution Overview
Problem
Gas turbines face challenges in efficiently cooling combustion nozzles within the cooling chamber, leading to potential damage from high temperatures generated during combustion.
Innovation Solution
The design incorporates a cooling chamber with a plurality of protrusions and accommodation portions on the inner and outer liners, along with a plate spring seal and transition pieces, to create an efficient cooling system that uses jet flows through cooling holes to cool the combustion nozzles, preventing damage from high temperatures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a cooling chamber is used to cool combustion nozzles, then the temperature of combustion nozzles is reduced, but the structural complexity increases due to the need for protrusions and accommodation portions between inner and outer liners
Solution Approach 1:
The cooling chamber is formed by nesting the inner liner within the outer liner, creating a hollow cooling space between them. The protrusions on the inner liner are nested within the accommodation portions on the outer liner, providing structural support while maintaining the cooling chamber integrity. This nested configuration achieves effective cooling without requiring separate, complex cooling components.
Solution Approach 2:
The protrusions are strategically positioned at specific locations on the inner liner where structural support is most needed, rather than uniformly distributing support structures throughout. The accommodation portions on the outer liner are similarly localized to match the protrusion positions. This localized approach provides necessary structural reinforcement only where required, minimizing overall complexity while maintaining cooling effectiveness.
2Strength
If protrusions are added to the inner liner for structural support, then the mechanical strength is improved, but the manufacturing precision requirements increase
Solution Approach 1:
The protrusions and accommodation portions are pre-formed as integral features of the inner and outer liners during the manufacturing process, rather than being added as separate components requiring post-assembly alignment. This preliminary formation ensures precise positioning and fit between the liners, meeting the required manufacturing precision while simplifying the assembly process.
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 effectively cools the combustion nozzles, enhancing the durability and performance of the gas turbine by maintaining optimal temperatures and reducing the risk of nozzle damage.
Implementation Method 1
a plurality of first cooling holes through which a jet flow penetrates may be formed in the outer transition piece
Implementation Method 2
a plurality of second cooling holes through which a jet flow penetrates may be formed in the outer liner
Data Source
AI summary
The present disclosure relates to a combustor comprising a plurality of combustion nozzles, a cooling chamber configured to surround the plurality of combustion nozzles, an inner liner configured to surround one end of the cooling chamber and to have a plurality of through-holes formed in a circumferential direction in an end region surrounding the one end, an outer liner configured to surround the inner liner and to be spaced apart from the inner liner at a predetermined interval, and a plurality of protrusions configured to be disposed so as to be spaced apart from each other in the circumferential direction on an outer circumferential surface of the inner liner in the end region, where some of the plurality of protrusions are spaced apart from the outer circumferential surface of the inner liner and overlap with a virtual line connecting the plurality of through-holes in a direction vertical to the outer circumferential surface.