Combustor Deflector for Cooling Air Direction
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Solution Overview
Problem
The existing methods for cooling combustors in gas turbines are inadequate, as they rely on air from the compressor, which has a lower temperature than the combusted air, leading to inefficiencies in maintaining durability and stability.
Innovation Solution
A combustor assembly that includes a plurality of swirlers and a base portion with through holes, where a second fluid from the compressor is directed through these holes by a deflector to change its flow direction and enhance cooling, while also using a liner with an anti-deformation portion to manage thermal stress.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If air from the compressor is used to cool the combustor, then the cooling effect is provided, but the temperature difference between cooling air and combusted air is insufficient, reducing cooling efficiency
Solution Approach 1:
The cooling air flow is divided into two separate streams: first cooling air passing through swirlers to form CRZ, and second cooling air passing through through-holes in the base portion to cool the combustor body. This segmentation allows each air stream to serve its specific cooling function independently, maximizing the temperature difference utilization for overall cooling efficiency.
2Temperature
If cooling air flow is increased to improve cooling effect, then cooling performance improves, but flow stability in the combustor deteriorates
Solution Approach 1:
By separating the cooling air paths, the patent enables independent optimization of each flow stream. The first cooling air maintains CRZ stability through swirlers, while the second cooling air provides enhanced cooling through the base portion without disrupting the combustion zone, thus achieving both cooling performance and flow stability.
Solution Approach 2:
The base portion with through-holes acts as an intermediary structure that directs second cooling air to cool the combustor body without interfering with the primary combustion flow. This intermediary path allows cooling function to be decoupled from the main combustion flow stability requirements.
3Reliability
If conventional cooling methods are used, then the combustor operates, but thermal shock and deformation occur, reducing durability
Solution Approach 1:
The second cooling air passes through through-holes in the base portion before the combustor is fully heated, providing preliminary cooling to the combustor body. This preliminary cooling action reduces thermal shock and prevents deformation, thereby improving durability.
Solution Approach 2:
The cooling system provides localized cooling at different positions: first cooling air cools the combustion zone through swirlers, while second cooling air cools the base portion and combustor body through through-holes. This local quality differentiation addresses thermal stress in specific areas to prevent deformation and improve overall durability.
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 combustor while maintaining flow stability and reducing thermal shock, thereby improving the durability and stability of the combustor assembly.
Implementation Method 1
a deflector provided in the base portion so as to face the first through hole, thereby changing a moving direction of the second fluid
Implementation Method 2
a plurality of swirlers through which a first fluid that is a part of a fluid discharged from a compressor passes; in order to maintain the CRZ, a swirl component has to be applied to the flow
Implementation Method 3
some of air discharged from a compressor is used to cool down the combustor. The air discharged from the compressor has a temperature that is relatively lower than that of combusted air, and thus, the air is diverged from the compressor and the diverged air is used as a cooling fluid
Implementation Method 4
a liner with an anti-deformation portion to manage thermal stress
Data Source
AI summary
Provided is a combustor assembly. The combust assembly includes: a plurality of swirlers through which a first fluid that is a part of a fluid discharged from a compressor passes; a base portion, in which the plurality of swirlers are provided, comprising a first through hole formed between one swirler and another swirler from among the plurality of swirlers so that a second fluid that is another part of the fluid discharged from the compressor and different from the first fluid passes through the first through hole; and a deflector provided in the base portion so as to face the first through hole for changing a moving direction of the second fluid.