Resonator System for Turbine Engine Combustor Liner
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing resonator systems in turbine engines face inefficiencies in both acoustic damping and cooling, leading to non-optimized performance due to uniform temperature distribution variations within the combustor section, which can result in excessive cooling in cold regions causing NOx emissions and inadequate cooling in hot regions, potentially degrading the liner integrity.
Innovation Solution
The resonator system is designed with high and low mass flow resonators aligned with hot and cold regions respectively, optimizing airflow to provide adequate cooling while maintaining acoustic performance, and additional rows of resonators are used to enhance acoustic damping and minimize airflow, thereby reducing emissions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If resonators are uniformly distributed across the combustor liner, then acoustic damping is provided, but cooling effectiveness is reduced due to excessive cooling in cold regions and inadequate cooling in hot regions
Solution Approach 1:
The patent applies local quality by varying the resonator characteristics according to the local thermal environment. Specifically, resonators in hot regions have higher mass flow rates and are positioned to provide maximum cooling, while resonators in cold regions have lower mass flow rates to avoid excessive cooling. This localized adaptation of resonator properties directly addresses the non-uniform temperature distribution problem while maintaining liner integrity.
Solution Approach 2:
The patent implements dynamics by making the resonator system adaptable to different operational conditions. The resonators can be configured with variable mass flow rates and adjustable positions, allowing the system to dynamically respond to changing temperature distributions during engine operation. This dynamic capability enables optimal cooling performance across varying flight conditions.
2Temperature
If high mass flow resonators are used in cold regions, then cooling is provided, but NOx emissions increase due to excessive cooling air
Solution Approach 1:
The patent applies local quality by matching resonator mass flow rates to the local thermal requirements. In cold regions, resonators are configured with lower mass flow rates sufficient for acoustic damping without providing excessive cooling, thereby avoiding the creation of cold wakes that lead to NOx emissions. In hot regions, higher mass flow rates are used to provide necessary cooling. This localized optimization eliminates unnecessary cooling air usage in cold regions, directly reducing NOx emissions while maintaining adequate cooling where needed.
3Reliability
If additional rows of resonators are added, then acoustic damping is enhanced, but device complexity increases
Solution Approach 1:
The patent applies segmentation by dividing the resonator system into multiple rows with distinct functions. The first row of resonators provides primary acoustic damping, while the second row provides enhanced damping and additional cooling. This segmentation allows each row to be optimized for its specific purpose, improving overall acoustic performance without requiring a complete redesign of the entire resonator system. The modular segmented structure makes the complexity manageable and the system easier to manufacture and maintain.
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 improves cooling effectiveness, reduces thermal stress, minimizes emissions, and provides more uniform temperature distribution, ensuring the liner operates within safe limits while optimizing airflow for better engine performance.
Implementation Method 1
One commonly used damping device is a resonator 24, which can be a Helmholtz resonator
Implementation Method 2
the air can pass through the holes 32 and directly impinge on the hot surface of the liner 22, thereby providing impingement cooling to the liner 22
Implementation Method 3
air entering the resonator 24 through the holes 32 in the resonator box 26 can exit the resonator 24 by flowing through the holes 38 in the liner 22. Such flow can provide a film cooling effect on the inner peripheral surface 40 of the liner 22
Data Source
Figure 1
Figure 2~3
Figure 4~6
AI summary
A resonator system for a turbine engine can improve acoustic performance and cooling effectiveness. During engine operation, a combustor liner exhibits alternating hot and cold regions in the circumferential direction corresponding to the non-uniform temperature distribution of the combustion flame. Accordingly, high flow resonators are formed with the liner in substantial alignment with the hot regions of the fluid flow within the liner, and low flow resonators are formed with the liner in substantial alignment with cold regions of the fluid flow within the liner. As a result, appropriate amounts of cooling can be provided to the liner so that cooling air usage is optimized. Alternatively or in addition, the liner can include two or more rows of resonators, which can provide an enhanced acoustic damping response. The resonators in the first row can be aligned with or offset from the resonators in the second row.