Acoustic Damping Resonator System for Gas Turbine Combustor
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Solution Overview
Problem
Gas turbine engines face challenges in efficiently damping longitudinal mode dynamics due to resonator cracking caused by thermal gradients and residual stress, leading to high repair costs and limited tuning flexibility for lower emissions.
Innovation Solution
An acoustic damping resonator system with a resonator housing and chamber design that allows for easy replacement of resonator chambers without exposing the housing to damage, featuring a crevice joint and offset inner surfaces to reduce heating and create a flow-path discontinuity, thereby mitigating dynamics and reducing emissions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If resonators are positioned within the combustor in the area of highest heat release to be most effective, then the acoustic damping effectiveness is improved, but the resonators are exposed to significant temperatures and thermal gradients causing cracking and high repair costs
Solution Approach 1:
The resonator system is divided into separate modular components: resonator elements that can be independently installed and replaced within the combustor liner. This segmentation allows the resonators to be positioned in high-heat-release areas for effectiveness while enabling easy replacement if thermal damage occurs, without compromising the entire system
Solution Approach 2:
The resonator elements are designed as replaceable, cost-effective components that can withstand the harsh thermal environment temporarily. When thermal damage or cracking occurs, individual resonator elements can be replaced rather than replacing the entire combustor liner, reducing repair costs while maintaining acoustic damping effectiveness
2Strength
If resonators are welded directly to the combustor, then the resonators are securely positioned, but cracks form due to residual stress and thermal gradients between the weld and the liner leading to high repair costs
Solution Approach 1:
The resonator system uses separate resonator elements that can be independently secured to the combustor liner without welding the entire assembly. This segmentation allows for localized attachment methods that reduce thermal stress and enable easier replacement of individual components
Solution Approach 2:
The patent introduces an intermediary attachment mechanism between the resonator elements and the combustor liner that avoids direct welding. This intermediary connection method reduces residual stress and thermal gradient effects while maintaining secure positioning, and allows for non-destructive removal and replacement of resonator elements
3Object-generated harmful factors
If resonators are used to damp longitudinal mode dynamics, then the dynamics are reduced, but the tuning flexibility of the gas turbine engine is restricted in order to operate at lower emissions
Solution Approach 1:
The resonator system is designed with adjustable and reconfigurable characteristics, allowing the resonator elements to be tuned to different frequencies and configurations. This dynamic adaptability enables the system to maintain effective damping of longitudinal mode dynamics while providing the flexibility needed for different operating conditions and emissions requirements
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
The system effectively dampens longitudinal mode combustion dynamics, increasing the engine's operating envelope and reducing emissions by creating a more uniform flow and better mixing profiles, while minimizing repair costs through modular design and reduced thermal stress.
Implementation Method 1
Resonators have been incorporated into combustors to damp the longitudinal mode dynamics
Implementation Method 2
the resonator chamber may include one or more inner surfaces that are offset radially outward from the inner surface of the at least one resonator housing, thereby creating a flow-path discontinuity and reducing heating of the resonator chamber
Data Source
Figure 1
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AI summary
An acoustically dampened gas turbine engine (10) having a gas turbine engine combustor (12) with an acoustic damping resonator system (14) is disclosed. The acoustic damping resonator system (14) may be formed from one or more resonators (16) formed from a resonator housing (18) positioned within the gas turbine engine combustor (12) at an outer housing (20) forming a combustor basket (22) and extending circumferentially within the combustor (12). In at least one embodiment, the resonator housing (18) may include resonator chambers (26) that may be welded in place within resonator chamber (26) receivers (24) but easily replaceable without exposing the resonator housing (18) to damage. In another embodiment, an inner surface (32) of the resonator chamber (26) may be offset radially outward from an inner surface (34) of the resonator housing (18), thereby creating a flow-path discontinuity and reducing heating of the resonator chamber (26). The acoustic damping resonator system (14) may mitigate dynamics thereby increasing an engine operating envelope and decreasing emissions.