Combustor Liner Seal Member for Gas Turbine Cooling
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Solution Overview
Problem
Gas turbine combustors experience thermal hotspots due to core gas flow path anomalies and hardware geometries, leading to inefficient cooling and accelerated thermal degradation in gaps between adjacent liner segments.
Innovation Solution
A seal member with a specific configuration, including a center section and flanges, is positioned between adjacent liner segments and the combustor shell, utilizing impingement cooling air to prevent flow between segments and enhance cooling, with features like thermal barrier coatings and cooling air slots to manage thermal loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If gaps are disposed between adjacent liner segments to facilitate assembly and thermal expansion, then ease of manufacture is improved, but thermal hotspots occur due to inefficient cooling and accelerated thermal degradation
Solution Approach 1:
A seal member is introduced as an intermediary component between adjacent liner segments. The seal member includes a cooling air slot that directs cooling air into the gap region, acting as a mediator to deliver cooling precisely where thermal hotspots occur due to the gap geometry
Solution Approach 2:
The seal member provides localized cooling to the gap region through the cooling air slot, while the thermal barrier coating on the seal member provides localized thermal protection. This local quality approach addresses the thermal hotspot problem specifically at the gap location without requiring changes to the entire liner segment structure
2Temperature
If cooling air is impinged against the back surface of liner segments, then temperature is reduced and thermal degradation is prevented, but cooling air flow is disrupted in the gap regions between segments
Solution Approach 1:
The cooling system uses local quality by providing general impingement cooling through the liner segment back surface and additional localized cooling through the seal member's cooling air slot that targets the gap region specifically, ensuring both bulk and localized cooling effectiveness
Solution Approach 2:
The cooling air slot in the seal member acts as an intermediary cooling path that redirects cooling air into the gap region, supplementing the main impingement cooling flow and ensuring continuous cooling coverage even in the problematic gap areas
3Reliability
If thermal barrier coatings are applied to liner segments, then thermal degradation is reduced, but manufacturing complexity increases
Solution Approach 1:
The seal member is designed as a relatively simple component with a cooling air slot and thermal barrier coating, replacing the need for complex integrated cooling structures. The seal member can be manufactured and replaced independently, simplifying the overall manufacturing process while maintaining thermal protection
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 seal member effectively mitigates thermal hotspots by filling gaps and improving cooling efficiency, reducing thermal degradation and protecting the combustor components from excessive heat.
Implementation Method 1
The impingement cooling air enters the impingement cavities formed between the liner segments and the combustor shell through impingement holes disposed within the shell
Implementation Method 2
The cooling air passes through film cooling holes disposed in the liner segments (typically at an angle) to create a film of cooling air that both cools the segment surface and provides a insulating film that protects the liner surface
Implementation Method 3
features like thermal barrier coatings and cooling air slots to manage thermal loads
Data Source
Figure 1~4
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Figure 9~12
AI summary
A combustor (20) for a gas turbine engine is provided that includes a support shell (22), a forward liner segment (24), an aft liner segment (24), and a seal member (26). The support shell (22) has an interior surface (28), and exterior surface (30), and a plurality of impingement apertures (40) disposed within the shell (22). The forward liner segment (24) and aft liner segment (24) are attached to the inner surface of the shell (22). The forward liner segment (24) has an edge surface (42) extending between a face surface (28) and a back surface (40), and a seal shoulder (48). The aft liner segment (24) has an edge surface (42) extending between a face surface (38) and a back surface (40), and a seal shoulder (48). The forward liner segment (24) and the aft liner segment (24) are separated from one another by a gap. The seal member (26) is disposed within the gap. At least some of the plurality of impingement apertures (34) disposed within the shell (22) are aligned with the seal member (26) and oriented to direct cooling air to impinge on the seal member (26).