Feather Seal Assembly With Metered Cooling Holes
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Solution Overview
Problem
The formation of cooling holes in gas turbine engine platforms to direct cooling air to edges exposed to hot gas core flows is difficult and expensive, posing challenges in sealing and reducing wear and corrosion effectively.
Innovation Solution
A seal assembly featuring two stacked feather seals with distinct cooling holes, where the first cooling hole extends over a portion of the second cooling hole, ensuring a continuous cooling air pathway even if the seals shift, preventing airflow restriction and maintaining effective cooling across the assembly.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling holes are formed in the edges of the platform to direct cooling air, then cooling effectiveness is improved, but manufacturing difficulty and cost increase
Solution Approach 1:
The seal assembly is divided into multiple feather seal elements (first feather seal, second feather seal) that can be manufactured separately and then assembled. This segmentation allows each element to be manufactured using simpler processes while maintaining overall cooling effectiveness through the combined structure with multiple cooling holes
Solution Approach 2:
The first feather seal and second feather seal are nested within the same seal channel, with the first feather seal positioned radially outward from the second feather seal. This nesting arrangement allows multiple cooling pathways to be integrated within a confined space, achieving effective cooling without requiring complex individual component manufacturing
2Ease of manufacture
If a single cooling hole configuration is used in the seal assembly, then manufacturing is simpler, but cooling reliability decreases when seals shift
Solution Approach 1:
The first feather seal and second feather seal are pre-configured with cooling holes at specific positions and orientations before assembly. This preliminary positioning ensures that when the seals are assembled in the seal channel, the cooling holes align to form continuous cooling pathways, and any subsequent shifts within the seal channel do not restrict airflow
Solution Approach 2:
The cooling holes are designed with specific geometric parameters including different orientations (first cooling hole oriented differently from second cooling hole) and positions. These parameter variations ensure that the cooling pathways remain effective even when seals experience thermal expansion or mechanical shifts during operation
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 allows for metered cooling flow, reducing thermal corrosion and extending the operating life of vane segments by ensuring consistent airflow and sealing between segments, even during shifts, thus enhancing the durability of gas turbine engine components.
Implementation Method 1
The first cooling hole extends over at least a portion of the second cooling hole to provide a cooling air pathway across the seal assembly
Data Source
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AI summary
A seal assembly (88) includes a first feather seal (90) with a first cooling hole (94) extending through the first feather seal (90). The seal assembly (88) also includes a second feather seal (92) adjacent to the first feather seal (90). The second feather seal (92) includes a second cooling hole (96) extending through the second feather seal (92). The first cooling hole (94) is positioned over at least a portion of the second cooling hole (96).