Gas Turbine Blade Platform Cooling via Vertical Chimney Feed
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Solution Overview
Problem
Gas turbine engine blade platforms face high thermal and mechanical loads due to high combustion temperatures, leading to reduced service life and increased maintenance costs, with existing cooling methods like leakage air and small cooling chambers resulting in low heat transfer coefficients and challenging feed hole placement under high stress areas.
Innovation Solution
The implementation of a cooling system that includes a pair of ribs forming a channel and a second cover plate to direct cooling air into a sealed pocket, allowing the feed opening to be located at a lower radius from the engine's centerline, reducing stress and improving heat transfer coefficients by creating a vertical chimney for easier access and drilling of the feed hole.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If small cooling chambers are used to adequately cool the platform, then cooling effectiveness is improved, but feed holes must be located in areas of high stress and difficult access
Solution Approach 1:
The patent introduces a vertical dimension by extending the cooling chamber downward from the platform into the blade structure. This allows the feed hole to be located at a lower radius where access is easier and stresses are lower, while still providing adequate cooling to the platform through the vertically extended chamber.
Solution Approach 2:
The patent introduces a channel as an intermediary element that connects the feed hole location (at lower radius) to the cooling chamber (at platform level). This channel acts as a mediator, allowing cooling air to be delivered to the platform cooling chamber without requiring the feed hole to be located in high-stress, hard-to-access areas.
2Ease of operation
If feed holes are located in the blade neck area close to the platform, then cooling air can be directly supplied to the platform, but the area experiences high stress due to platform centrifugal loads
Solution Approach 1:
The patent relocates the feed hole to a lower radial position by extending the cooling chamber vertically downward. This dimensional change allows the feed hole to be positioned in a region with lower centrifugal stresses while maintaining efficient cooling air delivery through the extended chamber and channel structure.
Solution Approach 2:
The cooling system is segmented into distinct components: the feed hole location, the connecting channel, and the cooling chamber at the platform. This segmentation allows the feed hole to be positioned in a low-stress area while the cooling function is performed at the platform level through the separated chamber structure.
3Area of stationary object
If leakage air cooling is used in a large plenum, then cooling coverage is improved, but heat transfer coefficients are low
Solution Approach 1:
The patent creates a localized cooling chamber directly beneath the platform with concentrated cooling air flow. Instead of using a large plenum with diffuse leakage cooling, the chamber provides focused cooling where it is most needed, achieving higher heat transfer coefficients through directed flow and reduced leakage paths.
Solution Approach 2:
The patent uses a cover plate to seal the cooling chamber, creating an enclosed space that directs cooling air flow efficiently. This sealed chamber configuration prevents leakage and maintains higher heat transfer coefficients compared to open plenum designs, while the cover plate can be configured in various shapes to optimize flow patterns.
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 enhances cooling efficiency by increasing heat transfer coefficients and reducing stress on the blade neck during drilling, while maintaining structural integrity and improving maintenance accessibility.
Implementation Method 1
cooling air from an inner blade channel into the cooling pocket
Data Source
Figure 1~2A
Figure 2B~3
Figure 4~5A
AI summary
A component for a gas turbine engine (10) is provided. The component having: a platform (34) secured to the component, the platform (34) having an exterior surface in fluid communication with an internal cooling pocket (40) of the platform via a plurality of cooling openings (46) located in the platform (34); a channel (76) in fluid communication with the internal cooling pocket (40); an internal cooling cavity (26) in fluid communication with the channel (76) via a feed opening (42) extending through an internal wall of the component, wherein a portion of the channel (76) and the feed opening (42) are located below the internal cooling pocket (40); and a cover plate (58) sealing the internal cooling pocket (40) and the channel (76).