Gas Turbine Vane Platform Cooling Passage Design
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Solution Overview
Problem
Current gas turbine engine turbine vane cooling arrangements face challenges in efficiently managing high operating temperatures, particularly in high-pressure vane sections, where traditional film cooling methods may not adequately distribute cooling air to all surfaces, leading to inefficiencies and potential damage from thermal stress.
Innovation Solution
The proposed solution involves a stator vane design with radially spaced inner and outer platforms connected by airfoils, featuring radial cooling passages without plug welds, multiple dead-end radial passages, and elongated ribs for structural support and convection cooling, which allows for effective distribution of cooling fluid through the vane structure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional film cooling holes are machined into internal passages or non-flow path pocket surfaces, then cooling is provided to specific surfaces, but cooling air distribution to all surfaces is inadequate leading to thermal stress damage
Solution Approach 1:
The cooling system is segmented into multiple independent cooling passages (first cooling passage and second cooling passage) that separately serve different surfaces of the vane. The first cooling passage provides cooling air to the flow path surface through film cooling holes, while the second cooling passage provides cooling air to the non-flow path surface, ensuring adequate cooling distribution to all surfaces and preventing thermal stress damage.
Solution Approach 2:
Different cooling strategies are applied to different locations of the vane based on their specific thermal requirements. The flow path surface receives film cooling through strategically positioned holes, while the non-flow path surface receives convection cooling through a dedicated passage, optimizing cooling effectiveness for each specific surface condition.
2Strength
If a single core portion extends through an annular flange with dead-ended passages, then structural support is provided, but no film cooling holes are connected to these passages reducing cooling effectiveness
Solution Approach 1:
The core structure is segmented into multiple functional components: a first core portion providing structural support, a second core portion creating the first cooling passage with film cooling holes for the flow path surface, and a third core portion creating the second cooling passage for the non-flow path surface. This segmentation allows each core portion to serve its specific function effectively.
Solution Approach 2:
The core structure serves multiple functions simultaneously: it provides structural support through the first core portion, enables film cooling of the flow path surface through the second core portion and film cooling holes, and enables convection cooling of the non-flow path surface through the third core portion and second cooling passage.
3Temperature
If radial cooling passages are implemented without plug welds, then cooling air distribution is improved, but manufacturing complexity increases
Solution Approach 1:
Multiple cooling functions are merged into an integrated core structure during the casting process. The first cooling passage, second cooling passage, and their associated film cooling holes are all formed simultaneously as part of the single core structure, eliminating the need for separate plug weld operations and reducing manufacturing complexity while maintaining improved cooling air distribution.
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 design enhances thermal management by ensuring uniform cooling distribution across the vane surfaces, reducing weight and maintaining structural integrity while improving the engine's compactness and power density.
Implementation Method 1
radial cooling passages without plug welds, multiple dead-end radial passages, and elongated ribs for structural support and convection cooling
Implementation Method 2
frequently require film cooling on flow path surfaces. Film cooling is facilitated by machining cooling holes to an internal passage or non-flow path pocket surface
Implementation Method 3
elongated ribs for structural support and convection cooling
Data Source
Figure 1~5
Figure 2
Figure 3~4
AI summary
A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.