Turbine Vane Dual Source Cooling Apertures
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Solution Overview
Problem
High-pressure turbine vanes in gas turbine engines face challenges in efficient cooling due to high operating temperatures, requiring improved cooling schemes to prevent material fatigue and failure, especially with limited cooling air availability from compressor stages.
Innovation Solution
The vane assemblies incorporate a vane platform with internal cavities and a blade outer air seal support system featuring multiple cooling flow apertures that connect to an outer diameter supply cavity, allowing high-pressure cooling air to be directed to the leading edge and lower-pressure air to the trailing edge, enhancing cooling efficiency and pressure control within the vane.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling air flow is increased to cool the vane, then cooling effectiveness is improved, but the availability of cooling air from compressor stages is limited
Solution Approach 1:
The cooling air flow path is segmented into multiple distinct routes: a first cooling flow path through the vane leading edge cavity, a second cooling flow path through the vane trailing edge cavity, and a third cooling flow path through the BOAS support. This segmentation allows different regions of the vane to receive cooling air from different compressor stages, optimizing both cooling effectiveness and air utilization.
Solution Approach 2:
Different regions of the vane are provided with different cooling characteristics: the leading edge receives high-pressure cooling air through the first cooling flow path, while the trailing edge receives lower-pressure cooling air through the second cooling flow path. The BOAS support receives cooling air through the third cooling flow path. This local differentiation allows each region to receive appropriately pressurized cooling air, resolving the contradiction between cooling effectiveness and air availability.
2Productivity
If high-pressure cooling air is directed to the leading edge, then cooling efficiency is improved, but cooling air flow distribution becomes more complex
Solution Approach 1:
The cooling air distribution system is segmented into multiple independent flow paths with dedicated apertures: the first cooling flow aperture in the vane leading edge, the second cooling flow aperture in the vane trailing edge, and the third cooling flow aperture in the BOAS support. This segmentation enables high-pressure air to be directed to the leading edge for improved cooling efficiency while maintaining a manageable, modular distribution architecture.
3Reliability
If multiple cooling flow apertures are implemented, then cooling coverage is improved, but manufacturing complexity increases
Solution Approach 1:
The BOAS support structure serves multiple functions: it provides structural support for the blade outer air seal, contains the third cooling flow aperture for cooling air delivery, and integrates with the vane assembly. This multi-functionality reduces manufacturing complexity by combining multiple features into a single component rather than requiring separate structures for each function.
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 increases the cooling air flow to vane cavities, improving thermal management and efficiency by utilizing high-pressure air effectively at the leading edge and lower-pressure air at the trailing edge, thereby reducing material stress and extending engine life.
Implementation Method 1
a cooling flow path is formed through the second cooling flow aperture and the third cooling flow aperture to fluidly connect to the outer diameter supply cavity
Implementation Method 2
the leading edge cavity is configured to receive relatively high pressure air and the trailing edge cavity is configured to receive relatively low pressure air
Data Source
AI summary
Vane assemblies for turbine engines are described. The vane assemblies include a vane having an internal cavity and a vane platform and a vane rail defining, in part, an outer diameter supply cavity. A blade outer air seal support (BOAS support) is arranged adjacent the vane and engages with a portion of the vane, the blade outer air seal support having BOAS support rail, and a BOAS supported on the BOAS support and engaging with a portion of the vane. The BOAS support includes a first cooling flow aperture configured to enable a cooling flow to cool at least the BOAS and a second cooling flow aperture formed in the BOAS support rail. The vane rail includes a third cooling flow aperture to form a cooling flow path through the second cooling flow aperture and the third cooling flow aperture to fluidly connect to the outer diameter supply cavity.