Recessed Stator Vane Array for Lower Back Pressure
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Solution Overview
Problem
Existing stator vane array structures in gas turbine engines have limitations in optimizing gas flow conditions and pressure within the flowpath, leading to inefficiencies in gas turbine performance.
Innovation Solution
The introduction of a vane array structure with recessed vanes that include a first vane with a recess projecting into the airfoil, configured to reduce back pressure by providing a leakage path for gas flow, thereby optimizing the interaction of wakes and bow waves within the vane array.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If traditional stator vane array structures are used, then the gas turbine engine can maintain basic flow conditioning, but back pressure increases and gas flow efficiency decreases
Solution Approach 1:
The vane array is segmented into multiple individual vanes with recesses, allowing independent optimization of each vane's flow characteristics. The recesses create segmented flow paths that reduce wake interference and lower back pressure while maintaining efficient gas flow conditioning through each individual vane structure.
Solution Approach 2:
Each vane is designed with localized recesses at specific positions along the flowpath, creating different flow characteristics in different regions. The recesses are strategically positioned to optimize wake management and pressure distribution locally, thereby reducing overall back pressure while maintaining gas flow efficiency.
2Productivity
If vanes are designed with standard airfoil shapes, then manufacturing is simpler, but wake and bow wave sizes increase reducing performance
Solution Approach 1:
The vane structure is segmented with recesses that create distinct flow regions. These recesses generate smaller wake and bow wave sizes by segmenting the flow separation zones, thereby improving gas turbine performance while adding only moderate structural complexity through the recess features.
Solution Approach 2:
The recesses extend in the spanwise dimension of the vane airfoil, adding a third dimension to the flow control. This dimensional addition allows the recesses to interact with wakes and bow waves in a way that reduces their sizes, improving performance without requiring complex three-dimensional shaping of the entire vane.
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 recessed vane design enhances gas flow management, reducing back pressure and improving the efficiency and performance of the gas turbine engine by minimizing wake and bow wave sizes.
Implementation Method 1
configured to reduce back pressure by providing a leakage path for gas flow
Implementation Method 2
optimizing the interaction of wakes and bow waves within the vane array
Data Source
AI summary
A vane array structure for a gas turbine engine includes a first platform, a second platform, a plurality of vanes and a flowpath. Each of the vanes extends across the flowpath between the first platform and the second platform. The vanes include a first vane and a second vane disposed longitudinally next to the first vane along the flowpath. The first vane includes a first airfoil and a first recess. The first airfoil extends spanwise between a first end at the first platform and a second end at the second platform. The first airfoil extends chordwise between a leading edge and a trailing edge. The first airfoil extends laterally between a first side and a second side. The first recess projects spanwise into the first airfoil from the first end. The first recess projects chordwise into the first airfoil from the trailing edge.