Integrated Strut-Vane Reduces Axial Length in Gas Turbine Case
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Solution Overview
Problem
The existing gas turbine engine case structures have limitations in efficiently managing the axial length and flow path geometry, particularly with discrete vanes and struts that do not effectively interconnect the inner and outer annular case portions, leading to suboptimal flow management and potential inefficiencies in compressor sections.
Innovation Solution
The introduction of circumferentially arranged airfoils that interconnect inner and outer annular case portions, featuring vanes and strut-vanes with aligned leading edges and varying axial lengths, solid cross-sections, and radial cavities to accommodate components like lubrication conduits, optimizing the flow path and reducing axial length.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If discrete vanes and struts are used to interconnect inner and outer annular case portions, then the case structure can accommodate components through hollow struts, but the axial length of the case structure increases
Solution Approach 1:
The patent merges the vane and strut into a single integrated strut-vane component. The strut-vane has a leading edge portion that forms the airfoil leading edge and a trailing edge portion that extends axially to interconnect the inner and outer annular case portions. This integration eliminates the axial gap that would exist between separate vanes and struts, thereby reducing the overall axial length of the case structure while maintaining the ability to accommodate components through the hollow cavity of the strut-vane.
2Ease of manufacture
If vanes and struts are axially spaced and discrete from one another, then manufacturing and assembly are simplified, but the flow path geometry and axial length are suboptimal
Solution Approach 1:
The strut-vane is manufactured as a single integrated component with a unified airfoil cross-section that transitions from the leading edge to the trailing edge. The leading edge portion and trailing edge portion are formed as one continuous structure, eliminating the need for separate vane and strut assemblies. This integration optimizes the flow path geometry by removing gaps between components while the hollow cavity design maintains ease of manufacturing by allowing modular assembly into the case structure.
3Adaptability or versatility
If hollow struts are used to accommodate components, then component passage through the case structure is enabled, but the axial length and structural complexity increase
Solution Approach 1:
The strut-vane integrates the structural airfoil function with the component accommodation function in a single component. The hollow cavity is formed within the strut-vane structure itself, allowing components to pass through radially while the leading and trailing edge portions maintain the aerodynamic flow path. This integration eliminates the need for separate struts that would extend axially beyond the vane trailing edge, thereby reducing axial length while maintaining component passage capability.
Data Source
AI summary
A gas turbine engine case structure includes inner and outer annular case portions radially spaced from one another to provide a flow path and circumferentially arranged airfoils extend radially and interconnect the inner and outer annular case portions. The airfoils include multiple vanes and multiple strut-vanes. Each vane has a vane leading edge. Each strut-vane includes a strut-vane leading edge. The vane leading edges and strut-vane leading edges are aligned in a common plane. The vanes include a first axial length and the strut-vanes include a second axial length that is at least double the first axial length.