Gas Turbine Vane Hub-and-Spoke Cooling
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Solution Overview
Problem
Existing gas turbine engine vane systems face challenges in efficiently managing aerodynamic loads and heat transfer, leading to potential material degradation and reduced performance.
Innovation Solution
The implementation of a vane assembly with composite airfoils, an inner ring, an outer ring, and spokes that form a hub-and-spoke arrangement, along with cooling air tubes and pads to transfer loads and reduce heat exposure, while pre-stressed spokes enhance load-carrying capacity and maintain structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional vane structures are used, then manufacturing is simpler, but aerodynamic load management and heat dissipation are insufficient
Solution Approach 1:
The vane is divided into multiple functional segments: blade portion, hub portion, cooling air tubes, and pads. This segmentation allows each component to specialize in specific functions - the blade handles aerodynamic loads, the hub provides structural support, and the cooling tubes manage heat dissipation, thereby improving overall reliability without excessive complexity
Solution Approach 2:
The cooling air tubes are nested within the hub portion and extend through the blade portion. This nested configuration allows the cooling system to be integrated within the structural framework, enabling heat management functionality without adding external complexity to the vane structure
2Object-affected harmful factors
If cooling air tubes are added to reduce heat exposure, then material degradation is reduced, but device complexity increases
Solution Approach 1:
Cooling air tubes serve as intermediary elements that introduce cooling air between the hot gas path and the vane structure. This intermediary cooling air layer acts as a thermal barrier, protecting the blade and hub materials from direct exposure to high temperatures, thereby reducing material degradation
Solution Approach 2:
The cooling air tubes are merged with the hub portion structure, combining the structural support function with the cooling function in a single integrated component. This merging reduces the need for separate cooling systems and minimizes overall structural complexity
3Strength
If pre-stressed spokes are used to enhance load-carrying capacity, then structural integrity is improved, but manufacturing complexity increases
Solution Approach 1:
The spokes are pre-stressed during assembly to create initial compressive forces in the blade portion and tensile forces in the spoke structure. This preliminary action of pre-stressing enhances the load-carrying capacity and structural integrity before the vane encounters operational aerodynamic loads, allowing the use of lighter materials while maintaining strength
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 effectively transfers aerodynamic loads and reduces heat-induced material degradation, enhancing the durability and performance of gas turbine engine vanes by maintaining structural integrity and cooling the components.
Implementation Method 1
cooling air tubes and pads to transfer loads and reduce heat exposure
Implementation Method 2
cooling air tubes...transfer cooling air through second stage vane assembly
Implementation Method 3
a plurality of spokes extending between the inner ring and the outer ring through the plurality of airfoils...transfer aerodynamic loads
Data Source
AI summary
One embodiment of the present invention is a gas turbine engine. Another embodiment is a gas turbine engine vane system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine vanes. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.