Gas Turbine Vane Axial Cooling Ribs Prevent Panel Bulge
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Solution Overview
Problem
Existing gas turbine engine cooling schemes face challenges in efficiently cooling components due to casting size limitations and interference from stiffening features that prevent pressure and suction side walls from bulging, while maintaining minimal weight and ensuring effective flow distribution.
Innovation Solution
A turbine vane design incorporating a baffle system with axial standoff ribs and a structural rib that ties the pressure and suction sides together, allowing axial cooling flow while preventing panel bulge, using refractory metal cores and additive manufacturing for complex geometries and materials like nickel-based superalloys.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If axial flow baffle designs are used to cool the component, then cooling efficiency is improved, but the pressure and suction side walls may bulge due to lack of stiffening
Solution Approach 1:
The airfoil is divided into multiple regions with axial standoff ribs creating segmented cooling passages. These ribs segment the flow while providing structural support, allowing the baffle design to cool the component without causing side wall bulge.
Solution Approach 2:
Axial standoff ribs serve as intermediary structures between the cooling flow and the side walls. These ribs mediate by providing stiffening to prevent bulge while allowing the cooling flow to pass through the axial passages efficiently.
2Stability of the object's composition
If stiffening features are added to prevent side wall bulge, then structural stability is improved, but flow interference increases and weight increases
Solution Approach 1:
Axial standoff ribs are placed locally at specific positions along the airfoil where stiffening is most needed. This localized approach provides structural support without unnecessarily complicating the flow paths in other regions, minimizing overall flow interference.
Solution Approach 2:
The stiffening is provided in the axial dimension through standoff ribs rather than through complex three-dimensional structures. This dimensional approach simplifies the overall design by using straightforward axial features rather than complicated multi-directional stiffening elements.
3Temperature
If dedicated cooling flow is implemented in multiple regions, then cooling coverage is improved, but device complexity increases
Solution Approach 1:
The axial flow baffle design serves multiple functions simultaneously: it provides cooling flow distribution, structural stiffening through standoff ribs, and flow direction control. This multi-functionality eliminates the need for separate dedicated cooling circuits in different regions, simplifying the overall design while maintaining comprehensive cooling coverage.
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 design effectively maintains component stiffness, allows axial cooling flow with minimal pressure loss, and can be applied to various engine components, enhancing cooling efficiency and structural integrity.
Implementation Method 1
Cooling of engine components is performed via communication of cooling flow through airfoil cooling circuits
Implementation Method 2
stiffening features are utilized to tie the pressure and suction side walls together which may further interfere with the flow
Data Source
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AI summary
A component for a gas turbine engine. The component includes: a first multiple of axial standoff ribs (110) that extend from a first sidewall (106); a second multiple of axial standoff ribs (110) that extend from a second sidewall (108); and a structural rib (130) that extends between the first multiple of axial standoff ribs (110) and the second multiple of axial standoff ribs (110).