Skewed Gas Turbine Vane Assembly Design
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Solution Overview
Problem
Existing vane assemblies in gas turbine engines face challenges in efficiently directing airflow and managing energy extraction due to limitations in design and mechanical attachment methods, which affect the overall performance and efficiency of the engine.
Innovation Solution
A vane assembly design featuring a first and second platform with stationary and variable airfoils, where the platforms are skewed relative to each other, allowing for a split line and rotational axes alignment, and mechanical attachment via bolts or ball and socket joints, enabling flexible airflow direction and energy management.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If traditional full ring vane assemblies are used, then structural integrity is maintained, but manufacturing complexity and assembly difficulty increase
Solution Approach 1:
The vane assembly is divided into multiple individual vanes rather than a single integrated full ring structure. Each vane can be manufactured independently and then assembled together to form the complete vane assembly, reducing manufacturing complexity while maintaining the structural integrity of the overall assembly through standardized connection interfaces between adjacent vanes
2Ease of manufacture
If fixed vane designs are used, then manufacturing simplicity is maintained, but airflow direction control and energy extraction efficiency are limited
Solution Approach 1:
The vane assembly incorporates variable vanes that can rotate about their longitudinal axes to change the angle of attack relative to the airflow. This dynamic adjustment capability allows the vanes to optimize energy extraction efficiency under different operating conditions while maintaining a relatively simple fixed mounting structure, thus balancing manufacturing simplicity with improved productivity
Data Source
Figure 1
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AI summary
A vane assembly (23) for a gas turbine engine includes a first platform (34), a second platform (36), and an airfoil (38) that extends radially across an annulus (100) between the first platform (34) and the second platform (36). The airfoil (38) is centered relative to a centerline axis (70) of the second platform (36) and is offset relative to a centerline axis (72) of the first platform (34). A variable airfoil (39A) is positioned adjacent to the airfoil (38) and extends at least partially beyond a mate face (44) of the second platform (36).