Integrated Guide Vane Assembly with Swept Bifurcation
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing gas turbine engine outlet guide vane assemblies struggle to effectively integrate advanced design swept and leaned guide vanes with bypass duct bifurcations, leading to aerodynamic inefficiencies and noise issues due to radially oriented bifurcations.
Innovation Solution
An integrated outlet guide vane assembly with guide vanes and bifurcations featuring non-zero lean and sweep angles, where the leading edge of the bifurcation is leaned and swept relative to the central axis, and the trailing edge of the guide vane is faired into the leading edge of the bifurcation, optimizing airflow and reducing noise.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If bifurcations are oriented radially to provide structural support and pass connections, then structural integrity and ease of manufacture are improved, but aerodynamic performance deteriorates due to flow disruption and noise generation
Solution Approach 1:
The bifurcation leading edge is designed with curved surfaces that are faired into the guide vane trailing edge, creating a smooth aerodynamic transition. This curvature eliminates sharp edges and discontinuities that would cause flow separation and noise, while maintaining the structural function of the bifurcation.
Solution Approach 2:
Different portions of the bifurcation structure have different orientations: the leading edge features lean and sweep angles optimized for aerodynamic flow, while the structural support portions can maintain radial orientation. This local differentiation allows simultaneous optimization of aerodynamic performance and structural integrity.
2Object-generated harmful factors
If guide vanes have non-zero lean and sweep angles to reduce noise and improve aerodynamics, then aerodynamic performance is improved, but device complexity increases due to integration with bifurcations
Solution Approach 1:
The guide vane and bifurcation are merged into a single integrated structure where the vane trailing edge is faired into the bifurcation leading edge. This combination eliminates the need for separate components and complex joints, reducing manufacturing complexity while maintaining aerodynamic benefits.
Solution Approach 2:
The integrated guide vane-bifurcation assembly performs multiple functions simultaneously: the guide vane portion redirects airflow and reduces noise, while the bifurcation portion provides structural support and houses mechanical/electrical connections. This multi-functionality reduces the overall number of components needed.
3Object-generated harmful factors
If bifurcations are integrated into guide vane profiles to reduce airflow disruption, then aerodynamic performance is improved, but manufacturing complexity increases
Solution Approach 1:
The fairing between the guide vane trailing edge and bifurcation leading edge uses smooth curved transitions that can be manufactured using standard aerodynamic forming techniques. This curvature approach is more manufacturable than sharp corners or complex multi-part joints while achieving superior airflow guidance.
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 solution reduces noise and enhances aerodynamic performance by optimizing the geometric sweep and lean characteristics of guide vanes and bifurcations, improving the overall efficiency and acoustic benefits of gas turbine engines.
Implementation Method 1
The guide vane comprises an airfoil having a leading edge and a trailing edge and has a non-zero angle of lean in the direction of rotation and a non-zero sweep angle relative to a line perpendicular to the central axis
Implementation Method 2
The trailing edge of the vane is faired into the leading edge of the bifurcation
Data Source
AI summary
An integrated outlet guide vane assembly for turbomachinery typically includes at least one outlet guide vane and at least one bifurcation having a leading edge and a trailing edge. The turbomachinery has a central axis of rotation and a defined direction of rotation about the axis. The guide vane comprises an airfoil having a leading edge and a trailing edge and has a non-zero angle of lean in the direction of rotation and a non-zero sweep angle relative to a line perpendicular to the central axis. The leading edge of the bifurcation has a non-zero angle of lean in the direction of rotation and a non-zero sweep angle relative to a line perpendicular to the central axis. The trailing edge of the vane is faired into the leading edge of the bifurcation.