Turbofan Stator Airfoil Forward Sweep Asymmetric Bow
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Solution Overview
Problem
Conventional airfoils in gas turbine engines face challenges in efficiently turning tangentially flowing air from the fan exit to the axial direction with minimal losses, leading to increased pressure losses and suboptimal flow conditions in the compressor section.
Innovation Solution
The airfoil design incorporates features such as forward sweep, increased chord, and asymmetric bow to redirect tangential airflow towards the inner or outer diameter edges, reducing pressure losses and improving flow alignment with the axial direction, thereby minimizing the turning required by subsequent inlet guide vanes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional airfoils are used in the fan exit stator, then the structure is simple and easy to manufacture, but the pressure losses increase and flow alignment to the axial direction is suboptimal
Solution Approach 1:
The airfoil is segmented into distinct functional zones: a leading edge portion with forward sweep for capturing tangential flow, a mid-section with asymmetric bow for flow redirection, and a trailing edge portion for flow completion. This segmentation allows each zone to address specific flow control objectives, reducing overall pressure losses while maintaining manufacturing feasibility through modular design
Solution Approach 2:
The airfoil employs asymmetric bow in its mid-section, where the curvature differs between the suction and pressure surfaces. This asymmetry creates differential pressure distribution that effectively redirects tangential airflow toward the axial direction, improving flow alignment and reducing pressure losses without requiring complex additional components
2Ease of operation
If conventional airfoils with standard geometry are used, then manufacturing is easier, but the turning of tangential airflow to axial direction is insufficient
Solution Approach 1:
The airfoil incorporates variable geometric parameters along its span, including changing sweep angles, bow magnitudes, and chord distributions. This dynamic geometry allows the airfoil to adapt to varying flow conditions across different radial positions, optimizing flow alignment efficiency while using standard manufacturing techniques for each sectional profile
Solution Approach 2:
The invention changes key geometric parameters of the airfoil: increasing the sweep angle at the leading edge, modifying the bow magnitude and distribution, and adjusting chord lengths. These parameter changes enhance the airfoil's ability to turn tangential flow to axial direction, improving operation efficiency without fundamentally altering the manufacturing process
3Power
If the fan creates high turning of airflow, then propulsion is enhanced, but tangential or circumferential air flow is generated that requires additional turning by stator blades
Solution Approach 1:
The airfoil design performs preliminary flow conditioning by incorporating forward sweep and asymmetric bow that begin redirecting tangential airflow toward the axial direction before the flow enters the compressor. This preliminary action reduces the turning burden on subsequent stator blades and inlet guide vanes, maintaining propulsion efficiency while simplifying downstream component requirements
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 design enhances airflow alignment, reduces pressure losses, and optimizes the turning of airflow into the compressor section, resulting in lower tangential velocities and improved efficiency.
Implementation Method 1
The airfoil design incorporates features such as forward sweep, increased chord, and asymmetric bow to redirect tangential airflow towards the inner or outer diameter edges, reducing pressure losses and improving flow alignment with the axial direction
Data Source
Figure 1
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Figure 3A~3B
AI summary
A gas turbine engine component is described. The gas turbine engine component includes an inner diameter edge (110, 200, 202), an outer diameter edge (208), a trailing edge (102) and a leading edge (100). The leading edge (100) has a positive (aft) aerodynamic sweep across substantially an entire span of the leading edge (100). The gas turbine engine component has a camber angle greater than 50 degrees across substantially an entire span of the component. The gas turbine engine component may have asymmetrical tangential stacking of the component in the radial direction.