Turbine Vane Airfoil Profile for Flow Separation Control
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Solution Overview
Problem
Gas turbine engine airfoils face challenges in achieving optimal thermal and mechanical design due to flow separation, limiting compressor work and overall engine power, and require a balance between aerodynamic and structural optimization under harsh conditions.
Innovation Solution
The design of a turbine vane airfoil with an external surface formed in substantial conformance to multiple cross-sectional profiles defined by Cartesian coordinates, scaled by local axial and circumferential chords, and span location, enhancing aerodynamic and structural optimization.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If conventional airfoil designs are used, then manufacturing and structural requirements are met, but flow separation occurs which limits compressor work and engine power capability
Solution Approach 1:
The patent applies local quality by varying the airfoil geometry parameters (thickness distribution, camber, leading edge radius) at different span locations and chord positions. The coordinates in Table 1 define a three-dimensional airfoil surface where each location has optimized local properties to control flow attachment and reduce separation, thereby improving power capability while managing the harmful flow separation effect.
2Productivity
If airfoil geometry is optimized for aerodynamic performance, then flow separation is reduced and power capability increases, but thermal and mechanical design requirements become more challenging to meet
Solution Approach 1:
The patent employs parameter changes by systematically varying the airfoil geometric parameters defined in the coordinate system (axial coordinate scaled by local axial chord, circumferential coordinate scaled by local axial chord, and span location). These parameter variations optimize the airfoil shape for reduced flow separation and improved compressor work capability, while the coordinated design ensures thermal and mechanical requirements are satisfied, thereby improving productivity without compromising reliability.
3Ease of operation
If airfoil design prioritizes aerodynamic optimization, then flow regimes are improved, but structural optimization under harsh temperatures and pressures becomes more difficult
Solution Approach 1:
The patent applies universality by designing a single airfoil geometry that simultaneously satisfies multiple requirements: aerodynamic performance (flow regime optimization), structural integrity (parts life), and thermal management. The coordinated three-dimensional surface defined by the coordinates achieves multi-functionality, reducing the need for separate aerodynamic and structural optimizations and thereby simplifying the overall design complexity while improving ease of operation.
Data Source
AI summary
A turbine vane for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface. The surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.