HP Turbine Vane Airfoil Profile for Flow Separation Control
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Solution Overview
Problem
Current gas turbine engine airfoil designs face challenges in achieving optimal thermal and mechanical performance due to flow separation, leading to reduced thrust and power capability, particularly in high-pressure turbines where harsh temperatures and pressures necessitate a balance between aerodynamic and structural optimization.
Innovation Solution
A novel airfoil profile for the second stage high-pressure turbine vane is defined using Cartesian coordinate values, specifically tailored to meet design criteria by extending between platforms with a fillet radius, ensuring smooth connection and tolerance within manufacturing limits, as outlined in Tables 1 and 2.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional airfoil designs are used in high-pressure turbines, then structural strength is maintained, but aerodynamic performance deteriorates due to flow separation
Solution Approach 1:
The patent applies different geometric characteristics to different regions of the airfoil. The leading edge portion has a specific curvature radius (0.005-0.02 times the airfoil chord length) optimized for flow attachment, while the trailing edge has different dimensional ratios. This local optimization prevents flow separation in critical regions while maintaining overall structural integrity.
Solution Approach 2:
The invention defines specific parameter ranges for airfoil geometry including the leading edge curvature radius (0.005-0.02 chord length), trailing edge dimensions, and overall airfoil shape parameters. By optimizing these parameters within defined ranges, the design achieves improved aerodynamic performance while preventing flow separation in the harsh high-pressure turbine environment.
2Power
If airfoil geometry is optimized for aerodynamic performance, then thrust and power capability improve, but structural integrity may be compromised under harsh temperatures and pressures
Solution Approach 1:
The patent optimizes different portions of the airfoil with specific geometric characteristics tailored to their functional requirements. The leading edge portion uses a curvature radius of 0.005-0.02 times the chord length for aerodynamic efficiency, while maintaining adequate thickness and structural dimensions in load-bearing regions. This localized optimization allows high power capability without compromising structural integrity under thermal and pressure loads.
Solution Approach 2:
The invention employs specific curvature characteristics, particularly at the leading edge with a radius of 0.005-0.02 chord length, and smooth transitions throughout the airfoil geometry. These curved surfaces optimize flow attachment and reduce stress concentrations, simultaneously improving thrust capability and structural durability in the high-pressure turbine environment.
3Productivity
If complex airfoil profiles are designed to meet multiple design criteria, then overall engine efficiency improves, but manufacturing complexity increases
Solution Approach 1:
The patent defines specific geometric characteristics for different portions of the airfoil (leading edge with 0.005-0.02 chord length radius, intermediate sections, trailing edge) rather than using a fully complex three-dimensional surface. This segmented approach with localized optimizations achieves high engine efficiency while maintaining manufacturability through clearly defined geometric parameters for each section.
Data Source
AI summary
A two-stage high pressure turbine includes a second stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.