Airfoil for Second Stage Nozzle Guide Vane
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Solution Overview
Problem
Gas turbine engine designers face challenges in improving thermal efficiency and reducing emissions, as existing airfoil designs for turbine nozzle guide vanes do not adequately optimize aerodynamic performance, leading to suboptimal fuel efficiency and increased emissions.
Innovation Solution
A new airfoil geometry with a contoured three-dimensional external surface defined by Cartesian coordinates is introduced, which extends between a hub and a tip in the spanwise direction and between a leading edge and a trailing edge in the streamwise direction, enhancing aerodynamic control and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a conventional airfoil design is used for the turbine nozzle guide vane, then the manufacturing process is simpler, but the aerodynamic efficiency and thermal efficiency are suboptimal
Solution Approach 1:
The patent applies curved surface geometry to the airfoil, replacing conventional flat or simple contoured surfaces with a complex three-dimensional curved surface defined by mathematical equations. The airfoil features a curved suction side and curved pressure side that extend along the spanwise direction, creating an optimized aerodynamic profile that enhances flow control and thermal efficiency while accepting increased geometric complexity
Solution Approach 2:
The invention transitions from traditional two-dimensional airfoil cross-sections to a three-dimensional curved surface geometry. The airfoil is defined by equations that incorporate spanwise variation (z-direction), streamwise position (x-direction), and thickness distribution (y-direction), adding dimensional complexity to achieve superior aerodynamic performance and thermal efficiency
2Productivity
If the airfoil external surface contour is optimized for aerodynamic performance, then turbine efficiency increases by 1.38%, but the manufacturing precision requirements increase
Solution Approach 1:
The patent defines the airfoil geometry through mathematical parameters and equations, allowing precise control of the external surface contour. The geometry is specified by equations that define the curved suction side, curved pressure side, and thickness distribution as functions of spanwise and streamwise coordinates, enabling high-precision manufacturing through CNC machining or investment casting while achieving the 1.38% efficiency improvement
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 new airfoil design improves the second stage turbine nozzle guide vane efficiency by 1.38% compared to prior art designs, leading to increased thermal efficiency and reduced emissions.
Implementation Method 1
a new aerodynamic design of an airfoil for a second stage turbine nozzle guide vane
Data Source
AI summary
The present invention provides an airfoil a second stage nozzle guide vane having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge and a trailing edge of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.