Turbine Nozzle Airfoil Core Shape for Cooling Optimization
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbines face challenges in achieving efficient airfoil core shapes that balance cooling flow, part life, and manufacturing requirements, particularly in the hot gas path section, where existing designs often require airfoil film cooling downstream of the nozzle throat and struggle with stress and temperature-induced changes.
Innovation Solution
A specific airfoil core shape defined by Cartesian coordinate values, which forms a complete profile through smooth continuing arcs, optimizing cooling flow and manufacturing efficiency while minimizing the need for downstream film cooling, and accommodating thermal stress and temperature changes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If conventional airfoil core shapes are used in turbine nozzles, then manufacturing is simpler, but cooling flow efficiency is insufficient requiring downstream film cooling
Solution Approach 1:
The patent applies parameter changes by modifying the geometric parameters of the airfoil core shape, specifically defining precise Cartesian coordinate values (X, Y, Z) that optimize the profile sections at different distances. This mathematical parameterization allows the airfoil to achieve superior cooling flow characteristics and impingement cooling area while maintaining manufacturability through defined coordinate systems and smooth arc connections.
2Productivity
If optimized airfoil core shapes are designed for maximum cooling, then turbine efficiency improves, but manufacturing precision requirements increase
Solution Approach 1:
The patent segments the airfoil core shape into multiple profile sections at different distances Z, where each section is defined by specific Cartesian coordinates (X, Y). This segmentation allows for optimized aerodynamic and cooling performance at each section while providing discrete manufacturing targets that can be achieved through modern manufacturing processes, balancing efficiency gains with manufacturing capabilities.
Solution Approach 2:
The patent employs continuous smooth arcs to connect the discrete coordinate points that define each profile section, creating a smoothly curved airfoil geometry. This curvature approach optimizes flow characteristics and cooling efficiency while providing a clear manufacturing guide for achieving the desired shape through arc-based fabrication methods.
3Device complexity
If airfoil core shape is optimized for impingement cooling, then downstream film cooling becomes unnecessary, but the design complexity increases
Solution Approach 1:
The patent achieves multi-functionality by designing the airfoil core shape to simultaneously provide structural support, aerodynamic performance, and optimized impingement cooling. The specific Cartesian coordinate definition enables the airfoil to maximize impingement cooling area inherent in the geometry itself, eliminating the need for separate downstream film cooling systems while maintaining a unified, manufacturable structure.
Data Source
AI summary
An article of manufacture includes an object having an airfoil core shape. The airfoil core shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1 where X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil core shape.