Compressor Vane Airfoil Profile Using Cartesian Coordinates
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Solution Overview
Problem
Compressor airfoils in gas turbines face challenges in meeting design goals for efficiency, reliability, and loading due to inadequate coatings that are not robust or permanent.
Innovation Solution
A compressor vane airfoil with a unique nominal profile defined by Cartesian coordinate values, allowing for scalable and robust airfoil shapes that enhance aerodynamic efficiency and reduce thermal and mechanical stresses, as specified in TABLE A.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If coatings are applied on the airfoil to meet design goals, then thermal and mechanical protection is improved, but coating robustness and permanence deteriorate
Solution Approach 1:
The invention extracts and removes the coating layer from the airfoil design, transitioning to an uncoated nominal airfoil profile. This eliminates the fundamental problem of coating degradation while maintaining aerodynamic performance through optimized geometry defined by Cartesian coordinate values.
Solution Approach 2:
The invention changes the design parameters by providing specific Cartesian coordinate values (X, Y, Z) that define an optimized uncoated airfoil profile. This parameter optimization compensates for the absence of coatings by enhancing the base geometry to meet thermal and mechanical design goals without relying on protective coatings.
2Reliability
If an uncoated nominal airfoil profile is used, then coating-related failures are eliminated, but aerodynamic efficiency and stress management must be optimized through geometry
Solution Approach 1:
The invention provides optimized Cartesian coordinate values that define the uncoated airfoil geometry, carefully adjusting shape parameters to maintain aerodynamic efficiency. The specific X, Y, Z coordinate optimization ensures that the uncoated profile achieves required performance while eliminating coating dependency.
Solution Approach 2:
The invention utilizes the base airfoil material to its full potential by designing an uncoated profile that leverages the inherent properties of the airfoil material, optimizing its geometric configuration to provide both aerodynamic efficiency and thermal-mechanical resilience without additional coating layers.
3Productivity
If the airfoil profile is optimized for efficiency, then aerodynamic performance is improved, but manufacturing complexity increases due to precise coordinate specifications
Solution Approach 1:
The invention provides a universal airfoil profile definition through Cartesian coordinate values that can be scaled and applied to various airfoil sizes while maintaining optimized aerodynamic characteristics. This standardized coordinate system simplifies manufacturing by providing a single scalable design solution rather than custom profiles for each application.
Solution Approach 2:
The invention transitions from two-dimensional airfoil cross-sections to a three-dimensional coordinate system (X, Y, Z values) that fully defines the airfoil geometry including pitch and span variations. This dimensional expansion enables precise manufacturing guidance while maintaining aerodynamic optimization across the entire airfoil structure.
Data Source
AI summary
An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. 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 can be joined smoothly with one another to form a complete airfoil shape.