Turbine Arm Aerodynamic Profile Design for Efficiency and Stress
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
The aerodynamic profile of turbine arm connections between central hubs and shrouds in low-pressure turbines faces challenges in achieving optimal efficiency, mechanical stress distribution, and cost-effective manufacturing while ensuring turbulence-free airflow and proper mechanical connection, especially under varying temperature conditions.
Innovation Solution
An optimized aerodynamic profile for the turbine arm is defined using Cartesian coordinates, which is substantially identical to a nominal profile with minor deviations, allowing for efficient airflow, mechanical stress distribution, and cost-effective manufacturing, and can be rotated within specific angles to accommodate manufacturing tolerances and deformation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a conventional aerodynamic profile is used for the turbine arm, then manufacturing is simpler and more cost-effective, but airflow turbulence increases which reduces turbine efficiency
Solution Approach 1:
The patent applies parameter changes by precisely controlling the aerodynamic profile parameters within specified tolerances (±0.5mm for radial distance, ±5° for angular position) to optimize airflow characteristics and reduce turbulence, thereby improving turbine efficiency while maintaining manufacturability through defined parameter ranges
2Productivity
If the aerodynamic profile is optimized for efficiency, then turbine performance improves, but manufacturing precision requirements increase
Solution Approach 1:
The patent applies partial action by implementing optimization only in the critical aerodynamic zones where it provides the greatest efficiency benefit, rather than requiring perfect precision across the entire arm profile. This allows achieving significant efficiency improvements with moderate manufacturing precision requirements
3Reliability
If the arm profile is designed for optimal stress distribution, then mechanical reliability improves, but aerodynamic efficiency may be compromised
Solution Approach 1:
The patent applies local quality by designing different sections of the arm profile with optimized characteristics: the leading edge and suction surface are optimized for aerodynamic efficiency with smooth contours, while the trailing edge and root section are designed for stress distribution with appropriate thickness and reinforcement, allowing both aerodynamic and mechanical requirements to be satisfied in their respective zones
4Reliability
If thermal coatings are added to withstand temperature variations, then thermal reliability improves, but the aerodynamic profile complexity increases
Solution Approach 1:
The patent applies preliminary action by pre-designing the base aerodynamic profile with built-in thermal management features such as optimized thickness distribution and cooling passage integration before applying thermal coatings. This preliminary design reduces the complexity added by coatings, as the profile already incorporates thermal considerations in its geometry
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 optimized profile enhances the turbine's efficiency by reducing turbulence, ensuring proper mechanical connection, and withstanding mechanical and thermal stresses, while being manufacturable through existing methods, thus improving overall turbine performance and reliability.
Implementation Method 1
it should enable the turbine to provide the desired efficiency. In order to do that it must be such that the flow of air around the profile is sound, i.e. substantially such that it does not give rise to turbulence, which is harmful for overall efficiency
Data Source
AI summary
When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.