Turbine Nozzle Solidity Optimization for Durability
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
The first stage turbine nozzle in gas turbine engines faces a harsh thermal environment due to higher absolute temperatures and enthalpy flux, leading to reduced durability and a trade-off with aerodynamic performance and fuel efficiency.
Innovation Solution
The design incorporates a first stage turbine nozzle with reduced solidity, optimized core radius ratio, and specific engine configurations that balance durability and aerodynamic performance, using the Nozzle Durability Performance Index (DPI) to guide the optimization.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the first stage turbine nozzle is exposed to higher absolute temperatures and higher enthalpy flux, then the energy extraction capability is improved, but the durability of the nozzle is reduced
Solution Approach 1:
The patent applies parameter changes by optimizing the solidity ratio and core radius ratio of the turbine nozzle to specific ranges. By changing these geometric parameters, the nozzle achieves improved durability while maintaining energy extraction capability in the harsh thermal environment.
2Reliability
If the solidity of the first stage turbine nozzle is reduced to improve durability, then the aerodynamic performance may be compromised
Solution Approach 1:
The patent resolves this contradiction by identifying an optimal range for the solidity ratio (0.2-0.8) and core radius ratio (0.9-1.3). Within these parameter ranges, the nozzle achieves both improved durability and satisfactory aerodynamic performance, eliminating the need to compromise one for the other.
3Reliability
If the core radius ratio is optimized to improve durability, then the engine configuration complexity increases
Solution Approach 1:
The patent simplifies the engineering approach by defining specific target ranges for the core radius ratio (0.9-1.3). This parameter specification provides clear design guidance that improves durability without requiring complex engine configurations or additional components.
Data Source
AI summary
A turbine engine includes a core having a fan section, a compressor section, combustion section, and turbine section in serial flow arrangement and defining an engine centerline. The turbine section has a set of turbine stages, having paired sets of non-rotating, circumferentially spaced vanes defining a respective nozzle, and rotating circumferentially spaced blades. A first stage turbine nozzle has a solidity that is a ratio of an axial chord length of the turbine vanes to the circumferential spacing between adjacent vanes.