Turbine Vane Corner Stress Distribution

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Solution Overview

Problem

Turbine vanes in gas turbines face stress concentration and potential cracking issues at corner parts where the airfoil meets the inner or outer shroud, due to inadequate structural strength under increasing turbine inlet temperatures.

Innovation Solution

The design incorporates a corner part with a first round portion connected in an arc shape to the shroud, a first inclined portion extending outwardly, and a second round portion extending in an arc shape, which improves structural strength by distributing stress and preventing cracks.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Productivity

If the turbine inlet temperature is continuously increased to improve efficiency, then the power generation efficiency is improved, but the stress concentration and cracking risk at corner parts increases

Engineering Contradiction:

Improvepower generation efficiencyVSAvoidstructural reliability of corner parts

Core Design Contradiction:

ProductivityVSReliability

Solution Approach 1:

The corner part is designed with a curved surface instead of a sharp angle, where the curvature radius R satisfies 5-15mm. This curved geometry smoothly transitions the stress distribution, eliminating stress concentration points while maintaining the structural integrity needed for high-temperature operation

Inventive Principle:

Principle #14Spheroidality (Curvature)

Solution Approach 2:

The invention changes the geometric parameters of the corner part by introducing a specific curvature radius (5-15mm) that optimizes stress distribution. This parameter modification allows the structure to withstand higher temperatures and stresses without cracking, enabling increased turbine inlet temperature for improved efficiency

Inventive Principle:

Principle #35Parameter changes

2Ease of manufacture

If a simple corner design is used to reduce manufacturing complexity, then the manufacturing ease is improved, but stress concentration and cracking occur at the corner parts

Engineering Contradiction:

Improvemanufacturing simplicityVSAvoidstructural strength of corner parts

Core Design Contradiction:

Ease of manufactureVSStrength

Solution Approach 1:

The corner part employs a curved surface design with a specified curvature radius (5-15mm) that distributes stress evenly across the transition zone between the airfoil and shroud. This curved geometry eliminates stress concentration while remaining manufacturable through standard casting or forging processes

Inventive Principle:

Principle #14Spheroidality (Curvature)

Data Source

PatentUS11933192B2Turbine vane, and turbine and gas turbine including same

Publication Date: 2024.03.19 DOOSAN ENERBILITY CO LTD

AI summary

A turbine vane includes an airfoil having a leading edge and a trailing edge, an inner shroud disposed at one end of the airfoil to support the airfoil, and an outer shroud disposed opposite to the inner shroud at the other end of the airfoil to support the airfoil, wherein a corner part is formed at a portion where the airfoil and the inner shroud or the outer shroud meet, the corner part including a first round portion connected in an arc shape to the inner shroud or the outer shroud, a first inclined portion connected to the first round portion and outwardly extending in an inclined shape, and a second round portion connected to the first inclined portion and outwardly extending in an arc shape.