Variable Height Trip Strips for Turbine Vane Cooling

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Solution Overview

Problem

Current turbine vane designs face challenges in achieving efficient platform cooling due to complex strain modeling and varying vane loading and temperature considerations, making it difficult to predict practical results and generalize designs across systems.

Innovation Solution

The design incorporates a circumferential platform core with chevron-shaped trip strips in a cooling passage, featuring varying trip strip heights and spacings to enhance heat transfer and cooling efficiency, using materials like ceramic or refractory metals for the core structure.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If complex strain modeling and non-linear flow analyses are used to achieve desired platform cooling results, then cooling effectiveness is improved, but design complexity and difficulty in predicting practical results increase

Engineering Contradiction:
Improveplatform cooling effectivenessVSAvoiddesign complexity
Core Design Contradiction:
TemperatureVSDevice complexity

Solution Approach 1:

The patent changes the geometric parameters of the cooling passage by incorporating trip strips with varying heights and spacings. This modifies the flow regime and heat transfer characteristics directly through geometric parameter optimization, achieving improved cooling effectiveness without requiring complex strain modeling or non-linear flow analyses.

Inventive Principle:
Principle #35Parameter changes

Solution Approach 2:

The trip strips are strategically positioned at specific locations within the cooling passage where they are most effective for generating turbulence and enhancing heat transfer. This localized modification approach improves cooling effectiveness at critical areas without requiring complex system-wide analysis.

Inventive Principle:
Principle #3Local quality

2Temperature

If trip strips of variable height are incorporated into the cooling passage to enhance heat transfer, then cooling capability is improved, but manufacturing complexity increases

Engineering Contradiction:
Improveheat transfer efficiencyVSAvoidmanufacturing complexity
Core Design Contradiction:
TemperatureVSEase of manufacture

Solution Approach 1:

The trip strips are designed as discrete, segmented elements that can be individually manufactured and then integrated into the cooling passage. This segmentation allows for simplified manufacturing of each strip component while achieving the desired variable height configuration for enhanced heat transfer when assembled.

Inventive Principle:
Principle #1Segmentation

Solution Approach 2:

The trip strips are pre-formed as separate components with specific height variations before being installed in the cooling passage. This preliminary fabrication approach simplifies the overall manufacturing process by allowing standardization of strip components and reducing the complexity of creating variable height structures directly in the final assembly.

Inventive Principle:
Principle #10Preliminary action

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

This configuration increases heat transfer and cooling capability, allowing for improved stress resistance and performance in turbine vanes by generating turbulence within the cooling passages, thus enhancing the overall efficiency and service life of gas turbine engine components.

Implementation Method 1

This configuration increases heat transfer and cooling capability, allowing for improved stress resistance and performance in turbine vanes by generating turbulence within the cooling passages

Methodology Applied
Scientific EffectTurbulence: Turbulence

Data Source

PatentEP2900967B1Turbine vane with trip strips of variable height
Publication Date: 2019.07.17 UNITED TECH CORP
  • EP2900967B1 patent drawingFigure 1
  • EP2900967B1 patent drawingFigure 2
  • EP2900967B1 patent drawingFigure 3~4

AI summary

An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.