Gas Turbine Airfoil Tip Turn Cooling Circuit

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Solution Overview

Problem

Contemporary gas turbine engine blades face issues with excessive dust or particulate matter collection due to cooling airflow elements, which reduces service life and requires additional maintenance.

Innovation Solution

Incorporating fastback turbulators within the tip turn of the airfoil's cooling circuit to enhance cooling efficiency and minimize dust accumulation by turbulating the cooling fluid flow.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If cooling airflow elements are added to enhance cooling efficiency, then cooling performance is improved, but dust collection increases

Engineering Contradiction:

Improvecooling efficiencyVSAvoiddust collection

Core Design Contradiction:

TemperatureVSObject-affected harmful factors

Solution Approach 1:

The patent changes the geometric parameters of the cooling circuit by introducing a tip turn configuration with specific curvature radius (0.05-0.15 times the airfoil chord length) and placing fastback turbulators at specific positions within the tip turn. This parameter optimization allows the cooling flow to maintain high cooling efficiency while reducing dust collection by controlling the flow pattern through the tip turn region.

Inventive Principle:

Principle #35Parameter changes

Solution Approach 2:

The patent introduces a curved tip turn configuration in the cooling circuit instead of straight channels. The curved geometry with optimized radius creates favorable flow patterns that reduce dust accumulation while maintaining cooling effectiveness. The curvature of the tip turn works in conjunction with fastback turbulators to control the cooling flow path.

Inventive Principle:

Principle #14Spheroidality (Curvature)

2Object-affected harmful factors

If fastback turbulators are added within the tip turn, then dust collection is reduced, but device complexity increases

Engineering Contradiction:

Improvedust collectionVSAvoidcooling circuit complexity

Core Design Contradiction:

Object-affected harmful factorsVSDevice complexity

Solution Approach 1:

The patent applies fastback turbulators locally only within the tip turn region of the cooling circuit rather than throughout the entire cooling passage. This localized application targets the specific area where dust accumulation occurs most, reducing overall dust collection while minimizing the addition of complex components. The turbulators are positioned at specific locations within the curved tip turn to maximize effectiveness.

Inventive Principle:

Principle #3Local quality

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 use of fastback turbulators within the tip turn of the airfoil's cooling circuit effectively reduces dust collection and improves cooling efficiency, thereby extending the airfoil's service life and reducing maintenance needs.

Implementation Method 1

At least one fastback turbulator is disposed at least partially within the tip turn

Methodology Applied

Scientific EffectTurbulence: Turbulence

Data Source

PatentUS10450874B2Airfoil for a gas turbine engine

Publication Date: 2019.10.22 GENERAL ELECTRIC CO

AI summary

A method and apparatus for an airfoil in a gas turbine engine can include an outer surface bounding an interior. At least one flow channel can be defined among one or more full-length and partial-length ribs to further define a cooling circuit within the airfoil. The cooling circuit can have at least one tip turn at the partial-length rib, having at least on fastback turbulator disposed at least partially within the tip turn.