Turbine Airfoil Tip Rail Cooling

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Solution Overview

Problem

Turbine engine components, particularly the high-pressure turbine, face challenges in efficient cooling due to the high temperature differences, which can lead to reduced performance and durability, especially in the tip regions where traditional cooling methods are less effective.

Innovation Solution

The design incorporates a thickened tip rail with cooling holes and channels that direct cooling fluid from the interior of the airfoil to outlets within the thickened portion of the tip rail, enhancing heat transfer and film cooling, while also acting as a wear surface and aerodynamic fin to improve durability and efficiency.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If traditional cooling methods are used in the tip region, then the cooling structure is simple, but the cooling effectiveness is insufficient and durability is reduced

Engineering Contradiction:

ImprovedurabilityVSAvoidcooling structure complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The tip rail is designed with a thickened portion specifically at the tip region where cooling is most needed. This local thickening creates a dedicated cooling chamber that allows for enhanced cooling effectiveness without requiring the entire airfoil to be more complex. The cooling holes are strategically positioned in this thickened portion to deliver cooling fluid directly to the critical tip area.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The cooling structure extends into the third dimension by creating a thickened portion in the tip rail that projects outward. This dimensional change allows for the formation of a cooling chamber that can accommodate cooling holes, providing a three-dimensional cooling pathway that traditional two-dimensional cooling surfaces cannot achieve.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

2Temperature

If cooling flow is increased to improve cooling effectiveness, then temperature reduction is enhanced, but specific fuel consumption increases

Engineering Contradiction:

Improvetip region temperatureVSAvoidspecific fuel consumption

Core Design Contradiction:

TemperatureVSUse of energy by moving object

Solution Approach 1:

The design changes the geometric parameters of the tip rail by creating a thickened portion with specific dimensions. This parameter change allows for optimized cooling fluid flow distribution, enabling effective cooling with reduced overall cooling flow requirements. The thickened portion acts as a flow distributor that efficiently delivers cooling fluid to the tip region without requiring excessive cooling flow from the interior.

Inventive Principle:

Principle #35Parameter changes

3Reliability

If the tip rail is thickened to improve cooling, then cooling capacity increases, but aerodynamic performance may be affected

Engineering Contradiction:

Improvecooling capacityVSAvoidaerodynamic efficiency

Core Design Contradiction:

ReliabilityVSProductivity

Solution Approach 1:

The thickening is localized specifically to the tip rail portion where cooling is needed, rather than increasing the thickness of the entire airfoil. This local quality change provides the necessary cooling capacity while minimizing the impact on aerodynamic performance. The thickened portion is strategically positioned to provide cooling without significantly altering the overall aerodynamic shape of the airfoil.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The thickened tip rail portion serves multiple functions simultaneously: it provides structural reinforcement, creates a cooling chamber for heat dissipation, and acts as an aerodynamic fin to reduce flow loss. This multi-functionality allows the structure to achieve enhanced cooling capacity while maintaining or improving aerodynamic efficiency.

Inventive Principle:

Principle #6Universality (Multi-functionality)

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 solution provides more efficient cooling of the tip region, reducing temperature gradients, improving durability, and enhancing the aerodynamic performance by minimizing flow loss and pressure differential, thus requiring less cooling flow and improving specific fuel consumption.

Implementation Method 1

at least one cooling hole with an inlet communicating with the interior, an outlet within the thickened portion on the tip rail, and a channel fluidly coupling the inlet to the outlet

Methodology Applied

Scientific EffectHeat transfer: Conduction (thermal)

Implementation Method 2

supplying a cooling fluid through a cooling channel from an interior of the airfoil to a thickened portion of a tip rail, and emitting the cooling fluid through an outlet in the thickened portion

Methodology Applied

Scientific EffectConvection: Convection

Implementation Method 3

emitting the cooling fluid through an outlet in the thickened portion... providing more efficient cooling of the tip region, reducing temperature gradients

Methodology Applied

Scientific EffectHeat absorption: Absorption (physical)

Data Source

PatentUS10830057B2Airfoil with tip rail cooling

Publication Date: 2020.11.10 GENERAL ELECTRIC CO

AI summary

An apparatus and method for cooling an airfoil tip for a turbine engine can include an airfoil, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the airfoil at the tip. A plurality of cooling holes can be provided in the tip rail at the tip. A flow of cooling fluid can be provided through the cooling holes from the interior of the airfoil to cool the tip of the airfoil.