Turbine Vane Cooling Platform With Segmented Passageways

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Solution Overview

Problem

Gas turbine engines face high thermal loads due to combustion processes, which can affect the durability and efficiency of turbine blades, and existing cooling systems may not adequately address these thermal challenges.

Innovation Solution

A turbine vane cooling system is introduced, featuring a platform with linear fluid passageways, access ducts, and outlet apertures, where fluid flow is directed from the passageways to the combustion flow path through outlet apertures, and plugs form a fluid-tight seal in the access ducts to optimize cooling efficiency.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If existing cooling systems are used, then cooling is provided to turbine blades, but heat transfer and pressure drop are not optimized

Engineering Contradiction:
Improvecooling efficiencyVSAvoidpressure drop
Core Design Contradiction:
TemperatureVSLoss of energy

Solution Approach 1:

The cooling system is segmented into distinct functional zones: access ducts for fluid introduction, linear fluid passageways for controlled flow distribution, and outlet apertures for targeted discharge. This segmentation allows optimization of heat transfer in each zone while minimizing overall pressure drop through efficient flow path design.

Inventive Principle:
Principle #1Segmentation

Solution Approach 2:

The system provides localized cooling by directing fluid through linear passageways to specific outlet apertures positioned at critical heat zones on the turbine blade. This local quality approach ensures cooling is applied precisely where thermal loads are highest, maximizing cooling efficiency while minimizing energy loss in non-critical areas.

Inventive Principle:
Principle #3Local quality

2Reliability

If complex cooling system geometries are manufactured using traditional methods, then cooling functionality is achieved, but manufacturing costs and complexity increase

Engineering Contradiction:
Improvecooling system functionalityVSAvoidmanufacturing cost
Core Design Contradiction:
ReliabilityVSEase of manufacture

Solution Approach 1:

The manufacturing process merges additive layer manufacturing with mechanical material removal to create the cooling system. Additive manufacturing builds the complex three-dimensional geometry of the platform, access ducts, and linear passageways in a single integrated structure, while mechanical removal refines critical surfaces and features. This combination achieves complex cooling geometries with reduced manufacturing steps and lower costs compared to traditional methods.

Inventive Principle:
Principle #5Merging (Combining)

Solution Approach 2:

The additive layer manufacturing process preliminarily creates the near-final complex geometry of the cooling system, including the platform structure, access ducts, and linear fluid passageways. This preliminary action eliminates the need for multiple complex machining operations, reducing manufacturing time and cost while maintaining the required cooling functionality.

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 cooling system effectively delays cooling until the fluid reaches the target location, reducing heat transfer and pressure drop, thereby enhancing the durability and efficiency of turbine blades by utilizing additive layer manufacturing and mechanical material removal processes to create complex shapes and reduce manufacturing costs.

Implementation Method 1

Fluid flowing through the linear fluid passageways of the platform is discharged from the outlet apertures

Methodology Applied
Scientific EffectFluid flow:

Implementation Method 2

Plugs are disposed in the access ducts to form a fluid tight seal

Methodology Applied
Scientific EffectFluid tight seal:

Data Source

PatentUS11225873B2Combustion turbine vane cooling system
Publication Date: 2022.01.18 ROLLS ROYCE CORP
  • US11225873B2 patent drawing
  • US11225873B2 patent drawing
  • US11225873B2 patent drawing

AI summary

A system includes an air foil positionable in a combustion flow path of a combustion turbine. A shank may be integrally formed with the air foil, and the platform may be integrally formed with the shank. The platform includes linear fluid passageways, access ducts penetrating a wedge face surface of the platform, and outlet apertures formed in a radially outward surface of the platform. The outlet apertures are in fluid communication with respective linear fluid passageways such that fluid flowing through the respective linear fluid passageways is discharged from the outlet apertures into the combustion flow path. The platform also includes plugs is disposed in respective access ducts to form a fluid tight seal and be positioned in at least one of the respective linear fluid passageways. Fluid flowing through the respective linear fluid passageways flows away from a respective plug for discharge from a respective outlet aperture.