Turbomachine Cooling Circuit Bypass Conduit

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Solution Overview

Problem

Conventional turbomachine rotor blade cooling circuits experience flow dead zones due to sharp turns, leading to decreased efficiency and inadequate cooling of the trailing edge root, which results in unwanted hot spots and thermal stresses.

Innovation Solution

A cooling circuit design featuring a plurality of exit channels along the trailing edge of the airfoil and at least one bypass conduit extending from an inlet in the cooling circuit to an outlet on the pressure side slash face, positioned radially inward of the exit channels, to reduce flow dead zones and enhance cooling efficiency.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Volume of moving object

If sharp turns are used in the cooling circuit, then the circuit can be compact and follow the airfoil contour, but flow dead zones are created that decrease cooling efficiency

Engineering Contradiction:

Improvecooling circuit compactnessVSAvoidcooling efficiency

Core Design Contradiction:

Volume of moving objectVSLoss of energy

Solution Approach 1:

The cooling circuit is divided into multiple segments including straight sections and bypass conduits. The bypass conduit segments the flow path to eliminate sharp turns, allowing the circuit to maintain compactness while improving flow characteristics and reducing dead zones.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The bypass conduit uses curved transitions instead of sharp angles to connect different sections of the cooling circuit. This curvature eliminates flow separation and dead zones while maintaining the compact layout required to follow the airfoil contour.

Inventive Principle:

Principle #14Spheroidality (Curvature)

2Device complexity

If conventional cooling circuits are used, then the structure is simple, but the trailing edge root experiences inadequate cooling and thermal stresses

Engineering Contradiction:

Improvecooling circuit structureVSAvoidtrailing edge root temperature

Core Design Contradiction:

Device complexityVSTemperature

Solution Approach 1:

The bypass conduit is specifically positioned to deliver cooling flow to the trailing edge root region, which experiences the highest thermal stresses. This localized cooling approach addresses the specific thermal problem at the trailing edge root without requiring complete redesign of the entire cooling circuit.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The bypass conduit acts as an intermediary flow path that redirects cooling air from the main cooling circuit to the trailing edge root region. This intermediary channel ensures adequate cooling to the problematic area while maintaining the simplicity of the overall circuit structure.

Inventive Principle:

Principle #24Intermediary (Mediator)

3Temperature

If cooling flow is directed to the trailing edge, then cooling efficiency at the trailing edge improves, but flow dead zones are created that cause hot spots

Engineering Contradiction:

Improvetrailing edge coolingVSAvoidhot spots and thermal stresses

Core Design Contradiction:

TemperatureVSObject-affected harmful factors

Solution Approach 1:

Instead of directing flow directly into sharp turns at the trailing edge, the bypass conduit inverts the approach by providing a separate, optimized flow path that delivers cooling air to the trailing edge root region without creating dead zones. This inverted flow path eliminates the harmful effect of flow stagnation while maintaining effective cooling.

Inventive Principle:

Principle #13The other way round (Inversion)

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 design minimizes flow dead zones and provides effective cooling to the trailing edge root, improving turbomachine performance by ensuring uniform coolant distribution and reducing thermal stresses.

Implementation Method 1

A cooling circuit is circumscribed in the rotor blade to provide a path for cooling air from the compressor section to flow through and cool the various portions of the airfoil that are exposed to the high temperatures of the hot gas flow

Methodology Applied

Scientific EffectConvection: Convection

Implementation Method 2

The pin bank functions to increase the amount of convective cooling within the rotor blade by increasing the overall surface area exposed to the compressor air

Methodology Applied

Scientific EffectConvection: Convection

Data Source

PatentUS12123319B2Cooling circuit having a bypass conduit for a turbomachine component

Publication Date: 2024.10.22 GE INFRASTRUCTURE TECH LLC

AI summary

A turbomachine component includes a platform, a shank, and an airfoil. The platform includes a pressure side slash face and a suction side slash face. The shank extends radially inward from the platform. The airfoil extends radially outward from the platform. The airfoil includes a leading edge and a trailing edge. A cooling circuit is defined within the shank and the airfoil. The cooling circuit further includes a plurality of exit channels disposed along the trailing edge of the airfoil. The cooling circuit further includes at least one bypass conduit that extends from an inlet disposed in the cooling circuit to an outlet positioned on the pressure side slash face. The at least one bypass conduit being positioned radially inward of the plurality of exit channels.