Gas Turbine Shroud Cooling Channel Pairing

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Solution Overview

Problem

Hot gas path components in gas turbine engines, particularly stationary shrouds, face extreme mechanical and thermal stresses due to high temperatures and velocities, leading to degradation and reduced component lifespan, necessitating improved cooling strategies that enhance durability and efficiency while being cost-effective.

Innovation Solution

The implementation of a cooling configuration within the inner shroud segment of the gas turbine engine, featuring a channel pairing comprising a continuous flow channel and a non-continuous flow channel with a variable path that resides closer to the exterior surface at valleys than peaks, effectively directing coolant to regions of highest need and reducing stress on the components.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If conventional cooling strategies are used in stationary shrouds, then component durability is maintained, but coolant efficiency is insufficient and component lifespan is shortened due to extreme thermal stresses

Engineering Contradiction:

Improvecomponent durabilityVSAvoidcoolant efficiency

Core Design Contradiction:

ReliabilityVSLoss of energy

Solution Approach 1:

The cooling channels are strategically positioned closer to the target exterior surface in regions experiencing highest thermal loads and degradation. The variable path distance from the exterior surface allows optimized local cooling where most needed, rather than uniform cooling throughout the component

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The cooling channel configuration uses a variable path that dynamically adapts to thermal stress distribution, with sections closer to the exterior surface in high-stress areas and farther in lower-stress areas, optimizing coolant effectiveness throughout the component

Inventive Principle:

Principle #15Dynamics

2Productivity

If engine operating parameters (size, firing temperatures, rotational velocities) are increased to improve efficiency, then engine performance is enhanced, but mechanical and thermal stresses on hot gas path components increase

Engineering Contradiction:

Improveengine efficiencyVSAvoidmechanical and thermal stresses

Core Design Contradiction:

ProductivityVSStress or pressure

Solution Approach 1:

Cooling channels are pre-positioned and configured within the stationary shroud before operation to anticipate and counteract thermal stresses. The channels are strategically located to provide cooling in advance to areas that will experience highest thermal loads during operation

Inventive Principle:

Principle #10Preliminary action

Solution Approach 2:

The cooling configuration provides thermal cushioning to the stationary shroud, creating a protective thermal barrier before extreme stresses can cause degradation. The variable path channels ensure cooling protection is in place before thermal damage occurs

Inventive Principle:

Principle #11Beforehand cushioning (Prior cushioning)

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 configuration enhances the durability and efficiency of hot gas path components by efficiently diverting coolant to areas of degradation, slowing down the degradation process and improving engine performance with reduced coolant usage, thereby lowering costs and extending component lifespan.

Implementation Method 1

a cooling configuration that includes a channel pairing in which a first channel type is paired with a second channel type... a non-continuous flow channel that extends lengthwise between a dead-end disposed at a first end and a dead-end disposed at a second end

Methodology Applied

Scientific EffectConvection: Convection

Implementation Method 2

a target interior region defined adjacent to the target exterior surface by a predetermined distance taken normal to the target exterior surface... effectively directing coolant to regions of highest need

Methodology Applied

Scientific EffectThermal conduction: Conduction (thermal)

Data Source

PatentUS10550710B2Shroud for gas turbine engine

Publication Date: 2020.02.04 GE INFRASTRUCTURE TECH LLC

AI summary

A turbine shroud segment including: a target exterior surface and target interior region; and a cooling configuration having first and second channel types. The first channel type includes: an inlet and outlet; a target section extending through the target interior region; lateral ports spaced lengthwise between first and second ends of the target section; and a path within the target interior region offset from the target exterior surface by a minimum offset. The second channel type includes: dead-ends disposed at first and second ends; lateral ports connecting to lateral ports of the first channel type; and a path through the target interior region that is variable between valleys and peaks. The second channel type resides closer to the target exterior surface at the valleys than at the peaks. At each of the valleys, the second channel type resides within the minimum offset.