Turbine Cavity Cooling via Flanges and Flow Guides

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Solution Overview

Problem

Gas turbine systems face challenges in optimizing heat transfer and cooling within turbine sections without the use of impingement plates and flow sleeves, which adds complexity and cost, while also risking component damage and clearance issues due to thermal expansion.

Innovation Solution

A system and method that utilize a cavity between inner and outer casings with structural features like flanges, false flanges, protrusions, and perforated plates to facilitate air flow and optimize heat transfer, controlling radial and axial clearances without the need for impingement plates or flow sleeves.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If impingement plates and flow sleeves are used to cool turbine sections, then heat transfer efficiency is improved, but device complexity and manufacturing cost increase

Engineering Contradiction:

Improveturbine section cooling efficiencyVSAvoidcomplexity of cooling system

Core Design Contradiction:

TemperatureVSDevice complexity

Solution Approach 1:

The patent removes impingement plates and flow sleeves from the cooling system, extracting the problematic components that caused complexity and cost issues while maintaining cooling functionality through alternative means

Inventive Principle:

Principle #2Taking out (Extraction)

Solution Approach 2:

The cavity structure itself serves the cooling function through its geometry and natural air flow patterns, eliminating the need for additional active cooling components like impingement plates and flow sleeves

Inventive Principle:

Principle #25Self-service

2Temperature

If impingement plates and flow sleeves are used to enhance cooling, then heat transfer is improved, but manufacturing and repair costs increase

Engineering Contradiction:

Improveheat transfer efficiencyVSAvoidmanufacturing cost

Core Design Contradiction:

TemperatureVSEase of manufacture

Solution Approach 1:

The patent eliminates impingement plates and flow sleeves from the design, removing components that require complex manufacturing processes and expensive maintenance, thereby reducing overall manufacturing and repair costs

Inventive Principle:

Principle #2Taking out (Extraction)

Solution Approach 2:

The design uses simpler, more cost-effective cavity structures that can be manufactured at lower cost compared to complex impingement plate assemblies, accepting that the simpler structure may require more frequent maintenance but at lower overall cost

Inventive Principle:

Principle #27Cheap short-living objects (Disposable)

3Strength

If thermal expansion is allowed to occur naturally, then component stress is reduced, but clearance between turbine blades and casing deteriorates

Engineering Contradiction:

Improvecomponent stress levelVSAvoidclearance between turbine blades and casing

Core Design Contradiction:

StrengthVSLength of stationary object

Solution Approach 1:

The patent modifies the thermal parameters of the casing through the cavity structure, changing the temperature distribution and thermal expansion characteristics to maintain clearances while accommodating stress requirements

Inventive Principle:

Principle #35Parameter changes

Solution Approach 2:

The cavity acts as an intermediary thermal management system between the hot turbine section and the external environment, controlling heat transfer rates to manage thermal expansion and maintain proper clearances

Inventive Principle:

Principle #24Intermediary (Mediator)

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 approach reduces manufacturing and repair costs, maintains component clearances, and enhances engine performance by effectively cooling turbine sections and managing thermal expansion, thereby improving heat transfer efficiency and reducing the risk of component damage.

Implementation Method 1

The cavity is configured to facilitate an air flow within the cavity to cool the outer surface of the inner casing and the inner surface of the outer casing

Methodology Applied

Scientific EffectConvection: Convection

Implementation Method 2

The at least one flow guide is configured to change a velocity or a direction of an air flow within the cavity to facilitate cooling

Methodology Applied

Scientific EffectFluid flow:

Implementation Method 3

the combustion generates a significant amount of heat. This heat can cause thermal expansion, as well as potential stress or wear to various components within the gas turbine engine

Methodology Applied

Scientific EffectThermal expansion: Thermal Expansion

Data Source

PatentUS9828880B2Method and apparatus to improve heat transfer in turbine sections of gas turbines

Publication Date: 2017.11.28 GE INFRASTRUCTURE TECH LLC

AI summary

A gas turbine engine system having a combustion section and a turbine section is provided. The turbine section includes at least one turbine stage having a plurality of turbine blades coupled to a rotor and an inner casing circumferentially disposed about the plurality of turbine blades. The turbine section includes an outer casing circumferentially disposed about at least a portion of the inner casing. The inner casing and the outer casing define a cavity comprising a volume configured to facilitate the distribution of air within the cavity to cool an outer surface of the inner casing and an inner surface of the outer casing. The outer casing comprises at least one air inlet and the inner casing comprises at least one air outlet. At least one flange is provided within the cavity, and the at least one flange flanks the air inlet and at least one flow guide.