Flow Sleeve Deflectors for Gas Turbine Combustor Cooling

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Solution Overview

Problem

In gas turbine combustors, the mixing of cooling air streams near the combustion liner surface reduces the velocity of air flow perpendicular to the surface, leading to ineffective cooling and accelerated thermal degradation of the liner, necessitating improved cooling methods to enhance durability.

Innovation Solution

The implementation of flow deflectors within the gas turbine combustor's flow sleeve redirects axial air flows radially outward, preventing mixing with radial cooling flows and maintaining higher perpendicular velocity of impingement air, thereby improving heat transfer and reducing thermal degradation.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If cooling air flows are directed through cooling apertures perpendicular to the combustor liner surface, then cooling effectiveness is improved, but the mixing with axial cross flow reduces the perpendicular velocity and diminishes cooling effectiveness

Engineering Contradiction:

Improvecombustor liner cooling effectivenessVSAvoidperpendicular air flow velocity

Core Design Contradiction:

TemperatureVSSpeed

Solution Approach 1:

Flow deflectors are introduced as intermediary components within the flow annulus to mediate between the axial cross flow and the radial impingement cooling flow. These deflectors redirect the axial flow away from the liner surface before it can mix with and reduce the velocity of the cooling air emerging from the apertures, thereby preserving the perpendicular velocity component and cooling effectiveness.

Inventive Principle:

Principle #24Intermediary (Mediator)

Solution Approach 2:

The flow annulus is segmented by introducing multiple flow deflectors that divide the axial cross flow into separate paths. This segmentation prevents the bulk axial flow from directly interacting with and mixing into the radial cooling jets at the liner surface, maintaining the integrity and velocity of the impingement cooling flow.

Inventive Principle:

Principle #1Segmentation

2Device complexity

If axial cross flow is allowed to travel parallel to the combustor liner surface, then flow distribution is simplified, but thermal degradation of the liner accelerates due to reduced cooling

Engineering Contradiction:

Improveflow distribution simplicityVSAvoidcombustor liner durability

Core Design Contradiction:

Device complexityVSReliability

Solution Approach 1:

Flow deflectors serve as intermediary structures that modify the axial cross flow path without fundamentally changing the overall flow distribution architecture. The deflectors are positioned to intercept and redirect the axial flow at strategic locations, providing thermal protection to the liner while adding only moderate structural complexity.

Inventive Principle:

Principle #24Intermediary (Mediator)

Solution Approach 2:

The flow deflectors perform preliminary redirection of the axial cross flow before it reaches the regions where impingement cooling is most critical. By acting in advance, the deflectors prevent the axial flow from interfering with the cooling process, thereby protecting the liner from thermal degradation before damage can occur.

Inventive Principle:

Principle #10Preliminary action

3Temperature

If flow deflectors are added to redirect axial flow away from the liner surface, then cooling effectiveness is improved, but device complexity increases

Engineering Contradiction:

Improvecombustor liner cooling effectivenessVSAvoidflow sleeve structure complexity

Core Design Contradiction:

TemperatureVSDevice complexity

Solution Approach 1:

The flow deflectors are implemented as discrete, modular elements distributed within the flow annulus rather than as a continuous complex structure. This segmentation allows for simpler manufacturing and assembly, reducing the overall structural complexity while still achieving the flow redirection function necessary to protect the combustor liner.

Inventive Principle:

Principle #1Segmentation

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 use of flow deflectors enhances the radial velocity of cooling air, leading to increased heat transfer rates and improved durability of combustion liners by shielding impingement flows from cross flows, thus reducing thermal degradation and extending the lifespan of combustor components.

Implementation Method 1

a plurality of flow deflectors are provided which discourage the axial flow from mixing with the radial cooling flow entering through apertures in the flow sleeve by directing the axial flow in a radially outward direction

Methodology Applied

Scientific EffectFluid flow redirection:

Implementation Method 2

The air flow directed through the cooling apertures is aimed to travel radially and impinge upon the outer surface of the combustor liner

Methodology Applied

Scientific EffectImpingement cooling:

Implementation Method 3

a portion of the compressed air flow is directed through the pressurized case and towards the outer surface of the combustion liner and transition piece, in a generally perpendicular direction, in order to cool these components

Methodology Applied

Scientific EffectConvection: Convection

Data Source

PatentUS10113745B2Flow sleeve deflector for use in gas turbine combustor

Publication Date: 2018.10.30 ANSALDO ENERGIA SWITZERLAND AG

AI summary

An apparatus for providing improved cooling to a combustion liner of a gas turbine combustor is provided. A plurality of flow deflectors is secured to a flow sleeve in order to improve the flow of impingement air from a flow sleeve to the combustion liner outer surface, such that the amount of impingement air being swept away by a cross flow of cooling air is reduced.