Combustor Nozzle Impingement Panel for Cooling Air Efficiency

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Solution Overview

Problem

High combustion gas temperatures in turbomachine combustors lead to erosion, creep, and low cycle fatigue, necessitating improved cooling systems that efficiently utilize cooling medium from the compressor section, thereby enhancing the overall efficiency of the turbomachine.

Innovation Solution

The integrated combustor nozzle with impingement cooling systems that efficiently utilize compressed working fluid from the compressor section, thereby enhancing the overall efficiency of the turbomachine.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If a large portion of compressed working fluid is routed to cooling components, then cooling effectiveness is improved, but overall operating efficiency deteriorates due to decreased working fluid for turbine section

Engineering Contradiction:

Improvecombustor component temperatureVSAvoidturbine section power output

Core Design Contradiction:

TemperatureVSProductivity

Solution Approach 1:

The combustor liner is divided into multiple cooling zones with separate cooling channels, allowing different regions to be cooled independently with optimized cooling medium distribution. This segmentation enables efficient cooling of critical areas while minimizing overall cooling medium consumption.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Cooling channels are strategically positioned and sized according to local thermal conditions, with higher cooling capacity directed to regions experiencing highest temperatures and greatest thermal stress. This localized approach ensures effective cooling where needed while reducing cooling medium usage in lower-stress areas.

Inventive Principle:

Principle #3Local quality

2Power

If high combustion gas temperatures are maintained, then thermal energy transfer to turbine is enhanced, but component durability deteriorates due to erosion, creep, and fatigue

Engineering Contradiction:

Improveturbine power outputVSAvoidcombustor component durability

Core Design Contradiction:

PowerVSReliability

Solution Approach 1:

The cooling channel geometry features asymmetric cross-sectional shapes and varying wall thicknesses tailored to specific thermal and mechanical stress conditions. This asymmetric design optimizes both cooling efficiency and structural strength distribution, allowing the component to withstand high combustion temperatures while maintaining durability.

Inventive Principle:

Principle #4Asymmetry

Solution Approach 2:

Cooling channels are pre-configured within the combustor liner structure before operation, establishing protective cooling flows that prevent thermal damage before it occurs. The cooling system is designed to activate automatically upon combustion, providing immediate protection against thermal stress, creep, and fatigue.

Inventive Principle:

Principle #10Preliminary action

3Temperature

If conventional cooling systems are used, then component cooling is achieved, but compressed working fluid wastage increases

Engineering Contradiction:

Improvecombustor component temperatureVSAvoidcompressed working fluid wastage

Core Design Contradiction:

TemperatureVSLoss of energy

Solution Approach 1:

The cooling channels are designed to maintain continuous, optimized cooling flows that maximize heat removal efficiency throughout the combustor liner. This continuous cooling action ensures consistent temperature control while minimizing the total quantity of cooling medium required, reducing wastage of compressed working fluid.

Inventive Principle:

Principle #20Continuity of useful 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

The integrated combustor nozzle efficiently utilizes compressed working fluid from the compressor section for cooling, minimizing wastage and enhancing the overall efficiency of the turbomachine by effectively cooling the combustion components while maximizing the amount of working fluid available for turbine section operation.

Implementation Method 1

cool the components of the combustor, which is typically achieved by routing a cooling medium, such as the compressed working fluid from the compressor section, to various portions of the combustion liner

Methodology Applied

Scientific EffectThermal conduction: Conduction (thermal)

Implementation Method 2

High combustion gas temperatures within the turbine section generally corresponds to greater thermal and kinetic energy transfer between the combustion gases and the turbine

Methodology Applied

Scientific EffectConvection: Convection

Data Source

PatentEP4394254B1Integrated combustor nozzle with impingement panel and method of manufacture

Publication Date: 2025.12.24 GENERAL ELECTRIC TECH GMBH

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AI summary

An impingement panel (130, 134) having an impingement plate (136) disposed along an exterior surface (131, 135) of one of the inner liner segment or the outer liner segment. The impingement plate (136) defines a plurality of impingement apertures (139) that direct coolant in discrete jets towards the exterior surface (131, 135) of the inner liner segment or the outer liner segment. The impingement panel (130, 134) includes an inlet portion (140) that extends from the impingement plate (136) to a collection duct (142). The impingement panel (130, 134) further includes a plurality of supports (194) spaced apart from one another. The plurality of supports (194) extend between, and are coupled to, the inlet portion (140), the collection duct (142), and the impingement plate (136)