Gas Turbine Combustor Liner Panel Discontinuous Rail Cooling

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Solution Overview

Problem

The combustor section of gas turbine engines faces challenges with thermal durability and cooling efficiency due to the segmented liner panels and adverse aerodynamics at transition regions, leading to potential durability issues and cooling inefficiencies.

Innovation Solution

The implementation of a liner panel assembly with a discontinuous rail end surface that allows for enhanced cooling airflow and improved heat transfer, featuring a design where the forward circumferential rail interfaces with the support shell at a discontinuous rail end surface, enabling impingement and slot film cooling, thereby improving durability and cooling efficiency.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of manufacture

If liner panels are segmented to accommodate growth and accommodate combustion chamber geometry transitions, then manufacturing and assembly ease is improved, but cooling efficiency deteriorates due to steps and dead regions at panel interfaces

Engineering Contradiction:

Improveease of manufactureVSAvoidcooling efficiency

Core Design Contradiction:

Ease of manufactureVSLoss of energy

Solution Approach 1:

The combustor liner is divided into multiple segmented panels that can be manufactured and installed separately, accommodating growth and geometric transitions. Each panel is a discrete component that can be independently manufactured and assembled, providing manufacturing flexibility while maintaining the ability to cover complex geometries.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The discontinuous rail end surface design converts the potentially harmful step at the panel interface into a beneficial feature by creating a recessed area that directs cooling airflow. The step that would normally create a dead region is redesigned to actively guide cooling air along the panel surface, transforming a cooling inefficiency into an improvement.

Inventive Principle:

Principle #22Blessing in disguise (Convert harm into benefit)

2Strength

If full perimeter rails are used to contact the inner surface of liner shells, then structural support and panel positioning are improved, but cooling airflow is blocked creating dead regions

Engineering Contradiction:

Improvestructural supportVSAvoidcooling airflow

Core Design Contradiction:

StrengthVSLoss of energy

Solution Approach 1:

The continuous perimeter rail is segmented into discrete sections with gaps, particularly at the distal ends where the rails interface with support shells. This segmentation allows cooling airflow to pass through the gaps while the rail segments maintain structural support and positioning functions at critical locations.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The rail structure has varying properties along its length - continuous sections provide structural support where needed, while discontinuous sections with gaps allow cooling airflow. The discontinuous rail end surface creates localized recesses that guide airflow, providing different functional characteristics at different locations along the same rail structure.

Inventive Principle:

Principle #3Local quality

3Ease of manufacture

If panels are designed with straight edges and linear profiles, then manufacturing simplicity is improved, but aerodynamic performance deteriorates at transition regions

Engineering Contradiction:

Improvemanufacturing simplicityVSAvoidaerodynamic performance

Core Design Contradiction:

Ease of manufactureVSObject-affected harmful factors

Solution Approach 1:

The panel edges, particularly the distal ends, are designed with curved or rounded profiles instead of sharp straight edges. This curvature eliminates abrupt geometric discontinuities that would create adverse aerodynamic effects, while the overall panel structure maintains manufacturing simplicity through standardized forming processes.

Inventive Principle:

Principle #14Spheroidality (Curvature)

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 design enhances combustor durability and operational lifespan by improving cooling efficiency and reducing thermal stress on the liner panels, leading to better aerodynamic performance and extended service life.

Implementation Method 1

enabling impingement and slot film cooling

Methodology Applied

Scientific EffectImpingement cooling: Convection

Implementation Method 2

enabling impingement and slot film cooling

Methodology Applied

Scientific EffectSlot film cooling: Convection

Implementation Method 3

cooling airflow is provided to meet desired service life requirements

Methodology Applied

Scientific EffectConvection cooling: Convection

Data Source

PatentEP3366995B1Combustor liner panel assembly and method for cooling the same

Publication Date: 2023.12.27 RTX CORP

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AI summary

A combustor for a gas turbine engine includes a support shell (68, 70), a first liner panel (72A, 72B) mounted to the support shell (68, 70) via a multiple of studs, the first liner panel (72A, 72B) including a first rail (124a) that extends from a cold side of the first liner panel (72A, 72B), and a second liner panel (74A, 74B) mounted to the support shell (68, 70) via a multiple of studs, the second liner panel (74A, 74B) including a second rail (122b) that extends from a cold side of the second liner panel (74A, 74B) adjacent to said first rail (124a), the second rail (122b) includes a discontinuous rail end surface (150).