Turbine Combustor Wall Cooling via Effusion Apertures

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Solution Overview

Problem

Turbine engine combustors face challenges with high thermal stresses in igniter aperture grommets and heat shields due to high temperatures, leading to potential structural issues and reduced efficiency.

Innovation Solution

The design incorporates a combustor wall with a shell, heat shield, and an annular body that includes a funnel-shaped portion to direct cooling air into a cooling cavity, reducing thermal stresses by impingement cooling and film cooling the igniter aperture bodies and heat shield.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Strength

If cooling apertures are added to cool the igniter aperture body, then thermal stress is reduced, but device complexity increases

Engineering Contradiction:

Improvethermal stress resistanceVSAvoidcombustor wall structure

Core Design Contradiction:

StrengthVSDevice complexity

Solution Approach 1:

The shell incorporates effusion apertures distributed across its surface, creating a porous-like structure that allows cooling air to pass through and contact the igniter aperture body. This distributed aperture approach effectively reduces thermal stress while maintaining structural integrity, resolving the contradiction between cooling effectiveness and structural complexity.

Inventive Principle:

Principle #31Porous materials

Solution Approach 2:

The shell serves multiple functions: it provides structural support, defines the combustion chamber volume, and acts as a cooling air distribution system through its effusion apertures. By integrating the cooling function into the existing shell structure rather than adding separate cooling components, the design reduces thermal stress without proportionally increasing device complexity.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Strength

If impingement cooling is applied to the igniter aperture body, then thermal stress is reduced, but manufacturing complexity increases

Engineering Contradiction:

Improvethermal stress resistanceVSAvoidcombustor wall assembly

Core Design Contradiction:

StrengthVSEase of manufacture

Solution Approach 1:

The cooling cavity is integrated directly into the shell structure, merging the cooling function with the existing combustor wall assembly. The effusion apertures are formed as part of the shell manufacturing process, and the igniter aperture body is positioned within the existing combustion chamber geometry. This integration approach enables impingement cooling while minimizing additional manufacturing steps and assembly complexity.

Inventive Principle:

Principle #5Merging (Combining)

3Temperature

If cooling air flow is increased to reduce thermal stress, then heat management improves, but energy loss increases

Engineering Contradiction:

Improveigniter aperture body temperatureVSAvoidcooling air energy

Core Design Contradiction:

TemperatureVSLoss of energy

Solution Approach 1:

Cooling air is directed specifically to the igniter aperture body through effusion apertures positioned in the shell, providing localized cooling only where thermal stress is most critical. This targeted approach reduces the temperature of the igniter aperture body effectively while minimizing the total volume of cooling air required, thereby reducing energy loss compared to blanket cooling of the entire combustor structure.

Inventive Principle:

Principle #3Local quality

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 configuration effectively reduces thermal stresses and improves the structural integrity and efficiency of the turbine engine combustor by efficiently managing heat through impingement and film cooling, enhancing the durability and performance of the igniter aperture grommets and heat shield.

Implementation Method 1

The shell defines a first cooling aperture through which air is directed to impinge against the outer surface

Methodology Applied

Scientific EffectImpingement cooling: Convection

Implementation Method 2

cooling air into a cooling cavity, reducing thermal stresses by impingement cooling and film cooling the igniter aperture bodies and heat shield

Methodology Applied

Scientific EffectFilm cooling: Convection

Data Source

PatentUS10968829B2Cooling an igniter body of a combustor wall

Publication Date: 2021.04.06 RTX CORP

AI summary

An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The body extends laterally between an inner surface and an outer surface. The inner surface defines an igniter aperture in the combustor wall. The outer surface is vertically between the heat shield and the shell. The shell defines a first cooling aperture through which air is directed to impinge against the outer surface.