Gas Turbine Combustor Wall Contour for Cooling Air Optimization

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Solution Overview

Problem

Gas turbine engines face challenges in efficiently cooling the combustor section due to higher temperatures and lower emissions requirements, necessitating reduced cooling air usage while maintaining effectiveness.

Innovation Solution

A wall assembly within the gas turbine engine featuring a support shell with a contoured region defining convergent passages between the support shell and liner panels, which directs cooling air to enhance cooling efficiency without additional hardware, utilizing a hyperbolic cosine, constant curve, or straight taper profiles to optimize heat transfer and airflow.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If cooling air is increased to meet service life requirements at higher combustor temperatures, then cooling effectiveness is improved, but cooling air consumption increases

Engineering Contradiction:

Improveservice lifeVSAvoidcooling air consumption

Core Design Contradiction:

ReliabilityVSQuantity of substance

Solution Approach 1:

The support shell incorporates contoured regions with curved surfaces that redirect cooling air flow. These curved geometries create convergent passages that focus and direct cooling air more effectively toward critical heat transfer zones, improving cooling efficiency without increasing air consumption

Inventive Principle:

Principle #14Spheroidality (Curvature)

Solution Approach 2:

The invention modifies the geometric parameters of the support shell by introducing contoured regions with specific curvature profiles. These parameter changes alter the flow dynamics and heat transfer characteristics, enabling more effective cooling with reduced air requirements

Inventive Principle:

Principle #35Parameter changes

2Reliability

If contoured regions are added to the support shell to create convergent passages, then cooling effectiveness is improved, but manufacturing complexity increases

Engineering Contradiction:

Improvecooling effectivenessVSAvoidsupport shell manufacturing

Core Design Contradiction:

ReliabilityVSEase of manufacture

Solution Approach 1:

The contoured regions utilize smooth curved surfaces that can be manufactured using standard aerospace forming techniques. The curvature profiles are designed to be compatible with existing hydroforming and stamping processes, avoiding the need for complex additive manufacturing or multi-piece assemblies

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

The solution effectively reduces cooling air requirements while increasing its effectiveness, providing improved heat management and maintaining engine performance under high-temperature conditions.

Implementation Method 1

directing cooling air into at least one convergent passage between a support shell and at least one of a multiple of liner panels

Methodology Applied

Scientific EffectConvection: Convection

Implementation Method 2

enhance cooling efficiency without additional hardware, utilizing a hyperbolic cosine, constant curve, or straight taper profiles to optimize heat transfer and airflow

Methodology Applied

Scientific EffectHeat transfer: Conduction (thermal)

Data Source

PatentUS10655855B2Gas turbine engine wall assembly with support shell contour regions

Publication Date: 2020.05.19 RTX CORP

AI summary

A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A method of cooling a wall assembly for a combustor of a gas turbine engine is also provided. This method includes a step of directing cooling air into at least one convergent passage between the support shell and a multiple of liner panels.