CMC Combustor Panel Curvature for Lower Thermal Stress

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Solution Overview

Problem

The ceramic matrix composite (CMC) panels in gas turbine combustors experience thermal stress due to the thermal gradient from the combustion chamber, which affects their structural integrity.

Innovation Solution

The CMC panels are designed with a neutral plane that has a planar or curved shape with a smaller curvature than the inner peripheral surface, reducing thermal stress by minimizing shape restrictions and maintaining a simple, flat plate-like configuration.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If the CMC panel is positioned facing the combustion chamber to utilize high heatproof temperature, then the heatproof temperature capability is improved, but thermal stress increases due to thermal gradient from the combustion chamber

Engineering Contradiction:

Improveheatproof temperatureVSAvoidthermal stress

Core Design Contradiction:

TemperatureVSStress or pressure

Solution Approach 1:

The patent applies curvature to the neutral plane of the CMC panel, designing it with a curved surface shape that has a smaller curvature radius than the inner peripheral surface of the shell. This curvature design allows the panel to better accommodate thermal expansion and reduce thermal stress concentration while maintaining high heatproof temperature capability.

Inventive Principle:

Principle #14Spheroidality (Curvature)

2Use of energy by moving object

If the panel is made of CMC to reduce cooling air requirements, then fuel efficiency is improved, but thermal stress management becomes more critical

Engineering Contradiction:

Improvefuel efficiencyVSAvoidthermal stress

Core Design Contradiction:

Use of energy by moving objectVSStress or pressure

Solution Approach 1:

The curved neutral plane design is specifically applied to CMC panels to manage thermal stress that arises when using these high-heatproof materials. The curvature allows the rigid CMC material to better handle thermal gradients, enabling fuel efficiency improvements without compromising structural integrity.

Inventive Principle:

Principle #14Spheroidality (Curvature)

3Stress or pressure

If the neutral plane has a curved surface shape with smaller curvature, then thermal stress is reduced, but manufacturing complexity may increase

Engineering Contradiction:

Improvethermal stressVSAvoidpanel manufacturing

Core Design Contradiction:

Stress or pressureVSEase of manufacture

Solution Approach 1:

The patent applies the curved surface shape specifically to the neutral plane of the panel, while other portions of the panel can maintain simpler geometries. This localized application of curvature targets the specific region where thermal stress occurs, reducing overall manufacturing complexity while still achieving stress reduction benefits.

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 design effectively reduces thermal stress in the CMC panels, enhancing their structural integrity and improving the efficiency and productivity of gas turbine operations.

Implementation Method 1

a thermal gradient from the inner peripheral surface toward an outer peripheral surface is generated

Methodology Applied

Scientific EffectThermal gradient: Temperature Gradient

Implementation Method 2

thermal stress is generated by the heat of the combustion chamber

Methodology Applied

Scientific EffectThermal stress: Thermal Expansion

Data Source

PatentUS12571537B2Combustor panel and gas turbine combustor including same

Publication Date: 2026.03.10 KAWASAKI JUKOGYO KK

AI summary

A panel of a combustor includes: an outer surface that is opposed to an inner peripheral surface of a shell so as to be spaced apart from the inner peripheral surface; and an inner surface that defines a combustion chamber extending in a flow direction from an upstream side of the combustor to a downstream side of the combustor. At least part of a neutral plane between the outer surface and the inner surface has a planar shape or a curved surface shape which extends in a circumferential direction and whose curvature is smaller than a curvature of a virtual circular arc that is concentric with the inner peripheral surface of the shell.