CMC Turbine Load-Bearing Insert for Mechanical Stress

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Solution Overview

Problem

Gas turbine engines face challenges due to the high temperatures generated by combustion products, which can degrade conventional materials, necessitating the use of ceramic matrix composites (CMCs) for turbine components, but these materials require enhancements to better withstand mechanical stresses.

Innovation Solution

Incorporating a load-bearing feature with a thickened portion and an insert formed of ceramic matrix composite layers, such as a 3D woven structure, to enhance the mechanical strength and durability of CMC components, particularly in areas subject to significant mechanical forces.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If ceramic matrix composite layers are used to form turbine components, then resistance to high temperatures is improved, but mechanical strength and durability deteriorate

Engineering Contradiction:

Improveresistance to high temperaturesVSAvoidmechanical strength

Core Design Contradiction:

TemperatureVSStrength

Solution Approach 1:

The patent applies composite materials by combining ceramic matrix composite layers with a load-bearing feature made of different materials (such as metal or ceramic insert). This creates a hybrid structure where the CMC layers provide thermal resistance while the insert provides mechanical strength, resolving the contradiction between temperature resistance and mechanical strength.

Inventive Principle:

Principle #40Composite materials

Solution Approach 2:

The load-bearing feature is strategically placed at specific locations where mechanical stresses are highest (such as mounting surfaces or load-bearing platforms). This local reinforcement approach maintains the overall CMC structure's thermal resistance while providing targeted mechanical strength enhancement where needed most.

Inventive Principle:

Principle #3Local quality

2Temperature

If ceramic matrix composite layers are used to form turbine components, then resistance to high temperatures is improved, but durability under mechanical stress deteriorates

Engineering Contradiction:

Improveresistance to high temperaturesVSAvoiddurability under mechanical stress

Core Design Contradiction:

TemperatureVSReliability

Solution Approach 1:

The hybrid composite structure combines CMC layers with a load-bearing insert to create a component that maintains thermal resistance while significantly improving durability under mechanical stress. The insert acts as a reinforcement that prevents cracking and degradation under repeated loading cycles.

Inventive Principle:

Principle #40Composite materials

Solution Approach 2:

The load-bearing feature is pre-installed within the CMC structure to provide beforehand cushioning against mechanical stresses. This preventive reinforcement protects the CMC material from stress concentrations that would otherwise lead to premature failure, thereby improving reliability before damage occurs.

Inventive Principle:

Principle #11Beforehand cushioning (Prior cushioning)

Data Source

PatentUS12428965B2Load bearing feature for ceramic matrix composite turbine components

Publication Date: 2025.09.30 RTX CORP

AI summary

A gas turbine engine component includes an inner surface and an outer surface. The outer surface and the inner surface are formed of ceramic matrix composite layers, and mount member. The mount member is in contact with an insert that is inserted within outer layers of the outer platform to form a thickened portion having an end surface that will react against forces from the mount member. A gas turbine engine and a method are also disclosed.