CMC Turbine Vane Spar System for Structural Integrity

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Solution Overview

Problem

Gas turbine engine turbine vanes face challenges in withstanding high temperatures and maintaining structural integrity due to the geometry and strength requirements, particularly when using composite materials.

Innovation Solution

A turbine vane assembly comprising a ceramic matrix composite vane supported by a metallic vane support and a spar system that extends between components to transfer loads and prevent twisting, with a spar system that includes first and second spars and a spar shield to enhance structural strength and stability.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If ceramic matrix composite materials are used for turbine vanes to withstand high temperatures, then temperature resistance is improved, but structural strength and geometry stability deteriorate

Engineering Contradiction:

Improvetemperature resistanceVSAvoidstructural strength

Core Design Contradiction:

TemperatureVSStrength

Solution Approach 1:

The patent employs a hybrid composite structure combining ceramic matrix composite (CMC) vane material with metallic support spars. The CMC provides high-temperature resistance while the metallic spars contribute structural strength and rigidity, creating a composite system that leverages the advantages of both material types to resolve the contradiction between temperature resistance and structural strength.

Inventive Principle:

Principle #40Composite materials

Solution Approach 2:

The turbine vane is divided into functional segments: the CMC airfoil section for temperature resistance and the metallic support spar system for structural strength. This segmentation allows each component to be optimized for its specific function while working together as an integrated assembly.

Inventive Principle:

Principle #1Segmentation

2Stability of the object's composition

If complex support structures are added to maintain vane geometry, then structural integrity is improved, but device complexity increases

Engineering Contradiction:

Improvegeometry stabilityVSAvoidsupport structure complexity

Core Design Contradiction:

Stability of the object's compositionVSDevice complexity

Solution Approach 1:

The patent extracts the structural support function from the main vane body and places it in separate, dedicated support spars. This separation allows the vane airfoil to focus on aerodynamic and temperature resistance functions while the spars handle structural support, reducing overall system complexity despite enhanced geometry stability.

Inventive Principle:

Principle #2Taking out (Extraction)

Solution Approach 2:

The metallic support spars are strategically positioned at critical locations within the vane structure where geometric stability is most needed, rather than providing uniform support throughout. This localized approach maintains geometry stability while minimizing unnecessary structural complexity.

Inventive Principle:

Principle #3Local quality

Data Source

PatentUS11732596B2Ceramic matrix composite turbine vane assembly having minimalistic support spars

Publication Date: 2023.08.22 ROLLS ROYCE PLC

AI summary

A turbine vane assembly adapted for use in a gas turbine engine includes a plurality of turbine vanes, an outer vane support, and an inner vane support. The plurality of turbine vanes comprise ceramic matrix composite material and are adapted to interact with hot gases flowing through a gas path of the gas turbine engine during use of the turbine vane assembly. A spar system couples the inner vane support with the outer vane support.