CMC Stator Vane Flange Layout to Cut Flow Obstruction

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Solution Overview

Problem

Existing stator vanes in gas turbine engines face challenges in withstanding very high temperatures due to their exposure to combustion products, and existing mounting methods can cause flow obstruction and delamination.

Innovation Solution

The stator vanes are formed of ceramic matrix composites (CMC) with attachment flanges extending axially and secured using CMC or metal c-clips, which provide additional strength and sealing without obstructing the flow path, and the ply layup design enhances structural integrity.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If traditional mounting flanges are used on stator vanes, then the stator vanes can be mounted in the housing, but the flanges extend in the circumferential direction and obstruct the flow path

Engineering Contradiction:
Improvemounting reliabilityVSAvoidflow obstruction
Core Design Contradiction:
ReliabilityVSObject-generated harmful factors

Solution Approach 1:

The mounting flanges are reoriented from extending in the circumferential direction to extending in the axial direction, changing the spatial dimension of the flange extension. This dimensional change allows the flanges to be positioned without obstructing the circumferential flow path while maintaining mounting functionality.

Inventive Principle:
Principle #17Another dimension (Dimensionality change)

2Ease of manufacture

If CMC components are formed using traditional ply layup methods, then the components can be manufactured, but the ply structure is vulnerable to delamination under high temperature and stress

Engineering Contradiction:
Improvemanufacturing feasibilityVSAvoidply structure stability
Core Design Contradiction:
Ease of manufactureVSStability of the object's composition

Solution Approach 1:

The ply layup structure is optimized with specific fiber orientations (0°, 90°, ±45° layers) at different locations within the CMC component. This local quality variation enhances the ply structure's resistance to delamination in high temperature and stress environments while maintaining manufacturability through controlled fiber placement.

Inventive Principle:
Principle #3Local quality

Solution Approach 2:

The stator vane is constructed as a CMC composite material structure with multiple plies of ceramic fibers embedded in a matrix material. This composite structure provides both manufacturability through layer-by-layer fabrication and enhanced stability against delamination through the interlaminar bonding and fiber reinforcement.

Inventive Principle:
Principle #40Composite materials

3Reliability

If mounting flanges are used to secure stator vanes, then the vanes can be firmly mounted, but the flanges and mounting hardware create leakage paths

Engineering Contradiction:
Improvemounting firmnessVSAvoidleakage
Core Design Contradiction:
ReliabilityVSObject-generated harmful factors

Solution Approach 1:

The harmful leakage paths created by traditional mounting flanges and hardware are eliminated by extracting the mounting function from the flow path area. The axial flanges are positioned to secure the vane firmly while being clear of the circumferential flow, separating the mounting function from the flow guidance function to prevent leakage.

Inventive Principle:
Principle #2Taking out (Extraction)

Data Source

PatentEP4325029B1Gas turbine engine stator vanes formed of ceramic matrix composites and having attachment flanges
Publication Date: 2026.02.18 RTX CORP
  • EP4325029B1 patent drawingFigure 1
  • EP4325029B1 patent drawingFigure 2A~5
  • EP4325029B1 patent drawingFigure 3

AI summary

A stator vane (100) formed of CMC has a radially outer platform (104) and a radially inner platform (106) attached to an airfoil (102). There are a pair of flanges (108, 110; 109, 112) on a side of each of the radially inner platform (106) and radially outer platform (104) which is remote from the airfoil (102). A first of the pair of flanges (108, 110; 109, 112) is associated with the suction side of the airfoil (102) and a second of the pair of flanges (108, 110; 109, 112) is associated with the pressure side of the airfoil (102). The flanges (108, 110; 109, 112) extend in a generally axial direction. The first of the pair of flanges (108, 110; 109, 112) extend over at least a majority of the suction side measured between the leading and trailing edge of the airfoil (102) and the second of the pair of flanges (108, 110; 109, 112) extend over at least a majority of the pressure side measured between the leading and trailing edges of the airfoil (102).