Single Yoke Cowl Flange for Gas Turbine Combustor

Solution Overview

Problem

The double yoke (clevis-type) connection in gas turbine engine combustors increases the radial profile and weight of the cowl structure due to its metallic nature, which is inefficient and cumbersome.

Innovation Solution

A single yoke or single connecting flange is used for connecting CMC outer and inner liners and a CMC dome to a metallic cowl structure, reducing the overall radial height and weight of the cowl structure.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If a double yoke (clevis-type) connection is used to connect CMC liners and dome to the metallic cowl structure, then the connection strength and reliability are improved, but the radial profile height and weight of the cowl structure increase

Engineering Contradiction:

Improveconnection strengthVSAvoidradial profile height

Core Design Contradiction:

ReliabilityVSLength of stationary object

Solution Approach 1:

The patent merges the outer yoke and inner yoke into a single integrated connecting flange structure. This single flange performs the function of both yokes by providing attachment points for both the outer liner and inner liner to the cowl structure, eliminating the need for separate yoke components and reducing radial profile height while maintaining connection reliability

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The connecting flange is segmented into multiple functional zones: an outer region for attaching the outer liner, an inner region for attaching the inner liner, and a central region for bolting to the cowl structure. This segmentation allows a single component to fulfill multiple connection functions that previously required separate yoke components

Inventive Principle:

Principle #1Segmentation

2Reliability

If a double yoke (clevis-type) connection is used to connect CMC liners and dome to the metallic cowl structure, then the connection strength and reliability are improved, but the weight of the cowl structure increases

Engineering Contradiction:

Improveconnection strengthVSAvoidcowl structure weight

Core Design Contradiction:

ReliabilityVSWeight of stationary object

Solution Approach 1:

The patent merges the outer yoke and inner yoke into a single integrated connecting flange structure. This single flange performs the function of both yokes by providing attachment points for both the outer liner and inner liner to the cowl structure, eliminating the need for separate yoke components and reducing radial profile height while maintaining connection reliability

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The patent employs CMC (ceramic matrix composite) materials for the liners and dome structure, which have high strength-to-weight ratios. This allows for lighter overall structure while maintaining connection strength, complementing the single flange design to reduce total cowl structure weight

Inventive Principle:

Principle #40Composite materials

3Length of stationary object

If a single yoke connecting flange is used to connect CMC liners and dome to the metallic cowl structure, then the radial profile height and weight are reduced, but the structural complexity of the connection increases

Engineering Contradiction:

Improveradial profile heightVSAvoidconnection structure complexity

Core Design Contradiction:

Length of stationary objectVSDevice complexity

Solution Approach 1:

The connecting flange is designed as a universal component that performs multiple functions: it serves as the attachment point for the outer liner, the inner liner, and the cowl structure simultaneously. This multi-functionality consolidates what would otherwise require multiple separate components, reducing radial profile height while the modular design keeps manufacturing complexity manageable

Inventive Principle:

Principle #6Universality (Multi-functionality)

Data Source

PatentUS20250290636A1Gas turbine engine combustor having ceramic matrix composite (CMC) liners and CMC dome

Publication Date: 2025.09.18 GENERAL ELECTRIC CO

AI summary

A combustor for a gas turbine engine includes a ceramic matrix composite (CMC) dome structure, a metallic cowl structure including a single yoke outer cowl connecting flange and a single yoke inner cowl connecting flange, a CMC outer liner, and a CMC inner liner. An outer connection connects the outer cowl connecting flange, the CMC dome structure, and the CMC outer liner in an outer stacked arrangement, and an inner connection connects the inner cowl connecting flange, the CMC dome structure, and the CMC inner liner in an inner stacked arrangement.