Inter-Compressor Frame Drag Links for Shorter Thrust Reversers
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Solution Overview
Problem
Existing thrust reverser systems in gas turbine engines face challenges in efficiently redirecting airflow for reverse thrust while maintaining structural integrity and reducing nacelle length and weight.
Innovation Solution
Incorporating an inter-compressor frame structure that supports the turbo-engine cowl and includes drag link connectors and bleed air vents, along with a cold stream cascade thrust reverser system, to redirect airflow and provide structural support, while allowing for a shorter nacelle design.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If a traditional thrust reverser system is used with separate structural support, then structural integrity is maintained, but nacelle length and weight increase
Solution Approach 1:
The inter-compressor frame structure is integrated to perform dual functions: supporting the turbo-engine cowl structure and serving as the mounting point for drag link connectors. This merging of structural support and thrust reverser attachment functions eliminates redundant structures, reducing nacelle weight while maintaining both structural integrity and thrust reverser functionality.
2Length of moving object
If a longer nacelle is used to accommodate thrust reverser components, then structural support is adequate, but nacelle length increases
Solution Approach 1:
The inter-compressor frame structure is designed as a multi-functional component that simultaneously provides structural support for the turbo-engine cowl and serves as the attachment structure for thrust reverser drag links. This universal structure eliminates the need for separate structural support elements, allowing for a shorter nacelle design while maintaining adequate structural support capability.
3Weight of moving object
If drag link connectors are positioned at the inter-compressor frame structure, then nacelle weight is reduced, but manufacturing complexity increases
Solution Approach 1:
The inter-compressor frame structure is segmented to include integrated drag link connector mounting points, allowing the structure to be manufactured as a unified component with built-in attachment features. This segmentation approach enables the complex multi-functional structure to be broken down into manufacturable sections that can be assembled, reducing overall manufacturing complexity despite the integrated design.
Data Source
AI summary
A gas turbine engine includes a fan assembly, a turbo-engine encased within a turbo-engine cowl structure, a nacelle, and a thrust reverser system arranged, at least in part, in the nacelle. The turbo-engine includes a low-pressure compressor, a high-pressure compressor, an inter-compressor frame structure between the low-pressure compressor and the high-pressure compressor and including an outer frame portion having a cowl door engagement member on an upstream side of the outer frame portion, and a plurality of cowl doors defining the turbo-engine cowl structure. Each cowl door includes an inter-compressor frame engagement portion that engages with the cowl door engagement member of the inter-compressor frame structure, and a plurality of thrust reverser drag link connectors arranged on an outer side of the cowl door and arranged between the upstream side of the inter-compressor frame structure and a downstream side of the inter-compressor frame structure.