Integrated Thrust Reverser Pylon Assembly Weight Reduction
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Solution Overview
Problem
Existing thrust reverser assemblies for bypass engines are heavy due to complex designs incorporating drag links, latches, hinges, and supporting structures, which reduce engine efficiency during ground deceleration.
Innovation Solution
An integrated thrust reverser/pylon assembly with a translatable cowl and cascade structure, utilizing a v-blade/v-groove arrangement and laminate composite materials, minimizes parts and weight by redirecting fan air for deceleration while allowing access to engine components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If complex thrust reverser assemblies with drag links, latches, hinges, and supporting structures are used, then the thrust reverser can effectively block bypass air flow, but the weight of the engine increases
Solution Approach 1:
The patent integrates the thrust reverser system directly into the pylon structure, merging previously separate components (thrust reverser mechanism, pylon, and supporting structures) into a unified assembly. This integration eliminates redundant supporting structures and reduces the overall number of parts while maintaining the ability to effectively block bypass air flow for thrust reversal.
2Reliability
If complex thrust reverser assemblies with multiple components are used, then the thrust reverser can effectively block bypass air flow, but the device complexity increases
Solution Approach 1:
The patent combines multiple previously separate systems into a single integrated pylon assembly, reducing device complexity by eliminating the need for separate supporting structures, drag links, and latches that were required in conventional designs.
Solution Approach 2:
The integrated pylon structure serves multiple functions simultaneously: it provides structural support for the engine, houses the thrust reverser mechanism, and enables thrust reversal functionality. This multi-functionality reduces the number of separate components needed while maintaining effective bypass air flow blocking capability.
Data Source
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AI summary
Assembly for supporting a gas turbine engine comprises a support member (14) including mounting sites for attachment to an associated aircraft. The support member includes integral slider tracks (78) disposed on opposed sidewalls for selective engagement with a translatable cowl. The translatable cowl (22) is translatable along the slider tracks to selectively cover and expose a cascade thrust- reversing structure (24). The cascade structure includes arcuate segments (24a) mounted in hinged relationship to the support member. Rearward translation of the translatable cowl (22) to a service position permits the cascade structure (24) to be opened for access to the core engine.