Thrust Reverser Cascade Segment Axial Translation
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Solution Overview
Problem
Conventional thrust reverser systems for gas turbine engines either require blocker doors that interfere with airflow or drag links that extend into the bypass passage, leading to inefficiencies and increased nacelle assembly size when stowed.
Innovation Solution
A thrust reverser system with a frame member, a forward ring movable along the axial centerline, and a cascade segment that is slidably and rotatably attached, allowing the cascade segment to be positioned outside or within the bypass passage depending on the forward ring's position, eliminating the need for blocker doors and drag links.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If blocker doors are used to block airflow through the bypass passage, then reverse thrust is generated, but the blocker doors interfere with airflow when stowed and increase nacelle assembly size
Solution Approach 1:
The patent removes the blocker doors from the system entirely, extracting the harmful element that caused airflow interference. Instead of using blocker doors to redirect airflow, the invention uses only cascades that are translated into the bypass passage to achieve reverse thrust without any components extending into or through the bypass passage when stowed.
Solution Approach 2:
The cascade is divided into multiple cascade segments that can be independently translated into the bypass passage. Each segment is movable between a stowed position outside the bypass passage and a deployed position within the bypass passage, allowing selective deployment to generate reverse thrust while maintaining clean airflow when not in use.
2Force
If drag links are used to translate cascades into the bypass passage, then reverse thrust is generated, but the drag links extend through the bypass passage even when stowed
Solution Approach 1:
The patent eliminates drag links and any other deployment mechanisms that extend into or through the bypass passage. The cascade segments are translated using mechanisms contained entirely within the nacelle assembly, removing the harmful extension into the bypass passage while maintaining the ability to generate reverse thrust.
3Object-affected harmful factors
If blocker doors are enclosed within the nacelle assembly when stowed, then airflow through the bypass passage is not interfered with, but the nacelle assembly becomes larger than desired
Solution Approach 1:
The patent removes blocker doors from the system entirely, eliminating the need to accommodate them within the nacelle assembly. This extraction of the harmful component allows the nacelle assembly to maintain a compact size while still achieving the function of generating reverse thrust through cascade segments alone.
Data Source
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AI summary
A thrust reverser system (100) for incorporation into a nacelle assembly (50) of a gas turbine engine includes a frame member (110) and a forward ring (108) movable along an axial centerline (12) relative to the frame member (110). The forward ring (108) is movable between a first position and the second position. The thrust reverser system (100) additionally includes a cascade segment (116) slidably attached to the frame member (110) and rotatably attached to the forward ring (108). When the forward ring (108) is in the first position the cascade segment (116) is in a radially outer position outside the bypass passage, and when the forward ring (108) is in the second position, the cascade segment (116) is in a radially inner position at least partially within the bypass passage for changing a direction of a flow of air to generate reverse thrust.