Foldable Aircraft Engine Ventilator Cover Design
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Solution Overview
Problem
The increasing size of ventilator covers on aircraft engine assemblies leads to aerodynamic performance reductions and risks of interaction with wing flaps due to deformation under external air pressure, as existing solutions fail to adequately address these issues.
Innovation Solution
The design incorporates foldable ventilator covers with articulation axes and guiding mechanisms using thrust inverter covers and air inlet structures, featuring guiding rails and a locking mechanism to enhance resistance to deformation and improve aerodynamic performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If the ventilator cover size is increased to improve dilution level, then the ventilator diameter increases, but the aerodynamic performance deteriorates due to deformation under external air pressure
Solution Approach 1:
The ventilator cover is divided into multiple sectors (first cover sector, second cover sector, third cover sector) that can move independently relative to each other. Each sector is articulated to allow independent deformation while maintaining overall cover integrity, reducing stress concentration and improving aerodynamic performance during high-dilution operation
Solution Approach 2:
The ventilator cover transitions from a static structure to a dynamic one with articulated sectors that can adapt their configuration. The cover sectors can pivot and adjust their positions in response to aerodynamic forces, allowing the cover to maintain better aerodynamic characteristics under varying pressure conditions while accommodating increased size for improved dilution
2Quantity of substance
If the ventilator cover size is increased to improve dilution level, then the ventilator diameter increases, but the cover deformation under external air pressure increases
Solution Approach 1:
The cover is segmented into multiple articulated sectors that can move independently, distributing the deformation stresses across multiple joints rather than concentrating them in a single rigid structure. This segmentation allows each sector to accommodate local pressure variations while maintaining overall cover stability
Solution Approach 2:
The cover structure changes its geometric parameters dynamically through the articulated sectors, which can alter their relative positions and orientations in response to external pressure. This allows the cover to adapt its shape and reduce deformation under varying aerodynamic loads
3Ease of operation
If the ventilator cover is opened for maintenance access, then maintenance operations become possible, but the risk of interaction with wing flaps increases during maximum opening
Solution Approach 1:
The cover is divided into multiple sectors that can be opened independently or in combination. This segmentation allows for controlled opening sequences that can provide adequate maintenance access while limiting the maximum extension of any single sector, thereby reducing the risk of interaction with wing flaps
Solution Approach 2:
The articulated sectors provide dynamic control over the opening configuration, allowing the cover to be positioned at various angles and orientations during maintenance. This dynamic capability enables optimization of the opening position to achieve sufficient access while maintaining safe clearance from wing flaps
Data Source
AI summary
For gains in terms of aerodynamic performance levels, an aircraft engine assembly includes a turbomachine, a fastening strut for the turbomachine, and at least one foldable ventilator cover which surrounds the turbomachine and which includes: a first cover sector which includes a first end portion which is mounted so as to be articulated to the fastening strut, along a first articulation axis, and a second cover sector which includes a first end portion which is mounted so as to be articulated to a second end portion of the first cover sector, along a second articulation axis parallel with the first articulation axis. The second end portion is mounted so as to be guided at one side and the other thereof by a thrust inverter cover of the engine assembly and an air inlet structure of this assembly, respectively.