Nacelle Front Frame Non-Penetrating Assembly
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Solution Overview
Problem
The conventional connection between the front frame and outer wall in aircraft propulsion nacelles disrupts the laminar airflow, leading to increased drag and reduced energy efficiency due to the formation of irregularities from rivets and other fastening methods.
Innovation Solution
The connection between the front frame and outer wall is achieved using assembly means located inside the anterior part, such as brackets or fastening tabs, which do not penetrate the outer wall, ensuring continuity of the aerodynamic surface and maintaining laminar flow, while avoiding stiffening and deformation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If the front frame is connected to the outer wall using conventional fastening methods (rivets penetrating the outer wall), then the structural connection is achieved, but the aerodynamic surface continuity is disrupted and laminar flow is broken
Solution Approach 1:
The invention extracts the fastening function from the outer wall surface by moving the assembly means inside the anterior part. The front frame connects to the outer wall through internal mounting elements (brackets, tabs, or adhesive layers) that do not penetrate the outer wall, thereby removing the source of aerodynamic irregularities while preserving structural connection.
Solution Approach 2:
The invention introduces intermediary elements (mounting elements, brackets, fastening tabs, or adhesive layers) that mediate the connection between the front frame and the outer wall. These intermediaries are positioned inside the anterior part and transfer mechanical loads without disrupting the external aerodynamic surface.
2Stability of the object's composition
If the outer wall is stiffened to prevent deformation, then structural stability is improved, but the aerodynamic efficiency is reduced due to increased weight and potential flow separation
Solution Approach 1:
The invention applies local quality by providing structural support only where needed through internal mounting elements. Instead of globally stiffening the entire outer wall, the mounting elements provide localized reinforcement at connection points, maintaining overall stability without adding excessive weight that would harm aerodynamic efficiency.
3Object-generated harmful factors
If assembly means are located inside the anterior part, then the aerodynamic surface continuity is maintained and laminar flow is preserved, but the manufacturing complexity increases
Solution Approach 1:
The invention segments the connection system into separate functional components: the front frame, the outer wall, and internal mounting elements. This segmentation allows each component to be optimized independently and assembled through non-penetrating connections, simplifying manufacturing while maintaining aerodynamic surface continuity.
Data Source
AI summary
An anterior part of a nacelle of an aircraft propulsion assembly, which comprises an air intake lip, an outer panel extending an outer part of the air intake lip, an inner structure extending an inner part of the air intake lip, a front frame connecting the outer wall to the air intake lip or to the inner structure. The outer panel and the outer part of the air intake lip together form an outer wall of the anterior part. The front frame and the outer wall are connected to one another by assembly means located inside the anterior part. The anterior part constituted in this manner ensures laminar flow of the air on an outer surface of the anterior part and reduces drag. A nacelle of a propulsion unit, comprising an anterior part of this kind is also provided.