Propeller Shaft Front Flange Reinforcement for Bending Load Relief
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Propeller shafts in aircraft engines face significant stress concentrations due to bending moments from aerodynamic and gyroscopic loads, leading to potential service damage and reduced service life, particularly at the propeller shaft/hub interface.
Innovation Solution
A propeller shaft assembly design featuring a reinforcement web with perforations that extends radially inward from an annular wall, providing a fillet and intersecting the shaft axis, which helps distribute stress and reduce concentration by allowing fluid flow communication, while maintaining structural integrity and minimizing weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If the front portion of the propeller shaft is exposed to high stress from engine operation and service damage, then the shaft is subjected to significant bending moments from aerodynamic and gyroscopic loads, but stress concentration increases leading to reduced service life
Solution Approach 1:
The patent applies local quality by implementing a reinforcement web with specific geometric features (fillets, radii) at the critical front flange area where stress concentration occurs. The reinforcement web has varying thickness and curved transitions that locally enhance strength precisely where needed, rather than uniformly thickening the entire shaft. This localized structural modification addresses the high stress region without adding unnecessary weight elsewhere.
Solution Approach 2:
The patent employs curvature principles through filleted transitions and rounded corners at stress concentration points. The reinforcement web includes fillets with specific radii (e.g., R1, R2, R3) that create smooth curved transitions between different structural elements, eliminating sharp corners that would act as stress concentrators. This spherical/curved geometry distributes stress more evenly and prevents crack initiation.
2Strength
If a reinforcement web is added to reduce stress concentration, then structural integrity is improved, but device complexity increases
Solution Approach 1:
The patent merges the reinforcement web with the existing front flange structure, creating an integrated component rather than a separate attachment. The reinforcement web extends from the front flange and merges with the shaft body, forming a unified structure that reduces stress concentration while avoiding the complexity of separate reinforcement components, fasteners, or assembly steps.
Solution Approach 2:
The reinforcement web serves multiple functions simultaneously: it strengthens the front flange area, provides stress distribution pathways, creates fluid flow communication channels through its perforations, and maintains structural continuity with the shaft body. This multi-functionality reduces the need for additional separate components.
3Strength
If the reinforcement web is made thicker to improve stress distribution, then strength is enhanced, but weight increases
Solution Approach 1:
The reinforcement web varies its thickness locally rather than being uniformly thick throughout. It is thicker at critical stress concentration points (such as where it merges with the front flange and shaft body) and thinner in less critical areas, optimizing strength-to-weight ratio by placing material only where structurally necessary.
Solution Approach 2:
The curved and filleted geometry of the reinforcement web allows for gradual thickness transitions that maintain structural integrity while minimizing material usage. The rounded transitions distribute stress more efficiently than sharp corners, allowing for thinner overall sections while maintaining equivalent or superior strength.
Data Source
Figure 1
Figure 2A~2B
Figure 3A
AI summary
A propeller shaft assembly (20) for an aircraft engine (10) includes a shaft (22) having: an annular wall (32) extending circumferentially about a shaft axis (X) and circumscribing a hollowed interior (25H) defining a cavity (25) in a front end portion (23) of the shaft (22), the annular wall (32) having an outer surface (26) and an inner surface (33) facing radially inwardly to the cavity (25); and a front flange (27) projecting radially outwardly from the annular wall (32). The front flange (27) includes a hub side surface (28) defining an interface plane (P1) and adapted to abut with a propeller hub (18). The shaft (22) also includes a reinforcement web (40) defining an end wall (41) of the cavity (25), the reinforcement web (40) extending radially inwardly from the inner surface (33) of the annular wall (32). At least part of the reinforcement web (40) is radially aligned with the front flange (27). At least one perforation (PP) extends axially through the reinforcement web (40).