Intercalated Balancing Ring Assembly for Compact Rotor Balancing
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Solution Overview
Problem
Aircraft engine rotor assemblies face challenges in balancing rotating components within limited engine space, leading to rotational vibrations due to manufacturing tolerances and variability, which existing dual counterweight balancing systems do not adequately address.
Innovation Solution
A rotary part assembly with an annular body and balancing ring configuration, where counterweights are secured to the balancing ring and mounted concentrically with the annular body, allowing for compact radial design and intercalation within the engine volume, reducing the radial footprint and enabling effective balancing of rotor assemblies.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional dual counterweight balancing systems are used, then balancing capability is provided, but radial space consumption is excessive and assembly complexity increases
Solution Approach 1:
The balancing ring is nested within the annular body structure, with the balancing ring positioned concentrically inside the annular body. This nesting arrangement allows the balancing components to occupy shared radial space rather than requiring separate radial envelopes, thereby reducing the overall radial footprint while maintaining both balancing capabilities
Solution Approach 2:
The patent merges the balancing ring and annular body into a single integrated assembly where both components share common mounting features and concentric alignment. The counterweights on the balancing ring and the annular body structure work together as a unified balancing system, eliminating the need for separate dual counterweight systems and reducing assembly complexity
2Reliability
If traditional balancing systems are used, then balancing function is achieved, but device complexity and assembly difficulty increase
Solution Approach 1:
The balancing ring serves multiple functions simultaneously: it provides the balancing counterweights, acts as a mounting structure for the counterweights, and interfaces with the annular body through shared mounting features. This multi-functionality reduces the number of separate components needed and simplifies the overall assembly process
Solution Approach 2:
The balancing system is segmented into modular components (annular body, balancing ring, counterweights) that can be independently manufactured and then assembled together using standardized mounting features. This segmentation allows for easier manufacturing and assembly while maintaining the complete balancing function
3Manufacturing precision
If more balancing components are added, then balancing precision improves, but engine volume and weight increase
Solution Approach 1:
By nesting the balancing ring within the annular body structure, the system achieves high balancing precision through the combined mass distribution of both components without requiring additional external space. The concentric arrangement allows precise balancing while maintaining compact engine volume
Solution Approach 2:
The patent utilizes the axial dimension by stacking the balancing ring and annular body concentrically along the rotation axis, rather than requiring additional radial or longitudinal space. This dimensional arrangement allows for enhanced balancing capability within the existing engine volume envelope
Data Source
Figure 1
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Figure 3~3B
AI summary
An annular parts assembly (20') for mounting onto a shaft (S) of an aircraft engine (10) is provided. The assembly (20') comprises a first annular body (40) having a surface defining a plurality of pulling features (41) extending from a remainder of the surface, the pulling features (41) circumferentially spaced apart on the surface. The assembly (20') comprises a second annular body (40) defining a balancing ring (50), the balancing ring (50) concentric with the first annular body (40), the balancing ring (50) having a plurality of protrusions (51) and circumferential spaces (52) between adjacent ones of the plurality of protrusions (51), the circumferential spaces (52) accommodating the pulling features (41) such that the pulling features (41) of the first annular body (40) and the protrusions (51) intercalate.