Aircraft Turbomachine Balancing System With Offset Annular Rows
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Solution Overview
Problem
Conventional turbomachine balancing systems have limited maximum balancing capacity, especially when the dimensions of the inlet cowl are small, leading to restrictive maintenance operations and reduced turbomachine lifespan.
Innovation Solution
The implementation of a dual annular row balancing system with axially offset mounting ports, allowing for temporary balancing on one row and subsequent rebalancing on the other row to increase the maximum balancing capacity without modifying the distribution of balancing members on the second row.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a single annular row of mounting ports is used, then the device complexity is low, but the balancing capacity is limited
Solution Approach 1:
The patent transitions from a single annular row to two annular rows of mounting ports arranged at different axial positions. This dimensional change from one plane to two planes multiplies the available mounting ports while maintaining the same radial geometry, thereby doubling the balancing capacity without proportionally increasing complexity
Solution Approach 2:
The balancing system is segmented into two separate annular rows, each capable of independent balancing operations. This segmentation allows the total balancing capacity to be distributed across two rows, enabling greater overall capacity while maintaining manageable complexity through modular organization
2Adaptability or versatility
If the number of mounting ports is increased, then the balancing capacity increases, but the diameter of the annular row must increase, which is constrained by the inlet cowl dimensions
Solution Approach 1:
Instead of increasing the diameter of a single annular row to accommodate more ports, the patent utilizes the axial dimension by creating a second annular row at a different axial position. This allows the system to achieve higher balancing capacity while maintaining the same radial diameter constraints imposed by the inlet cowl
3Adaptability or versatility
If balancing members are placed in closely spaced mounting ports, then the balancing capacity increases, but interactions between inner radial ends of members occur
Solution Approach 1:
The patent resolves the interaction problem by distributing mounting ports across two different axial planes. This axial separation ensures that balancing members in closely spaced angular positions do not have their inner radial ends interacting, as they are separated along the axial dimension while maintaining high angular resolution
4Adaptability or versatility
If a dual annular row system is implemented, then the balancing capacity increases, but the ease of operation decreases due to more ports to manage
Solution Approach 1:
The dual annular row system is segmented into two independent balancing planes, each with its own set of mounting ports. This segmentation allows operators to perform balancing operations on one row at a time, making the increased capacity manageable through systematic, step-by-step procedures rather than requiring simultaneous management of all ports
Data Source
AI summary
The invention relates to a balancing system of an aircraft turbomachine comprising a first annular row of first mounting ports for mounting balancing members, and a second annular row of second mounting ports for mounting balancing members which is axially offset from the first annular row, the number and angular positions of the first mounting ports being identical to the number and angular positions of the second mounting ports.