Compressor Disk Balancing Holes for Vibration Reduction
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Solution Overview
Problem
Larger gas turbine engines face challenges in balancing their compressor rotor assemblies to reduce vibrations and enhance reliability, as existing methods may not adequately address stress concentrations and fatigue issues caused by imbalanced rotating components.
Innovation Solution
A first stage compressor disk with forward and aft balancing holes and a radial flange, along with a method for determining and mounting weights and airfoils, is used to achieve rotational balance, reducing vibrations and stress concentrations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a single balancing hole configuration is used in the compressor disk, then the manufacturing process is simple, but the ability to reduce vibrations and balance the rotor assembly is insufficient
Solution Approach 1:
The balancing system is segmented into multiple groups of balancing holes (first group, second group, third group) distributed at different locations on the compressor disk. Each group can receive balancing weights independently, allowing the system to address complex vibration patterns through distributed counterbalancing rather than relying on a single balancing location.
Solution Approach 2:
Different groups of balancing holes are positioned at specific locations around the compressor disk to address local imbalance issues. The first group is positioned to counteract vibrations in one plane while the second and third groups address vibrations in different planes, providing localized balancing solutions throughout the rotor assembly.
2Reliability
If traditional balancing methods are used, then the manufacturing process is straightforward, but stress concentrations and fatigue issues persist in the rotating components
Solution Approach 1:
The balancing holes are pre-drilled and positioned on the compressor disk during manufacturing, allowing balancing weights to be installed later during assembly or maintenance. This preliminary preparation enables precise weight placement to counteract imbalances without requiring complex modifications during the balancing process itself.
Solution Approach 2:
The system allows for adjustment of balancing parameters by changing the weights installed in the balancing holes. Different weight configurations can be tried to optimize the balance, and the parameters can be modified without changing the physical structure of the compressor disk, facilitating iterative balancing to eliminate stress concentrations.
3Reliability
If multiple groups of balancing holes are implemented, then vibration reduction effectiveness is improved, but the complexity of the balancing system increases
Solution Approach 1:
The multiple groups of balancing holes serve multiple functions: they can be used independently or in combination to address different types of vibrations, they work with various weight configurations, and they can be adjusted during different stages of assembly and maintenance. This multi-functionality allows a single balancing system design to handle diverse balancing requirements without requiring separate systems for different vibration modes.
Data Source
AI summary
A first stage compressor disk of a gas turbine engine includes a body. The body includes a forward end, an aft end, and an outer surface. The body also includes a plurality of forward balancing holes through the outer surface. The forward balancing holes align circumferentially about the body. The body further includes a plurality of aft balancing holes through the outer surface. The aft balancing holes align circumferentially about the body and are located aft of the forward balancing holes. The first stage compressor disk also includes a radial flange at the aft end of the body. The radial flange extends radially outward from the body. The radial flange includes slots for mounting airfoils.