Locking Spacer Assembly for Turbine Engine Disc Grooves
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Solution Overview
Problem
Conventional locking spacer assemblies in turbine engines are prone to disassembly due to centrifugal forces and often require multi-piece components that do not fit securely, leading to potential damage and installation challenges.
Innovation Solution
A locking spacer assembly formed from multiple components, including end supports with stepped profiles and a mid spacer, utilizing a locking device with angled surfaces to secure the assembly within the disc groove without interacting with adjacent blades, preventing disassembly during operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If multi-piece spacers are used to fill the remaining space in the disc groove, then the void can be filled, but centrifugal forces cause the spacers to come apart and cause extensive damage to the turbine engine
Solution Approach 1:
The spacer assembly is divided into multiple components: a first end support, a second end support, and a locking device. These segmented parts can be assembled together to fill the void while maintaining integrity under centrifugal forces through the locking mechanism that prevents separation.
Solution Approach 2:
The locking device acts as an intermediary element between the first and second end supports, providing a positive locking mechanism that prevents the spacer components from separating under centrifugal loads while allowing the assembly to fill the void effectively.
2Quantity of substance
If conventional spacers are used, then the void can be filled, but the spacers come apart if either side of the devices develop clearance relative to adjacent turbine components
Solution Approach 1:
The locking device is designed to engage with the end supports in a predetermined configuration, establishing a stable locked state before operation begins. This preliminary locking action prevents clearance development and maintains assembly stability throughout turbine operation.
Solution Approach 2:
The locking device serves as an intermediary that transfers and distributes loads between the end supports and the void-filling structure, maintaining stable composition by preventing relative movement and clearance development under operational conditions.
3Quantity of substance
If multi-piece spacers are used, then the void can be filled, but the components have problems fitting together
Solution Approach 1:
The spacer assembly is segmented into standardized components (first end support, second end support, locking device) that can be manufactured separately and then assembled together through the locking mechanism, simplifying manufacturing while ensuring proper fit and function.
Solution Approach 2:
The locking device serves as an intermediary that facilitates the assembly process by providing a straightforward locking interface between the end supports, making it easier to manufacture and assemble the multi-piece spacer configuration while maintaining void-filling effectiveness.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The locking spacer assembly remains securely positioned and self-sustaining, preventing unwanted disassembly and ensuring reliable operation of turbine blades by using angled surfaces and a retainer to wedge the end supports into lateral recesses, maintaining assembly throughout the turbine engine's operational stages.
Implementation Method 1
The locking device may include first and second angled surfaces configured to bear against the support surfaces of the first and second end supports such that as the locking device is moved relative to the first and second end supports while keeping the locking device in contact with the first and second end supports, at least one force vector is developed that urges the first and second end supports away from each other and into the lateral recesses of the turbine component.
Data Source
AI summary
A locking spacer assembly for filling a void between adjacent components in a turbine engine. In at least one embodiment, the locking spacer assembly may be configured to be inserted between adjacent turbine blades in a disc groove in a turbine blade stage assembly. The locking spacer assembly may be formed from fore and aft end supports and a locking device having fore and aft angled surfaces for urging the fore and aft end supports into lateral recesses in the disc groove. The locking spacer assembly may also include a mid spacer positioned between the fore and aft end supports. A retainer may be attached to the locking device to draw the fore and aft angled surfaces of the locking device into contact with the fore and aft support surfaces and urge the first and second end supports into lateral recesses in the disc groove.