Gas Turbine Rotor Assembly Compression Washer Retaining Ring
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing gas turbine engine rotor assembly and disassembly methods face challenges in maintaining secure coupling and efficient operation, particularly in maintaining a consistent preload between rotor components during assembly and disassembly.
Innovation Solution
A system utilizing a compression washer and a retaining ring to clamp together rotor components, with the compression washer providing a mechanical preload and the retaining ring reacting this load to secure the components, allowing for axial clamping and easy assembly and disassembly through controlled displacement of the retaining ring.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If traditional rotor assembly methods are used, then assembly is straightforward, but maintaining consistent preload between rotor components becomes difficult
Solution Approach 1:
A preload maintenance device is introduced as an intermediary tool during the rotor assembly process. This device includes a retaining ring that engages with grooves in the rotor components and a compression element that applies controlled force to maintain consistent preload between the first and second rotor components during assembly and disassembly operations
2Reliability
If rotor components are tightly coupled for secure operation, then operational reliability improves, but assembly and disassembly becomes more difficult
Solution Approach 1:
The coupling system transitions from a static tight connection to a dynamic controlled connection. The retaining ring can be displaced axially to release the compression element, allowing the coupling force to be dynamically adjusted or released as needed, facilitating easy assembly and disassembly while maintaining secure operation when engaged
Solution Approach 2:
The compression element acts as a mediator between the rotor components, providing the necessary clamping force for secure operation while being controllable through the retaining ring mechanism, thus enabling both reliable coupling and easy disassembly
3Manufacturing precision
If specialized tools are used for precise rotor assembly, then assembly precision improves, but the need for specialized tools increases complexity
Solution Approach 1:
The preload maintenance device is designed to be self-contained, with the retaining ring engaging directly with grooves in the rotor components and the compression element automatically applying the necessary preload. The system serves itself by using the rotor component geometry (grooves) to locate and constrain the assembly tools, eliminating the need for external specialized positioning tools
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
This solution ensures a secure and consistent coupling of rotor components during operation while facilitating efficient assembly and disassembly, reducing the need for specialized tools and maintaining operational preload across various conditions.
Implementation Method 1
a compression washer disposed between the first face and the second face, wherein the compression washer is operative to mechanically load the first face against the second face
Implementation Method 2
a retaining ring, wherein the first face, the first channel, the second face and the second channel are positioned so that the compression washer is in a state of compression between the first face and the second face when the retaining ring is positioned in both the first channel and the second channel; and wherein the retaining ring reacts the mechanical loading produced by the compression of the compression washer
Data Source
AI summary
One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique gas turbine engine main engine rotor. Still another embodiment is a unique method for assembling a gas turbine engine main engine rotor. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine rotors. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.