Modular Engine Turbine Nut Access via Speed Reducer Opening
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Solution Overview
Problem
The modularity of aeronautical propulsion engines with gear reducer architectures is compromised due to the difficulty in accessing the internal turbine nut, requiring the dismantling of parts to maintain or replace components, which complicates maintenance and assembly operations.
Innovation Solution
A modular structure with a speed reducer that includes a first nut for securing the drive means to the trunnion and a second nut for the turbine shaft, allowing the first module to be separated without disassembling the speed reducer, and a central opening for tool access to the turbine nut, enabling the module to be disassembled and reassembled without losing modularity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If a speed reducer is placed between the LP shaft and the power transmission shaft to enable fan rotation at lower speed, then aerodynamic performance is improved, but maintenance complexity increases due to difficulty in accessing the turbine nut
Solution Approach 1:
The engine is divided into separate modules (first module with fan and LP compressor, second module with HP body, third module with LP turbine) that can be independently maintained. The speed reducer is integrated into the first module, allowing the turbine nut to be accessed by separating modules rather than dismantling the reducer itself.
Solution Approach 2:
The patent introduces an intermediary connection system where the turbine nut connects the LP turbine shaft to the fan shaft through the speed reducer. By designing the reducer with a through-opening and separate fixation points, the turbine nut becomes accessible as an intermediary element that can be serviced without complete disassembly.
2Adaptability or versatility
If the engine is divided into multiple modules for easier maintenance, then modularity is improved, but the turbine nut becomes hidden behind the speed reducer requiring dismantling
Solution Approach 1:
The engine is segmented into distinct modules that can be assembled and disassembled independently. The speed reducer is positioned and structured such that it does not block access to the turbine nut, allowing module separation while maintaining nut accessibility through strategic placement and design of the reducer components.
Solution Approach 2:
The patent resolves the spatial conflict by creating a through-opening in the speed reducer structure, allowing access to the turbine nut from the front end of the engine. This dimensional solution (creating a passage through the reducer) eliminates the need to dismantle the reducer while maintaining modularity.
3Volume of moving object
If the turbine nut is hidden behind the speed reducer, then compact design is achieved, but intervention on the first module requires dismantling of the reducer
Solution Approach 1:
The speed reducer is designed with a through-opening that acts as an intermediary access path. This allows maintenance personnel to reach the turbine nut from the front end of the engine without dismantling the reducer, significantly reducing maintenance time while preserving the compact integrated design of the first module.
Solution Approach 2:
The speed reducer is pre-designed with the through-opening feature during the manufacturing stage. This preliminary design decision eliminates the need for time-consuming disassembly operations during maintenance, as the access path is already prepared and integrated into the reducer structure.
Data Source
Figure 1~4
Figure 2~6
AI summary
The present invention relates to an engine (1) with a modular structure comprising a plurality of coaxial modules (A, B, C) with, at one end, a first module (A) comprising a power transmission shaft (3) and a speed reduction gear (7), said power transmission shaft being driven via the speed reduction gear (7) by a turbine shaft (2) secured to one (C) of said coaxial modules that is separate from the first module, the speed reduction gear comprising a drive means (8 and 9) fixed to the turbine shaft (2) and to a journal (13) of a shaft of a low-pressure compressor rotor (1 a), characterized in that it comprises a first nut (16) for fastening the drive means to the journal and a second nut (14) for fastening the drive means to the turbine shaft.