Aircraft Engine High-Pressure Shaft Mounting Tool
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Solution Overview
Problem
Aircraft engine maintenance is hindered by the lightweight construction and lack of a separate support structure, leading to sequential maintenance of components and increased processing time due to the inability to dismantle certain components simultaneously without proper axial and radial securing of the high-pressure shaft.
Innovation Solution
A tool comprising a shaft end cap element, a connector element with a fixing element, and a spring element that applies a predetermined spring force radially to secure the high-pressure shaft axially, allowing for simultaneous dismantling and radial movement while simulating the weight force, thus preventing undesired stresses and enabling complete axial fixation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If the high-pressure shaft is completely fixed in the radial direction, then the shaft is held in the required position, but undesired stresses are introduced due to fixed bearing at the rear end
Solution Approach 1:
The patent changes the constraint parameter from rigid fixation to spring-loaded contact, allowing the shaft to maintain radial position while accommodating thermal expansion and weight-induced deflections, thereby preventing undesired stresses
2Productivity
If the front bearing mount and high-pressure turbine module are dismantled simultaneously, then maintenance time is reduced, but the high-pressure shaft cannot be properly secured axially
Solution Approach 1:
The patent introduces an intermediary device (holding tool with shaft end cap receptacle and fixing element) that provides axial securing functionality independent of the front bearing mount and turbine module, enabling simultaneous dismantling of both components while maintaining shaft security
Solution Approach 2:
The holding tool is prepared and positioned on the high-pressure shaft before dismantling the front bearing mount and turbine module, ensuring axial securing is established in advance to enable simultaneous removal of both components
3Stability of the object's composition
If the high-pressure shaft is held with a fixed bearing, then radial position is stable, but weight force cannot be simulated and undesired stresses occur
Solution Approach 1:
The patent uses a spring element to apply a counteracting force that simulates the weight force of the high-pressure turbine, allowing the shaft to deflect naturally under simulated weight while maintaining stable radial position through controlled spring pressure
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 tool allows for complete axial securing and radial holding of the high-pressure shaft during maintenance, reducing processing time and preventing damage by simulating the weight force and allowing for adjustable spring force, thereby facilitating efficient maintenance without introducing additional stresses.
Implementation Method 1
a spring element that is stationary relative to the shaft end cap receptacle is provided for applying a predetermined spring force to the shaft end cap element in the radial direction
Data Source
Figure 1
Figure 2
Figure 3a~3b
AI summary
The invention relates to a tool (1) for mounting and axially fixing the high pressure shaft (80) of an aircraft engine in a disassembled high-pressure turbine stage and to the use thereof. The tool (1) comprises: - a shaft end cap element (2) with an inner radius which is adapted to a specified shaft diameter for plugging onto the turbine-side end (84) of the high-pressure shaft (80), - a shaft end cap receiving area (3) for radially moving and receiving the shaft end cap element (2) in an axially limited manner in a first direction, and - a prevention element (4) which can be secured to the shaft end cap receiving area (3) and comprises a shaft (5) that can be introduced into the high-pressure shaft, comprising a fixing element (6) for axially securing the shaft end cap receiving area (3), wherein a spring element (12) which is stationary relative to the shaft end cap receiving area (3) is provided for applying a specified spring force to the shaft end cap element (2) in the radial direction. The use according to the invention relates to the attachment of said tool to the high-pressure shaft (80) of an aircraft engine.