Turbine Retaining Ring Flange Axial Force Decomposition
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Solution Overview
Problem
In turbo-machine rotors, conventional support systems fail to maintain adequate axial pre-tension due to centrifugal and thermal expansions, leading to reduced cooling efficiency and potential distortions from excessive axial forces.
Innovation Solution
A flange and ring assembly where the flange exerts both axial and radial components of force, with an oblique bearing face to decompose the force and prevent excessive axial effort from causing distortion, ensuring robust support and sealing of the rotor disk blades.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the flange is axially pre-tensioned to prevent displacement of the ring, then the ring is securely retained axially, but the flange becomes detached from the ring under centrifugal and thermal expansion forces
Solution Approach 1:
The flange bearing face is inclined at an angle to the axial direction, transforming the axial pre-tension force into a combination of axial and radial components. This dimensional transformation allows the flange to maintain contact with the ring while accommodating centrifugal and thermal expansion forces through the radial component of the bearing force.
Solution Approach 2:
The bearing force parameters are modified by introducing an inclined bearing face, changing the force distribution from purely axial to having both axial and radial components. This parameter change enables the flange to adapt to operational expansions while maintaining secure ring retention.
2Reliability
If excessive axial pre-tension is applied to the ring, then the ring is firmly supported axially, but the flange distorts under the excessive axial effort
Solution Approach 1:
The inclined bearing face redirects the excessive axial force into a radial component, preventing flange distortion while maintaining axial support. The force is transformed from a purely axial direction that causes distortion to a radial direction that reinforces the ring support without compromising flange integrity.
Solution Approach 2:
The excessive axial force, which would normally cause flange distortion and harm, is converted through the inclined bearing face into a beneficial radial force that reinforces the ring support. The harmful axial effort is transformed into a useful radial component that prevents ring displacement.
3Reliability
If the flange is made rigid to maintain pre-tension, then the ring is securely retained, but the flange cannot accommodate centrifugal and thermal expansions
Solution Approach 1:
The inclined bearing face creates a dynamic force distribution system where the axial pre-tension is continuously adjusted into axial and radial components based on operational conditions. This dynamic adaptation allows the flange to accommodate centrifugal and thermal expansions while maintaining secure ring retention through the radial component of the bearing force.
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 configuration effectively converts excessive axial forces into radial efforts, maintaining the ring's support and preventing distortions, while maintaining cooling efficiency by guiding air flow through the grooves.
Implementation Method 1
the flange is bearing against the ring so that the flange support force on the ring has an axial component and a radial component relative to the axis of revolution X
Implementation Method 2
Under the effect of the centrifugal forces and the thermal expansions due to the high temperature gases coming from the combustion chamber of the engine, the axial pre-tension being applied on the ring 30 by the flange 1 is not sufficient
Implementation Method 3
A cooling channel is arranged between the flange 1 and the upstream ferrule 12 of the rotor disk 10 so as to guide a fresh air flow, tapped upstream the low pressure turbine stage, in the supporting grooves for the blades 20 arranged in the rotor disk 10. The air circulates in the grooves under the feet 23 of the blades 20, thereby cooling the disk 10 and protecting the latter against excessive temperatures
Implementation Method 4
The truncated central part of the flange 1 takes on the truncated shape of the upstream ferrule 12 of the rotor disk 10 so that the cooling channel has a constant section between the flange 1 and the truncated upstream part 12 of the rotor disk 10
Data Source
AI summary
A retaining ring assembly for at least one blade of a rotor disk of a turbine engine and a supporting flange for the ring. The flange and the ring are rotating parts having an axis X, the flange including an attachment edge configured to be connected to the rotor disk and a free edge configured to bear against the retaining ring; and the flange bears against the ring such that the bearing force of the flange on the ring has an axial component and a radial component relative to the axis of revolution X.