Turbine Rotor Disk Segmented Blade Retention Slots
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Solution Overview
Problem
The existing blade retention slot configuration in turbine engine rotor assemblies allows air leakage across the rotor disk, reducing efficiency and structural integrity, as there is no structural connection between slot portions of the rotor disk.
Innovation Solution
The design includes blade retention slots that extend axially and radially into the rotor disk, with a neck and root portion, and apertures that enhance retention of rotor blades, using machining techniques with rotating cutting tools to create these features, thereby improving structural integrity and reducing air leakage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If blade retention slots extend axially through the rotor disk, then rotor blades can be retained in the rotor disk, but air leakage occurs across the rotor disk reducing efficiency
Solution Approach 1:
The blade retention slot is segmented into multiple portions: a first portion extending axially from the first disk end, a second portion extending radially from the outer disk surface, and a third portion connecting these portions. This segmentation allows the slot to retain blades while blocking axial air leakage paths through the rotor disk.
Solution Approach 2:
The slot configuration transitions from a simple axial through-slot to a three-dimensional path that includes radial and circumferential components. By adding the radial portion extending from the outer disk surface and the connecting portion, the slot blocks air leakage in multiple dimensions while maintaining blade retention functionality.
2Reliability
If blade retention slots extend axially through the rotor disk, then rotor blades can be retained in the rotor disk, but structural integrity of the rotor disk is reduced
Solution Approach 1:
The slot is divided into discrete portions that are strategically positioned to minimize structural disruption. The first portion extends axially to secure the blade, while the second and third portions extend radially and circumferentially to close off leakage paths without requiring a complete axial through-slot that would severely compromise disk integrity.
Solution Approach 2:
The slot geometry is optimized locally at different positions: the first portion provides blade retention at the disk end, while the second and third portions provide leakage blocking at radial and circumferential locations. This localized optimization maintains structural integrity in regions where the slot does not extend.
Data Source
AI summary
A turbine engine rotor assembly includes a turbine engine rotor disk that extends axially along a centerline between a first disk end and a second disk end, and radially to an outer disk surface. The rotor disk includes one or more blade retention slots arranged circumferentially around the centerline. A first of the blade retention slots extends axially into the rotor disk from a disk end surface at the first disk end to a slot end surface, and radially into the rotor disk from the outer disk surface to a slot base surface.