Conical Rotor Disk for Low-Pressure Turbine Stability
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Solution Overview
Problem
Turbomachines for aircraft engines face challenges in achieving high propulsion efficiency, compact construction, and reduced weight due to high mechanical and thermal loads, which are not adequately addressed by existing rotor arrangements.
Innovation Solution
A rotor arrangement for a low-pressure turbine with a conical disk design that expands radially in the flow direction, providing rotational rigidity and stabilizing radial and axial displacements, thereby enhancing efficiency and mechanical stability through a compact and weight-optimized design.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If a smaller number of rotor disks or stages is used to meet mechanical and thermal loads, then construction length is reduced and weight is lowered, but the ability to withstand high mechanical and thermal loads is compromised
Solution Approach 1:
The rotor disk geometry is changed from a conventional cylindrical shape to a conical shape with a specific half-angle alpha. This parameter change in the geometric configuration allows the disk to better distribute and withstand the mechanical and thermal loads, enabling weight reduction while maintaining strength capability.
Solution Approach 2:
The rotor disk is designed with a conical geometry featuring curved surfaces characterized by a half-angle alpha. This curvature design optimizes the stress distribution across the disk, allowing it to withstand high loads more efficiently than flat or cylindrical designs, thus enabling reduced weight while maintaining load-bearing capacity.
2Length of moving object
If the rotor disk geometry is optimized for compact construction, then construction length is reduced, but radial and axial displacements increase affecting efficiency
Solution Approach 1:
The conical geometry parameter (half-angle alpha) is specifically optimized to balance two competing requirements: achieving compact construction length while simultaneously controlling radial and axial displacements. By adjusting this geometric parameter, the design finds an optimal compromise that satisfies both compactness and stability requirements.
Solution Approach 2:
The conical shape with its specific curvature provides structural rigidity that limits radial and axial displacements of the rotor stages. The curved geometry distributes mechanical stresses more effectively, maintaining stability even when the overall construction length is reduced for compact design.
Data Source
AI summary
The invention relates to a rotor arrangement for a low-pressure turbine of a turbomachine with end-side linkage to a shaft of the turbomachine, comprising a plurality of rotating stages, which are arranged in a flow direction and are connected to one another, wherein the last rotating stage in the flow direction can be linked to the shaft by a rotor disk.