Gas Turbine Rotor Structural Members With Varying Cross-Sections
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Solution Overview
Problem
Current gas turbine engine rotors face challenges in efficiently distributing loads and optimizing structural design to withstand centrifugal and aerodynamic loads while minimizing deflection of rotating blades.
Innovation Solution
The design incorporates a hub with structural members that increase in cross-sectional length and alignment as they extend from the hub to an annular ring, with airfoils extending radially outward, allowing for improved load distribution and airflow paths, and a method of transferring loads between the hub and airfoils via these structural members.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If structural members are designed with uniform cross-sections, then manufacturing is simpler, but load distribution and deflection resistance are suboptimal
Solution Approach 1:
The structural members are designed with non-uniform cross-sections where the cross-sectional area varies along the radial length. Specifically, the cross-sections are larger near the hub where loads are transferred and taper toward the annular ring, providing optimized load distribution and deflection resistance in each local region based on the specific loading conditions at that position.
Solution Approach 2:
The patent varies the geometric parameters of the structural members along their length, specifically changing the cross-sectional dimensions (width and thickness) as a function of radial position. This parameter variation allows the structural members to withstand varying centrifugal and aerodynamic loads more efficiently while maintaining structural integrity throughout the rotor assembly.
2Strength
If structural members are made thicker to withstand centrifugal loads, then strength improves, but weight increases
Solution Approach 1:
Rather than uniformly thickening all structural members, the patent applies varying cross-sectional dimensions localized to where needed. The structural members have larger cross-sections near the hub where centrifugal forces are highest and load transfer occurs, while tapering to smaller sections toward the outer radius where forces are lower, thus providing adequate strength without unnecessary weight.
Solution Approach 2:
The structural members are effectively segmented into multiple cross-sectional zones along their radial length, with each zone having optimized dimensions for its specific loading conditions. This segmentation allows the rotor to achieve required strength while minimizing overall weight by avoiding material in regions where it is not critically needed.
3Productivity
If cross-sections are aligned perpendicular to the rotation axis, then manufacturing is easier, but aerodynamic performance and load distribution are suboptimal
Solution Approach 1:
The structural members are designed with asymmetric cross-sections relative to the rotation axis, with the cross-sectional orientation and dimensions varying along the radial length. This asymmetric design optimizes both aerodynamic performance and load distribution, with the cross-sections angled or twisted to align with airflow patterns and stress trajectories, accepting increased manufacturing complexity for significant performance gains.
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 design enhances load distribution and airflow management within the rotor, providing improved performance and efficiency compared to prior art rotors in various applications and operating conditions.
Implementation Method 1
This structural component is typically designed to withstand the centrifugal and aerodynamic loads of the rotating components
Implementation Method 2
This structural component is typically designed to withstand the centrifugal and aerodynamic loads of the rotating components
Data Source
AI summary
A rotor for an aircraft engine includes a hub having a rotation axis, a circumferential array of structural members extending radially outward from the hub to an annular ring, the structural members having cross-sections that increase in length as the structural members extend from the hub to the annular ring, the length of each cross-section of the cross-sections defined by opposite edges of a structural member of the structural members that corresponds to that cross-section, and a circumferential array of airfoils extending radially outward from the annular ring.