CMC Rotor Disk Stress Distribution via Integrated Bladed Design
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Solution Overview
Problem
Gas turbine engine rotor components face challenges in withstanding elevated temperatures and oxidizing gas flows, particularly in maintaining structural integrity and reducing stress concentrations in conventional disk structures.
Innovation Solution
The use of Ceramic Matrix Composite (CMC) materials for disk components, featuring a ring-strut-ring configuration with integrated bladed rotor design, full hoop shroud, and optimized rail geometry to distribute load and minimize stress, replacing conventional bolted or tied structures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If conventional bolted or tied structures are used to fasten rotor disks, then assembly and disassembly is simplified, but stress concentrations occur and structural integrity deteriorates at high temperatures
Solution Approach 1:
The patent merges the rotor disk and blade into a single integrated CMC component, eliminating the need for separate fastening structures. The disk includes integrated blade roots that are monolithically formed with the disk body, creating a unified structure that eliminates stress concentrations at bolt holes or attachment points while maintaining structural integrity in high-temperature environments.
Solution Approach 2:
The patent employs Ceramic Matrix Composite (CMC) materials for the rotor disk and blade structure. These composite materials provide high-temperature strength and oxidation resistance, enabling the component to withstand the harsh thermal environment while maintaining structural integrity without requiring complex fastening systems.
2Reliability
If traditional rotor disk designs are used, then manufacturing is simpler, but stress concentrations reduce reliability in oxidizing gas flow environments
Solution Approach 1:
The rotor disk and blade are manufactured as a single integrated CMC component, eliminating interfaces and fastening points where stress concentrations would occur. This monolithic design improves reliability by removing weak points while the integrated structure is manufactured using advanced CMC fabrication processes.
Solution Approach 2:
The use of CMC materials provides inherent resistance to stress concentrations and oxidation, enhancing reliability in the oxidizing gas flow environment. The composite structure distributes stresses more evenly throughout the component compared to traditional metal alloys.
3Temperature
If conventional disk structures are used, then weight is higher, but thermal resistance is insufficient at elevated temperatures
Solution Approach 1:
The patent uses CMC materials that exhibit superior high-temperature thermal resistance compared to conventional metal superalloys. These ceramic-based composites can withstand elevated temperatures without significant strength degradation, enabling the rotor to operate in hotter environments while the lightweight nature of CMC reduces overall component weight.
Data Source
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AI summary
A ceramic matrix composite (CMC) disk (64C) for a gas turbine engine (20) includes a CMC hub (68C) defined about an axis (A) and a multiple of CMC airfoils (66C) integrated with the CMC hub (68C). A corresponding rotor module (62) is also provided.