Sectored Rotor Blade Coatings for Gas Turbine Vibration Tuning
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Solution Overview
Problem
Existing bladed rotors for gas turbine engines lack effective methods to tune their dynamic response and reduce vibratory issues, limiting their performance and efficiency.
Innovation Solution
The implementation of a bladed rotor design where rotor blades are divided into sectors with different coatings, each sector having unique coating configurations to alter the dynamic response and reduce vibrations, achieved by varying coating materials and thicknesses across the rotor blades.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If rotor blades are divided into sectors with different coating configurations, then the dynamic response is tuned and vibratory responses are reduced, but the device complexity increases due to multiple coating types and thicknesses
Solution Approach 1:
The rotor blade array is segmented into multiple sectors, where each sector contains rotor blades with identical coating configurations. Different sectors have different coating types or thicknesses. This segmentation allows the system to achieve mistuning effects for reducing vibratory responses while maintaining manufacturing feasibility through standardized sector-based production.
Solution Approach 2:
Different sectors of the rotor blade array are assigned different coating qualities (types or thicknesses) to create localized variations in dynamic characteristics. For example, certain sectors may have thicker thermal barrier coatings while others have thinner coatings, allowing targeted modification of vibratory behavior without requiring all blades to be different.
2Reliability
If different coating materials and thicknesses are applied to rotor blades in different sectors, then the fundamental bending modes are mistuned, but the manufacturing precision requirements increase
Solution Approach 1:
By grouping rotor blades into sectors with identical coating configurations, the manufacturing process can be standardized within each sector. This reduces the overall precision requirement compared to making every blade unique, as coatings can be applied in batches to entire sectors rather than individually to each blade.
Solution Approach 2:
The invention varies discrete parameters (coating type and thickness) across different sectors rather than requiring continuous variation. This approach to parameter changes simplifies manufacturing control, as there are a limited number of standardized coating specifications to maintain rather than continuous precision requirements.
Data Source
AI summary
An apparatus is provided for a gas turbine engine. This apparatus includes a bladed rotor rotatable about an axis. The bladed rotor includes a rotor disk and a plurality of rotor blades projecting radially out from the rotor disk. The rotor blades are arranged circumferentially around the rotor disk in an array. The array of the rotor blades are divided into a plurality of sectors including a first sector and a second sector. The rotor blades are disposed in the first sector including a plurality of first rotor blades. Each of the first rotor blades includes a first coating. The rotor blades are disposed in the second sector including a plurality of second rotor blades. Each of the second rotor blades includes a second coating that is different from the first coating.