Abrasive Tip on Ceramic Matrix Composite Turbine Blade
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Solution Overview
Problem
Ceramic matrix composite materials used in gas turbine engine blades are prone to degradation due to rubbing with other engine parts, leading to material limitations and performance issues.
Innovation Solution
The integration of an abrasive tip made from ceramic materials, such as chopped ceramic fibers or monolithic ceramic pieces, bonded to the radially-outwardly facing surface of the blade to protect the ceramic matrix composite materials from rub damage, using ceramic matrix materials like silicon-carbide, carbon-boron, and silicon-nitride particles, and employing laminate layers or slurry infiltration for coupling and protection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If ceramic matrix composite materials are used in turbine blades to withstand high temperatures, then temperature resistance is improved, but the materials become prone to rubbing damage from engine parts
Solution Approach 1:
The turbine blade employs a composite structure combining ceramic matrix composite materials for high-temperature resistance with an abrasive tip layer for rubbing protection. The abrasive tip comprises ceramic particles (such as silicon carbide, aluminum oxide, or boron carbide) embedded in a ceramic matrix material, creating a dual-function composite that simultaneously withstands thermal exposure and mechanical abrasion from contact with engine structures.
2Reliability
If an abrasive tip is added to protect ceramic matrix composite materials from rubbing, then durability is improved, but device complexity increases
Solution Approach 1:
The abrasive tip is integrated with the ceramic matrix composite airfoil through direct bonding, forming a unified protective structure. The tip is bonded to the radially outwardly facing surface of the airfoil, creating a combined structure that simplifies manufacturing compared to separate attachment methods while maintaining protective functionality against rubbing damage.
Solution Approach 2:
The abrasive tip is applied specifically to the radially outwardly facing surface of the airfoil where rubbing contact occurs, rather than coating the entire blade. This localized application provides protection precisely where needed while minimizing additional complexity and material usage on non-critical surfaces.
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
The abrasive tip effectively prevents rub damage to the ceramic matrix composite materials, maintaining their integrity and reducing rub temperatures, thereby enhancing the durability and performance of the turbine blades.
Implementation Method 1
The abrasive tip may be bonded to a radially-outwardly facing surface of the airfoil included in the primary body
Implementation Method 2
the abrasive tip may be sized to cover at least a portion of the radially-outwardly facing surface of the airfoil to protect ceramic matrix composite materials of the airfoil from rub by structures mounted radially-outward of the turbine blade
Data Source
AI summary
The present disclosure relates generally to blades used in gas turbine engines. More specifically designs in accordance with the present disclosure include turbine blades comprising ceramic matrix composite materials with abrasive tips coupled thereto.