Innovation

Self-Healing Matrices for High Temperature Turbine Engine Composites

University of California System: University of California, Santa Barbara
posted on 02/03/2012

A novel matrix concept for silicon carbide (SiC)-based ceramic matrix composites (CMCs) that has the ability to self heal under high temperature conditions.

Suggested Uses

  • Turbine Engines used for:
    • Propulsion (e.g. Jet Engines)
    • Power Generation (e.g. Electricity Plants)


This technology is available for licensing.

Advantages

  • Long-term reliability through self-healing
  • Largely decreased turbine engine weight when replacing superalloys, which is of substantial importance for aircraft propulsion engines
  • Increased turbine engine efficiency and decreased emissions due to increased operating temperature capabilities of up to 2700°F (1482°C)


Innovation Details
 

Detailed Description

Researchers at the University of California, Santa Barbara have developed a novel matrix concept for silicon carbide (SiC)-based ceramic matrix composites that has the ability to self heal under high temperature conditions. It accomplishes this by forming a stable, protective water vapor barrier in-situ when exposed to a high temperature oxidizing environment. When used in combination with an outer environmental barrier coating (EBC), the matrix concept provides robustness in case of cracking or local loss of the EBC, allowing the surface to form a thin layer of EBC-like material that self-heals the exposed area. The matrix concept may even eliminate the need for an explicit EBC layer altogether in less aggressive environments, contributing to valuable weight savings on rotating components. This technology promises to allow composite component implementation in propulsion and power generation turbine engines, resulting in reduced weight and increased efficiency due to high temperature capabilities.

File Number: 22238 

Other Information:

Background

SiO2 volatilization and oxidative degradation are significant obstacles when considering SiC-based composite materials in turbine engine combustion environments, and current protective coatings can crack or spall and expose the underlying composite to harsh conditions. For this reason, there is a need to increase the reliability of composite turbine hardware to exploit their high temperature and low density properties.


IP Protection

Copyright: ©2012, The Regents of the University of California

License Online

This innovation currently is not available for online licensing. Please contact Franco Caporale at University of California System: University of California, Santa Barbara for more information.

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Case Manager:

Franco Caporale Franco Caporale

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