Proposal Number:          21-1- A1.03-2120

          

          

   

Subtopic Title:
      Propulsion Efficiency - Propulsion Materials and Structures

          

          

   

Proposal Title:
      Computational design of CMAS-resistant multiphase thermal and environmental barrier coatings for CMCs

          

          

   

Firm:

          

QuesTek Innovations, LLC

          

   

Address:

          

1820 Ridge Avenue, Evanston, IL 60201

          

   

Phone:

          

(847) 328-5800                                                                                                                                                                                

          

   

Name:

          

Jiadong Gong

          

   

E-mail:

          

jgong@questek.com

          

   

Address:

          

1820 Ridge Avenue, IL 60201 - 3621

          

   

Phone:

          

(847) 425-8221                                                                                                                                                                                

          

   

Name:

          

Mr. Kevin Creely

          

   

E-mail:

          

kcreely@questek.com

          

   

Address:

          

1820 Ridge Avenue, IL 60201 - 3621

          

   

Phone:

          

(847) 328-5800                                                                                                                                                                                

          

   

Estimated Technology Readiness Level (TRL) :                                                                                                                                                          
Begin: 1
End: 2

          

          

     

Technical Abstract (Limit 2000 characters, approximately 200 words):

Although ceramic matrix composites (CMCs) have been a material of interest for gas turbine components with operating temperatures 100-150 °C higher than typical superalloy materials, the temperature capability of CMCs is still limited by the lack of environmental durability of coatings. One of the main degradation mechanisms at high temperature (>1200 °C) is due to calcia-magnesia-alumina-silicate (CMAS) deposit. Under this SBIR program, QuesTek Innovations LLC will utilize its expertise in Integrated Computational Materials Engineering (ICME) and Materials by Design® approach to design multilayer thermal-environmental barrier coatings (T-EBCs) with improved environmental durability for enhanced performance of advanced CMC engine components. While EBC such as ytterbium disilicate is promising for protection against volatilization of thermally grown oxide, it is ineffective as a long-term protection against CMAS attack. Phase I will focus on development of a multiphase TBC with desired properties such as high reactivity with CMAS, high fracture toughness, low thermal conductivity and small coefficient of thermal expansion. This multiphase TBC acts as sacrificial layer by promoting reactive crystallization to mitigate CMAS infiltration and protect underlying materials from CMAS attack. QuesTek will leverage computational thermodynamic models and databases to predict CMAS-coating interactions and develop a CMAS-resistant multilayer T-EBC capable of extended performance at temperatures at or above 1482°C by the end of Phase II. The proposed integrated computational and experimental approach will accelerate material and architecture design to balance multiple competing performance requirements by reducing the need for time-consuming experiments.

          

          

     

Potential NASA Applications (Limit 1500 characters, approximately 150 words):

Potential NASA applications will be propulsion components (nozzles, turbine vanes and blades, combustor liner, exhaust nozzle) for subsonic and supersonic fixed and rotary wing aircrafts and combustor panel components on hypersonic vehicles.

          

          

     

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words):

Potential non-NASA applications will be turbine components in future civilian aircraft propulsion systems (e.g. future generations of turbofan engines similar to CFM LEAP and GE9X) and turbine components in industrial gas turbine plants.

          

          

     

Duration:     6