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Durable High Temperature Coatings for Utility Scale Gas Turbine Hot Gas Path Components

Award Information
Agency: Department of Energy
Branch: N/A
Contract: DE-SC0011335
Agency Tracking Number: 210371
Amount: $150,000.00
Phase: Phase I
Program: STTR
Solicitation Topic Code: 14c
Solicitation Number: DE-FOA-0000969
Timeline
Solicitation Year: 2014
Award Year: 2014
Award Start Date (Proposal Award Date): 2014-02-18
Award End Date (Contract End Date): 2014-11-17
Small Business Information
4401 Dayton-Xenia Rd.
Dayton, OH 45432-1894
United States
DUNS: 074489217
HUBZone Owned: No
Woman Owned: Yes
Socially and Economically Disadvantaged: No
Principal Investigator
 Amarendra Rai
 Dr.
 (937) 426-6900
 arai@ues.com
Business Contact
 Rick Weddle
Title: Mr.
Phone: (937) 426-6900
Email: rweddle@ues.com
Research Institution
 The Pennsylvania State University
 
P.O. Box 30
State College, PA 16804-16804
United States

 () -
 Nonprofit college or university
Abstract

For advanced gas turbines where turbine inlet temperature reaches 2650F and beyond, the current state-of-the-art thermal barrier coating (TBC) systems are not adequate to provide the needed protection for the metallic components of the turbine engine. Thus there is a need to develop new chemistries and architectures for TBC systems (both bond coats and top TBCs) with enhanced durability. For the top TBC, we propose to develop innovative coating chemistry having the desired attributes for higher temperature operation in advanced gas turbines. For the bond coat we propose to develop a coating chemistry having thermo-mechanical compatibility with the relevant metallic alloy. The developed top coat, bond coat and complete TBC system (metallic alloy/bond coat/top coat) will be evaluated in terms of relevant characteristics needed for application in advanced gas turbines including durability. TBC materials with new chemistries will be synthesized and their relevant characteristics will be evaluated. Bond coats having chemistries and thermo- mechanical properties compatible with turbine engine metallic components will be fabricated and evaluated. A complete TBC system with optimal bond coat and top TBC will be fabricated utilizing conventional techniques. Validation of the as-fabricated TBC system will be accomplished by evaluating its relevant characteristics and by comparing with the current TBC system. Commercial Applications and Other Benefits: The TBCs developed in this program will have application in turbine engines utilized in electric power production, propelling aircraft, pumping fluids etc. Successful completion of the project will enable gas turbine engine to operate at elevated temperatures with higher efficiency (lower cost), lower emission (less environmental pollution) and increased reliability and performance

* Information listed above is at the time of submission. *

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