Robust Cryogenic Compatible Turbo-machinery and Liquid Rocket Engine coatings

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9300-13-M-1004
Agency Tracking Number: F131-169-1184
Amount: $149,998.00
Phase: Phase I
Program: SBIR
Awards Year: 2013
Solicitation Year: 2013
Solicitation Topic Code: AF131-169
Solicitation Number: 2013.1
Small Business Information
1037 Watervliet-Shaker Road, Albany, NY, -
DUNS: 883926594
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Said Jahanmir
 VP
 (518) 862-4290
 sjahanmir@mitiheart.com
Business Contact
 Hooshang Heshmat
Title: Technical Director
Phone: (518) 862-4290
Email: hheshmat@miti.cc
Research Institution
N/A
Abstract
ABSTRACT: It is proposed to develop new thermal barrier coatings based on current MiTi Korolon coatings for the turbomachinery of the rocket engines. The proposed coating system will provide thermal and environmental protection and at the same time provides sufficient damping characteristics to prevent fatigue failure. Furthermore, when applied to the entire rotating group, including the shaft, the coating provides low friction and wear resistance to ensure reliable operation of the bearings. Korolon is a high temperature, scratch resistant flexible ceramic coating that has demonstrated excellent adhesion to nickel superalloys and thermal and environmental barrier characteristics that make it attractive to a wide array of applications to turbopump components. Collaborations will be established in Phase II with turbine engine OEMs to expand the application of the proposed coating system. BENEFIT: The coating technology developed in this program will have several civilian and military applications, aside from rocket engines. The proposed TBC can be used in UAVs, gas turbine engines, ramjet engines, cruise missiles, decoys, and small aircraft engines. The proposed technology also has a great potential for use in systems that require corrosion and wear resistant TBC coatings. Examples include: turbopumps, cryogenic liquid pumps/compressors, refrigerant compressors, and many others. The use of more efficient and durable TBC/EBC will lead to increased engine efficiency by maximizing turbine inlet temperature and/or reducing the amount of cooling air required for airfoils.

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

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