NASA SBIR 2019-I Solicitation

Proposal Summary

 19-1- A1.10-3499
 Hypersonic Technology - Innovative Manufacturing for High Temperature Structures
 Additive Manufacturing of SiC-SiC CMCs
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Advanced Ceramics Manufacturing
7800 South Nogales Highway
Tucson, AZ 85756- 9645
(520) 547-0850

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Zachary Wing
7800A South Nogales Highway Tucson, AZ 85756 - 9645
(520) 547-0861

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Mark Angier
7800A South Nogales Highway Tucson, AZ 85756 - 9645
(520) 547-0856
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

SiC-SiC ceramic matrix composites (CMC) offer significantly lower density and higher resistance against high temperature oxidation than conventional materials. They are widely used in aerospace and energy production industry in shrouds, combustor liners, blades, jet tabs and vanes, blast tubes, and nozzle throats. CMC use in aircraft engines is projected to double over the next five years.

It is necessary to reduce the cost of SiC-SiC CMC production and to increase durability of CMC components. There are different SiC-SiC CMC fabricating technologies, each of which has its advantages and disadvantages. Melt infiltration approach provides the greatest opportunities for commercialization/mass production, but it suffers with a drawback of residual free silicon, which invariably remains in the matrix, volatilize at high temperatures and form cracks. The excessive silicon may also react with environmental water vapor resulting in deterioration in service properties. All production methods are time and labor consuming and thus, expensive.

It is proposed to use laser assisted additive manufacturing (AM) process to build layer by layer near net shape preform 3D structures as well as to implement laser assisted AM infiltration of a SiC + C preform with molten silicon. It is also proposed to almost fully eliminate free silicon in SiC-SiC CMC by bonding Sifree into compounds with high energy of formation. Silicon carbide fabric/carbon preform will be infiltrated with the alloyed silicon melt which results in dense SiC matrix targeting free silicon content of ≤0.5%. The compositions of the preform and infiltrating melt will be optimized by analyzing the microstructures and phase compositions and by measuring density, flexural strength and fracture toughness of the consolidated CMC. Mechanical properties will also be measured after temperature aging tests.

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

Components of aerospace engines and other parts working at high temperatures in harsh environments.

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

High temperature components of military (Navy, Air Force, Army) and civilian aircraft engines; nuclear and fossil fuel power production turbines.

Duration: 6

Form Generated on 06/16/2019 23:35:22