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A Novel Test Method for Measuring Interlaminar Tensile Strength of Ceramic Matrix Composites at High Temperature

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-08-C-0490
Agency Tracking Number: N082-154-0992
Amount: $79,999.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: N08-154
Solicitation Number: 2008.2
Solicitation Year: 2008
Award Year: 2008
Award Start Date (Proposal Award Date): 2008-09-02
Award End Date (Contract End Date): 2009-03-02
Small Business Information
2600 Campus Drive, Suite D
Lafayette, CO 80026
United States
DUNS: 161234687
HUBZone Owned: No
Woman Owned: Yes
Socially and Economically Disadvantaged: No
Principal Investigator
 Dash Weeks
 Senior Engineer
 (303) 664-0394
Business Contact
 Lori Pike
Title: Sr. Finance and Contracts Mannager
Phone: (303) 664-0394
Research Institution

The use of ceramic matrix composite (CMC) materials in aero-engine hot-section components has grown substantially over recent decades. Attributes that make these materials attractive to aero-engine designers include their lower specific weight, higher creep resistance, higher thermoshock resistance and higher specific strength over a large temperature range in comparison to superalloys and greater damage tolerance in comparison to monolithic ceramics. However, there remains a great deal of uncertainty regarding the strength properties of CMCs at high temperatures due in large part to a lack of standardized test protocols applicable to high temperatures. In particular, there exists no test method that enables accurate measurements of the interlaminar tesnsile strength of CMC material at high temperatures. To address this shortcoming, Composite Technology Development (CTD) proposes the development of a novel test protocol that enables accurate and reliable measurement of interlaminar tensile strength of CMC material at temperatures up to 2300oF. The proposed test protocol will utilize a non-contact heating method that enables quick and efficient heating up to the target temperature of 2300oF. The proposed test protocol will also allow for test samples to be prepared from existing stock of thin-gage, aero-section-hot-component-relevant CMC material thereby making custom test sample manufacture unnecessary.

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

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