High Temperature Sensor Materials Optimization and Fabrication Methods

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-09-M-5219
Agency Tracking Number: F083-079-0665
Amount: $100,000.00
Phase: Phase I
Program: SBIR
Awards Year: 2009
Solicitation Year: 2008
Solicitation Topic Code: AF083-079
Solicitation Number: 2008.3
Small Business Information
1980 Olivera Ave, Suite D, Concord, CA, 94520
DUNS: 149397015
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Mike McFarland
 Principal Investigator
 (925) 798-5770
Business Contact
 Ann Mulville
Title: Senior Contracts Administ
Phone: (925) 798-5770
Email: submissions302@lunainnovations.com
Research Institution
The purpose of this project is to demonstrate the feasibility of using an innovative, nanoparticle inkjet process for directly writing high temperature health monitoring sensors on turbine engine and thermal protection system components without the need for expensive sputtering, CVD, clean room or photolithography equipment. The inkjet process allows sophisticated sensor geometries and material combinations to be produced on the component in a matter of minutes as opposed to the hours needed to produce the sensors using the conventional clean room/sputtering approach. The nanoparticle inkjet process is capable of applying a wide variety of ceramic and refractory metal materials. In this project a number of ceramic materials will be investigated for high temperature strain and TC sensor use. These materials are conductive ceramics that are stable at high temperatures in air and oxidizing environments up to or exceeding 1600° C. BENEFIT: The development of low cost, robust, high temperature sensors will allow: 1) the monitoring of critical structures for degradation during space vehicle reentry, 2) measuring the operating parameters in extremely hot environments such as the compressor and turbine sections to validate computer modeling codes, 3) allow active control of pressure surges in turbine engines, 4) allow the ability to diagnose turbine engine and thermal protection system health and estimate component capability for future missions, 5) and help reduce the significant costs of testing and qualifying turbine engines.

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

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