Non-Equilibrium Pulsed Plasma Ignitor

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$99,970.00
Award Year:
2002
Program:
STTR
Phase:
Phase I
Contract:
F49620-03-C-0001
Award Id:
56059
Agency Tracking Number:
F023-0188
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
2766 Indian Ripple Rd, Dayton, OH, 45440
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
884812025
Principal Investigator:
Michael Brown
Senior Scientist
(937) 252-2706
msbrown@innssi.com
Business Contact:
Larry Goss
President
(937) 429-4980
gosslp@innssi.com
Research Institute:
University of Southern California
Irene Andreadis
University of Southern Califor
Los Angeles, CA, 90089
(213) 740-7762
Nonprofit college or university
Abstract
"The proposed program is directed toward the development of a plasma ignitor to address relight and flame-holding problems experienced by high-altitude aircraft. Conventional spark ignitors are insufficient to overcome these problems that are associatedwith the reduced temperature and pressure of air-breathing aircraft at high altitude. The proposed ignitor is based on highly non-equilibrium pulsed discharges that initiate low-temperature chemistry which then drives ignition. The proposed Phase I effortcombines measurements made in a non-equilibrium, single-component low-molecular-weight hydrocarbon discharge with detailed chemistry modeling to a) characterize the nascent radical pool in the discharge and b) determine the key radical-initiatedpre-ignition chemical pathways. This information would permit the "tuning" of the electrical characteristics of the discharge to optimize the ignition capability of the plasma kernel. The Phase II effort would extend this work to heavy-molecular-weighthydrocarbons and mixtures, leading to the design of a prototype plasma ignitor for testing on model combustors. The proposed plasma ignitor will augment or replace conventional spark ignitors in high-altitude aircraft. The plasma ignitor will initiatehydrocarbon ignition and promote flame holding in the reduced temperature and pressure environment that is characteristic of subsonic, high-altitude, air-breathing aircraft engines."

* information listed above is at the time of submission.

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