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Compact Stable Low Residence Time Inter-Turbine Combustor

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-09-M-2983
Agency Tracking Number: F083-107-1180
Amount: $99,959.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: AF083-107
Solicitation Number: 2008.3
Solicitation Year: 2008
Award Year: 2009
Award Start Date (Proposal Award Date): 2009-03-24
Award End Date (Contract End Date): 2009-12-24
Small Business Information
410 Sackett Point Road
North Haven, CT 06473
United States
DUNS: 178154456
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Shahrokh Etemad
 Director, Engineering and
 (203) 287-3700
Business Contact
 J. Kevin Burns
Title: Process Engineering Manag
Phone: (203) 287-3700
Research Institution

PCI proposes a novel reformer/injector system for aviation fuel combustion that offers the ability to produce compact/low residence time combustion at high efficiency.  This technology offers a simple, light-weight, compact and cost-effective design providing stable combustion with low emissions in two stages for gas turbine engines.  In the first stage, the Liquid to Gaseous Fuel Reformer will gasify and partially reform the liquid aviation fuel.  The resulting enhanced reactivity gas will, in the second stage, be combusted in a novel, compact, low emissions combustor.  The combustor residence time will be shorter than in a traditional combustor through vaporization in the reformer and the reduction in flame length/residence time due to combustion of a highly reactive gas.  Reduced in-engine residence time, allows application in tight engine train space requirements (small aircraft, UAV, interturbine burner) with increased efficiency and reduced emissions.  During Phase I, PCI will show feasibility of the reformer/injector system by analyzing reactivity enhancement through fuel reforming and predicting ability of the injector to stabilize short residence time combustion.  Phase II would extend the analysis by performing subscale and full scale testing of the system with eventual demonstration in a high pressure test rig. BENEFIT: This technology would have applications in military and commercial subsonic/supersonic engines by allowing reduction of combustor size and lowering gaseous emissions such as NOx, carbon monoxide and unburned hydrocarbons.  This technology will be of benefit in the field of interturbine combustors for system efficiency improvements.  Other applications include improvements to liquids reforming technology for fuel cell power generation systems and to low residence time combustion systems for power generation combustion systems (such as microturbines used in distributed generation) among others.

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

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