Refractory Composite Convection/Transpiration (CONTRAN) Cooling for NASP Engine Combustor

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$73,859.00
Award Year:
1993
Program:
SBIR
Phase:
Phase I
Contract:
n/a
Agency Tracking Number:
20242
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
Analytical Services &
107 Research Drive, Hampton, VA, 23666
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
H. Neal Kelly
(804) 865-7093
Business Contact:
() -
Research Institution:
n/a
Abstract
An innovative actively cooled structure concept is proposed which integrates proven cooling techniques and state-0f-the-art fabrication methods to extend the maximum combustor wall temperature, thereby reducing cooling requirements and aircraft weight while improving engine performance. Specifically, CONvective and TRANspiration cooling(CONTRAN) are uniquely combined, relying on hydrogen coolant to permeate a carbon-carbon structure providing oxidation and thermal protection. State-of-the-art fabrication techniques will be used during Phase I to develop the desired carbon-carbon permeability specimen based on thermal and boundary layer analytical estimates and experimental testing refinements. Preliminary characteristics will be defined based on results from undensified and densified carbon-carbon permeability tests, thermal and structural analysis, and shock impingement and coolant compatibility reviews. In Phase II, final concept design verification models will be fabricated and tested in realistic flowing gas environment representative of the NASP engine combustor. Based on the concept verification tests, a prototype 20 by 20 inch test panel of a CONTRAN cooled NASP engine combustor wall will be designed and analyzed. Pending funding, Phase II could include the fabrication and testing of the 20 by 20 inch panel.

* information listed above is at the time of submission.

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