Innovative Burn Resistant Material System

Award Information
Agency:
Department of Defense
Branch
n/a
Amount:
$149,923.00
Award Year:
2013
Program:
SBIR
Phase:
Phase I
Contract:
FA9300-13-M-1009
Award Id:
n/a
Agency Tracking Number:
F131-169-0587
Solicitation Year:
2013
Solicitation Topic Code:
AF131-169
Solicitation Number:
2013.1
Small Business Information
1701 Military Trail, Suite 110, Jupiter, FL, -
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
Y
Duns:
048159342
Principal Investigator:
John Appleby
Program Manager
(561) 427-6470
JAppleby@fttinc.com
Business Contact:
Lloyd Mazer
Director of Contracts and Pricing
(561) 427-6337
LMazer@fttinc.com
Research Institution:
n/a
Abstract
ABSTRACT: Liquid rocket propulsion systems require the use of high pressure LOX, and therefore have the need for LOX compatible materials. This is especially true in LOX turbopumps, which have inducers, impellers, discharge volutes, and housings exposed to or submerged in LOX. The high pressures present in these turbopumps dictate that the LOX compatible materials also be high strength. LOX compatible materials are also needed for injectors, valves, and oxygen rich turbines. LOX compatible materials, also known as combustion resistant materials, will not burn when in contact with LOX. Some materials may be LOX compatible only up to a certain pressure level or flow velocity; however, materials that are compatible with LOX at all pressure and flow velocity levels are needed for use in advanced liquid rocket propulsion systems. Throughout the evolution of the gas turbine, materials with specific benefits have been applied as surface treatments when the material alone does not have sufficient structural strength. The use of coatings eliminates a significant amount of characterization and mechanical property testing that is required before new substrate materials can be introduced in structural applications. This effort proposes the application of a robust burn resistant vitrious enamel coating to components exposed to LOX. BENEFIT: Potential application for all future and existing liquid propellant engine turbopumps including booster and upper stage engines. The coating can be applied to any metallic turbopump component in the current fleet of engines with minimal design or hardware modifications. Other potential applications include all pumps used in industrial commercial sector applications to move oxygen. The coating system can be applide to existing designs and incorporated into new designs.

* information listed above is at the time of submission.

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