MODIFICATION
A -- Defense Sciences Research and Technology
- Notice Date
- 7/7/2004
- Notice Type
- Modification
- NAICS
- 541990
— All Other Professional, Scientific, and Technical Services
- Contracting Office
- Other Defense Agencies, Defense Advanced Research Projects Agency, Contracts Management Office, 3701 North Fairfax Drive, Arlington, VA, 22203-1714
- ZIP Code
- 22203-1714
- Solicitation Number
- BAA04-12
- Response Due
- 2/2/2005
- Archive Date
- 2/17/2005
- Point of Contact
- Brett Giroir, Deputy Director, DSO, Phone (571) 218-4224, Fax (571) 218-4553,
- E-Mail Address
-
bgiroir@darpa.mil
- Description
- SMALL UNINHABITED AIR VEHICLE ENGINES (SUAVE), SOL BAA04-12, Addendum 6, DUE: 10/15/04. POC: Dr. William Coblenz, DARPA/DSO, Ph: (571) 218-4647, Email: baa04-12@darpa.mil; Website Submission: http://www.sainc.com/dso0412. Description. The Defense Sciences Office is interested in innovative research ideas for design and prototyping of Small Uninhabited Air Vehicle Engines (SUAVE). The SUAVE program seeks to demonstrate gas turbine engines under 10 horsepower that are highly efficient (greater than 25% thermal efficiency), power densities greater than 2 horsepower per pound, capable of utilizing heavy fuel (i.e., JP-8, JP-5), and with a durability exceeding 500 hours. Engine designs with high efficiency over a large power range would be especially useful for UAV mission profiles that typically include both sprint and loiter modes of operation. Successful offerors will combine innovative designs that exploit the high temperature capabilities of structural ceramics. It is the intent of this Broad Agency Announcement (BAA) to solicit proposals that only consider revolutionary advancements in small size scale propulsion. Background. Ceramic components are of interest for the hot section components of gas turbine engines where they enable higher turbine inlet temperatures and, therefore, higher thermal efficiencies. In most cases, the ceramic components are substituted for metal components with only minor design changes to accommodate the brittle failure mode of ceramics. The compressive strength of ceramic materials are typically a factor of 10 higher than the tensile strength, suggesting the adoption of designs in which rotating ceramic components go into compression as they spin-up. This design approach suggests ceramic blades placed on the inside of rotating cylinders rather than blades attached to a rotating shaft. Engines of this design have been referred to as either exoskeleton or inside-out designs. Design variations might include: utilization of air or magnetic bearings; radial staging of turbine and compressor sections; and/or high power density motor-generators to extract power from turbine sections and operate inlet fans. Accommodation of steady-state and transient thermal stresses is particularly important in ceramic engine components. Exploiting rapid prototyping methods that build ceramic or metal components without part-specific tooling and which can be modified to spatially control composition, may be useful in producing surface compressive stresses and thermally insulating surface layers. Commercially available gas turbine engines in this power range are typically less than 10% efficient. Design issues specific to small gas turbines related to the high surface to volume ratio to be addressed include reduction of tip clearance losses, thermal losses, and reduced transit time for combustion. Miniaturization of auxiliary equipment, such as transmissions and fuel pumps, can also be a problem at small size scale. The design of a transmission for a small turboprop gas turbine engine spinning in excess of 150,000 rpm would be particularly challenging. Since power density of electric motors and generators increases with rotational speed, turboelectric variant gas turbines might be particularly effective. Gas turbine engines designed to produce thrust directly for propulsion are also of interest in this program; however, conditions used to calculate engine efficiency must be clearly stated relative the intended use in powering small UAVs. Silicon nitride and silicon carbide have been the materials that have attracted the most interest for use in gas turbine engines. Designs that will put the ceramic components into compression and manufacturing methods (such as Solid Freeform) may justify consideration of other ceramic systems for use in engines. It is anticipated that once developed these small gas turbine engines will find additional uses, such as: generation of electrical power on the battlefield, battery recharging systems that operate on logistics fuel NOTE: THIS NOTICE WAS NOT POSTED TO WWW.FEDBIZOPPS.GOV ON THE DATE INDICATED IN THE NOTICE ITSELF (07-JUL-2004); HOWEVER, IT DID APPEAR IN THE FEDBIZOPPS FTP FEED ON THIS DATE. PLEASE CONTACT fbo.support@gsa.gov REGARDING THIS ISSUE.
- Web Link
-
Link to FedBizOpps document.
(http://www.eps.gov/spg/ODA/DARPA/CMO/BAA04-12/listing.html)
- Record
- SN00616709-F 20040709/040707213533 (fbodaily.com)
- Source
-
FedBizOpps.gov Link to This Notice
(may not be valid after Archive Date)
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