Aspirated Compressors for High Altitude Engines

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$99,928.00
Award Year:
2010
Program:
SBIR
Phase:
Phase I
Contract:
NNX10CC84P
Agency Tracking Number:
094241
Solicitation Year:
n/a
Solicitation Topic Code:
A2
Solicitation Number:
n/a
Small Business Information
Aurora Flight Sciences Corporation
9950 Wakeman Drive, Manassas, VA, 20110
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
604717165
Principal Investigator:
Nathan Fitzgerald
Principal Investigator
(617) 500-0279
nfitzgerald@aurora.aero
Business Contact:
Scott Hart
Financial Analyst
(617) 500-0536
shart@aurora.aero
Research Institution:
n/a
Abstract
Aurora Flight Sciences proposes to incorporate aspirated compressor technology into a high altitude, long endurance (HALE) concept engine. Aspiration has been proven to increase the stage loading of gas turbine compressors and fans, potentially allowing weight reduction through the reduction of compression stages or through the reduction of stresses through decreased spool speeds. Additionally, aspiration has the potential to increase the low Reynolds number capability of an engine through improved control of the viscous boundary layer. Low Re capability is important for the performance of high altitude engines operating in low density air, as well as of lower power, micro-scale engines. Although the component level benefits of aspiration have been experimentally verified and the design techniques established, the issues surrounding the integration of the technology in an engine system have yet to be adequately addressed. The performance benefit of aspiration to an engine system will depend on the details of how bleed air from the compressor is utilized elsewhere in the engine cycle. The maximum benefit of the technology will also depend on the net weight reduction achievable once all supporting subsystems are taken into account. Aurora proposes to investigate the interdependences between aspiration flow requirements, weight reduction, and overall cycle efficiency as part of an optimization effort to maximize the capability of a HALE engine. The effort will define the benefits of compressor aspiration in a low Reynolds number environment and provide the rational for using the HALE mission as a launch application for this promising technology.

* information listed above is at the time of submission.

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