NASA SBIR 2010 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER: 10-1 A2.10-8672
SUBTOPIC TITLE: Propulsion Systems
PROPOSAL TITLE: Advanced Turbine Blade Cooling Techniques

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Micro Cooling Concepts, Inc.
7522 Slater Avenue, #122
Huntington Beach, CA 92647 - 7738
(714) 847-9945

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
David S Underwood
daveunderwood@microcoolingconcepts.com
7522 Slater Ave #122
Huntington Beach, CA 92647 - 7738
(714) 847-9945

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
Gas turbine engine technology is constantly challenged to operate at higher combustor outlet temperatures. In a modern gas turbine engine, these temperatures can exceed the blade and disk material limits by 600 oF or more, necessitating both internal and film cooling schemes in addition to the use of thermal barrier coatings. Internal convective cooling is inadequate in many blade locations, and both internal and film cooling approaches can lead to significant performance penalties in the engine.

Micro Cooling Concepts has developed a turbine blade cooling concept that provides enhanced internal impingement cooling effectiveness via the use of micro-structured impingement surfaces. These surfaces significantly increase the cooling capability of the impinging flow, as compared to a conventional untextured surface. This approach can be combined with microchannel cooling and external film cooling to tailor the cooling capability per the external heating profile. The cooling system can then be optimized to minimize impact on engine performance.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The proposed Phase I effort directly supports core NASA research efforts in turbine engine development, as well as the multi-agency Verstaile Affordable Advanced Turbine Engine (VAATE) initiative. It is also applicable to two-state to orbit designs.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Military and commercial aircraft can both benefit from this technology, which permits higher combustion temperatures with lower engine penalties than state-of-the-art turbine blade cooling technologies. The blade cooling concept could be also applied to power generation plants, which are also seeking means of operating at higher temperatures.

More generally, the enhanced impingement cooling techniques proposed here could be applied to a variety of cooling problems in the electronics, industrial processes, automotive, and laser industries.

TECHNOLOGY TAXONOMY MAPPING (NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.)
Active Systems
Heat Exchange
Isolation/Protection/Shielding (Acoustic, Ballistic, Dust, Radiation, Thermal)


Form Generated on 09-03-10 12:12