Coupled Transpired and Discretely Injected Films

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$99,698.00
Award Year:
2011
Program:
SBIR
Phase:
Phase I
Contract:
NNX11CD94P
Award Id:
n/a
Agency Tracking Number:
105146
Solicitation Year:
2010
Solicitation Topic Code:
A2.10
Solicitation Number:
n/a
Small Business Information
OH, Dayton, OH, 45431-1262
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
Y
Duns:
782766831
Principal Investigator:
SivaramGogineni
Principal Investigator
(937) 266-9570
spgogineni@gmail.com
Business Contact:
SivaramGogineni
Business Official
(937) 266-9570
spgogineni@gmail.com
Research Institute:
Stub




Abstract
NASA, and all users of turbomachinery, continuously requires improvements in engine durability and efficiencies. As combustion engineers push turbine inlet temperatures to new extremes, cooling designers are faced with increasing heat loads and less available coolant usage. Surface cooling techniques such as film cooling have proven invaluable in this quest. Films generated by forcing the coolant to bleed through a porous substrate have been shown to perform substantially better than discrete film injection in a thermal sense. However, the associated aerodynamic penalties limit the application. On the other hand, discretely injected films have drawbacks as well, including non-uniform coolant profiles significant mixing with the hot working fluid, lowering their effectiveness. Spectral Energies, LLC and the University of Central Florida propose a novel, low risk approach to surface cooling wherein traditional discrete film holes are embedded within a transpiring porous strip. The motivation behind this approach is multi-faceted, with the ultimate goal of developing a cooling arrangement which possesses the thermo-mechanical benefits of a transpired film, the aerodynamic benefits of discrete film injection, and mixing characteristics that are some compromise of the two.

* information listed above is at the time of submission.

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