Computational Characterization of Aeroengine Combustor/Augmentor Fuel Injectors

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-11-C-0446
Agency Tracking Number: N101-028-1250
Amount: $999,985.00
Phase: Phase II
Program: SBIR
Awards Year: 2011
Solicitation Year: 2010
Solicitation Topic Code: N101-028
Solicitation Number: 2010.1
Small Business Information
2445 Faber Place, #100, Palo Alto, CA, -
DUNS: 179576715
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Hung Le
 General Manager
 (650) 521-0243
Business Contact
 Donna Carrig
Title: CFO
Phone: (408) 482-3749
Research Institution
The work proposed for this project arises from the need for modeling a realistic fuel atomization process in a complex combustor/augmentor fuel injector. In a real gas turbine combustor or augmentor, the injected liquid fuel undergo atomization for fast evaporation, mixing and combustion. Furthermore, this atomization process occurs in the spatial regions adjacent to solid walls. Experimental studies have been limited to either simple injector geometries, or to far field measurements, after most of the atomization has occurred. Thus this project aims to study the computational characteristics of geometrically complex aeroengine combustor/augmentor fuel injector under realistic operating conditions. The overall objective of this project is to develop a computational tool capable of predicting the atomization of liquid injected trough geometrically complex injectors under realistic operating conditions. The approach will be integrating the Refined Level Set Grid (RLSG) method with the Cascade"s unstructured flow solver. The simulation results will then be validated with parallel experiments. The computational code development is performed by Cascade in collaboration with Dr. Marcus Herrmann, whereas Cascade's OEM partner, United Technologies Research Center (UTRC), will assist in validation with experimental conditions and results.

* Information listed above is at the time of submission. *

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