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Computation of the flow field in an annular gas turbine combustorThe KIVA-II code was modified to calculate the 3D flow field in a typical annular gas turbine combustor. The airblast fuel nozzle, cooling baffle, cooling slots, primary and dilution jets, and effusion cooling (bleed) pads were accounted for in this calculation. The turbulence and combustion were modeled using the k-epsilon model and laminar Arrhenius kinetics, respectively. The fuel was modeled as an evaporating liquid spray. The results illustrate the complicated flow fields present in such combustors. From the results obtained to date it appears that the modified KIVA-II code can be used to study the effects of different annular combustor designs and operating conditions.
Document ID
19930065906
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cline, Michael C.
(Los Alamos National Lab. NM, United States)
Deur, John M.
(Sverdrup Technology, Inc. Brook Park, OH, United States)
Micklow, Gerald J.
(NASA Lewis Research Center Cleveland, OH, United States)
Harper, Michael R.
(Florida Univ. Gainesville, United States)
Kundu, Krishna P.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 16, 2013
Publication Date
June 1, 1993
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 93-2074
Meeting Information
Meeting: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit
Location: Monterey, CA
Country: United States
Start Date: June 28, 1993
End Date: June 30, 1993
Sponsors: SAE, ASEE, ASME, AIAA
Accession Number
93A49903
Funding Number(s)
CONTRACT_GRANT: NASA ORDER C-30050-R
CONTRACT_GRANT: NAG3-1113
Distribution Limits
Public
Copyright
Other

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