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Modeling of a Sequential Two-Stage Combustor, SupplementA sequential two-stage, natural gas fueled power generation combustion system is modeled to examine the fundamental aerodynamic and combustion characteristics of the system. The modeling methodology includes CAD-based geometry definition, and combustion computational fluid dynamics analysis. Graphical analysis is used to examine the complex vortical patterns in each component, identifying sources of pressure loss. The simulations demonstrate the importance of including the rotating high-pressure turbine blades in the computation, as this results in direct computation of combustion within the first turbine stage, and accurate simulation of the flow in the second combustion stage. The direct computation of hot-streaks through the rotating high-pressure turbine stage leads to improved understanding of the aerodynamic relationships between the primary and secondary combustors and the turbomachinery.
Document ID
20050176385
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Hendricks, R. C.
(NASA Glenn Research Center Cleveland, OH, United States)
Liu, N.-S.
(NASA Glenn Research Center Cleveland, OH, United States)
Gallagher, J. R.
(NASA Glenn Research Center Cleveland, OH, United States)
Ryder, R. C.
(Flow Parametrics, LLC Bear, DE, United States)
Brankovic, A.
(Flow Parametrics, LLC Bear, DE, United States)
Hendricks, J. A.
(Diligent Design Toledo, OH, United States)
Date Acquired
August 23, 2013
Publication Date
March 1, 2005
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA/TM-2005-212631/SUPPL
E-14193/SUPPL
ISROMAC10-2004-037-Suppl
Meeting Information
Meeting: 10th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery
Location: Honolulu, HI
Country: United States
Start Date: March 7, 2004
End Date: March 11, 2004
Sponsors: Pacific Centre of Thermal Fluids Engineering
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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