Three Dimensional CFD Analysis of the GTX Combustor
- Author:
- Steffen, C. J., Jr.
- Published:
- June 2002.
- Physical Description:
- 1 electronic document
- Additional Creators:
- Edwards, J. R. and Bond, R. B.
Online Version
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- Restrictions on Access:
- Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access - Summary:
- The annular combustor geometry of a combined-cycle engine has been analyzed with three-dimensional computational fluid dynamics. Both subsonic combustion and supersonic combustion flowfields have been simulated. The subsonic combustion analysis was executed in conjunction with a direct-connect test rig. Two cold-flow and one hot-flow results are presented. The simulations compare favorably with the test data for the two cold flow calculations; the hot-flow data was not yet available. The hot-flow simulation indicates that the conventional ejector-ramjet cycle would not provide adequate mixing at the conditions tested. The supersonic combustion ramjet flowfield was simulated with frozen chemistry model. A five-parameter test matrix was specified, according to statistical design-of-experiments theory. Twenty-seven separate simulations were used to assemble surrogate models for combustor mixing efficiency and total pressure recovery. ScramJet injector design parameters (injector angle, location, and fuel split) as well as mission variables (total fuel massflow and freestream Mach number) were included in the analysis. A promising injector design has been identified that provides good mixing characteristics with low total pressure losses. The surrogate models can be used to develop performance maps of different injector designs. Several complex three-way variable interactions appear within the dataset that are not adequately resolved with the current statistical analysis.
- Other Subject(s):
- Collection:
- NASA Technical Reports Server (NTRS) Collection.
- Note:
- Document ID: 20020061704.
NAS 1.15:211572.
E-13357.
NASA/TM-2002-211572.
Simulation Subcommittees Joint Meeting; 8-12 Apr. 2002; Destin, FL; United States.
Combustion, Airbreathing Propulsion, Propulsion Systems Hazards, and Modelling; 8-12 Apr. 2002; Destin, FL; United States. - Terms of Use and Reproduction:
- Copyright, Distribution as joint owner in the copyright.
View MARC record | catkey: 15968148