Gas turbine combustor CFD modeling has become an important combustor design tool in the past few years, but CFD models are generally limited to the flow field inside the combustor liner or the diffuser/combustor annulus region. Although strongly coupled in reality, the two regions have rarely been coupled in CFD modeling. A CFD calculation for a full model combustor from compressor diffuser exit to turbine inlet is described. The coupled model accomplishes the following two main objectives: (1) implicit description of flow splits and flow conditions for openings into the combustor liner, and (2) prediction of liner wall temperatures. Conjugate heat transfer with nonluminous gas radiation (appropriate for lean, low emission combustors) is utilized to predict wall temperatures compared to the conventional approach of predicting only near wall gas temperatures. Remaining difficult issues such as generating the grid, modeling Swirled vane passages, and modeling effusion cooling are also discussed.
Skip Nav Destination
Article navigation
January 1999
Research Papers
CFD Modeling of a Gas Turbine Combustor From Compressor Exit to Turbine Inlet
D. S. Crocker,
D. S. Crocker
CFD Research Corporation, 215 Wynn Drive, Huntsville, AL 35805
Search for other works by this author on:
D. Nickolaus,
D. Nickolaus
CFD Research Corporation, 215 Wynn Drive, Huntsville, AL 35805
Search for other works by this author on:
C. E. Smith
C. E. Smith
CFD Research Corporation, 215 Wynn Drive, Huntsville, AL 35805
Search for other works by this author on:
D. S. Crocker
CFD Research Corporation, 215 Wynn Drive, Huntsville, AL 35805
D. Nickolaus
CFD Research Corporation, 215 Wynn Drive, Huntsville, AL 35805
C. E. Smith
CFD Research Corporation, 215 Wynn Drive, Huntsville, AL 35805
J. Eng. Gas Turbines Power. Jan 1999, 121(1): 89-95 (7 pages)
Published Online: January 1, 1999
Article history
Received:
April 1, 1998
Online:
November 19, 2007
Citation
Crocker, D. S., Nickolaus, D., and Smith, C. E. (January 1, 1999). "CFD Modeling of a Gas Turbine Combustor From Compressor Exit to Turbine Inlet." ASME. J. Eng. Gas Turbines Power. January 1999; 121(1): 89–95. https://doi.org/10.1115/1.2816318
Download citation file:
Get Email Alerts
Numerical Analysis of High Frequency Transverse Instabilities in a Can-Type Combustor
J. Eng. Gas Turbines Power
Analysis of Unburned Methane Emission Mechanisms in Large-Bore Natural Gas Engines with Prechamber Ignition
J. Eng. Gas Turbines Power
Development and Evaluation of Generic Test Pieces for Creep Property Assessment of Laser Powder Bed Fusion Components
J. Eng. Gas Turbines Power (September 2024)
Multidisciplinary Design Methodology for Micro-Gas-Turbines—Part II: System Analysis and Optimization
J. Eng. Gas Turbines Power (October 2024)
Related Articles
Aspects of Cooled Gas Turbine Modeling for the Semi-Closed O 2 / CO 2 Cycle With CO 2 Capture
J. Eng. Gas Turbines Power (July,2004)
Optimization of Wall Cooling in Gas Turbine Combustor Through Three-Dimensional Numerical Simulation
J. Eng. Gas Turbines Power (October,2005)
Siemens Westinghouse Advanced Turbine Systems Program Final Summary
J. Eng. Gas Turbines Power (July,2004)
Metal Temperature Prediction of a Dry Low NO x Class Flame Tube by Computational Fluid Dynamics Conjugate Heat Transfer Approach
J. Eng. Gas Turbines Power (March,2016)
Related Proceedings Papers
Related Chapters
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Thermodynamic Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential