Investigation The Effects of Choking And Combustion Products Swirling Frequency on Fractures of Gas Turbine Compressor Blades

Article Sidebar

PDF
Published: Aug 31, 2020
DOI: https://doi.org/10.61841/turcomat.v11i2.14298
Keywords:
CFD, fluid instability, turbomachines, Reacting flows

Main Article Content

Dr. J. MURALI NAIK
Associate Professor, Department of Mechanical Engineering, Holy Mary Institute of Technology and Sciences, Bogaram (v), Keesara(m), Medchal Dist, Hyderabad, Telangana-501301

Abstract

Premature blade fractures occurred in four gas turbine compressors at a refinery. To assess the impact of combustion instability on blade failure, such as choking and chamber resonance issues, 3D models of the combustion chamber structure and combustion flow were examined using finite element analysis and computational fluid dynamics codes, respectively. By comparing the natural frequencies of the combustion chamber with the combustion swirl frequency, it was determined that the chamber structure was not experiencing resonance. To verify the likelihood of choking, the Mach number of the combustion product flow was analyzed. The Mach number distribution results indicated that the flow was subsonic in the transition piece area. However, due to the presence of supersonic flow conditions near the swirl vanes, the flow could become supersonic under certain critical conditions. Therefore, it is recommended that operators maintain engine operation as close to the optimal design conditions as possible to avoid choking. The simulation results indicated that the blade fractures were not a result of combustion issues.

Downloads

Download data is not yet available.

Metrics

Metrics Loading ...

Article Details

How to Cite
NAIK, D. J. M. . (2020). Investigation The Effects of Choking And Combustion Products Swirling Frequency on Fractures of Gas Turbine Compressor Blades. Turkish Journal of Computer and Mathematics Education (TURCOMAT), 11(2), 684–693. https://doi.org/10.61841/turcomat.v11i2.14298
Issue
Vol. 11 No. 2 (2020)
Section
Research Articles
Creative Commons License

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

You are free to:

  1. Share — copy and redistribute the material in any medium or format for any purpose, even commercially.
  2. Adapt — remix, transform, and build upon the material for any purpose, even commercially.
  3. The licensor cannot revoke these freedoms as long as you follow the license terms.

Under the following terms:

  1. Attribution — You must give appropriate credit , provide a link to the license, and indicate if changes were made . You may do so in any reasonable manner, but not in any way that suggests the licensor endorses you or your use.
  2. No additional restrictions — You may not apply legal terms or technological measures that legally restrict others from doing anything the license permits.

Notices:

You do not have to comply with the license for elements of the material in the public domain or where your use is permitted by an applicable exception or limitation .

No warranties are given. The license may not give you all of the permissions necessary for your intended use. For example, other rights such as publicity, privacy, or moral rights may limit how you use the material.

Crossref
Scopus
Google Scholar
Europe PMC

References

Quinn, D. D., and Paxson, D. E., 1998, “A Simplified Model for the Investiga-tion of Acoustically

Driven Combustion Instabilities,” 34th Joint Propulsion Conference, Cleveland, OH, July 12–15.

Paxson, D., 2000, “A Sectored One-Dimensional Model for Simulating Com-bustion Instabilities

in Premix Combustors,” 38th Aerospace Sciences Meeting and Exhibit, Reno, NV, Jan. 10–13.

Schuermans, B., Bellucci, V., and Paschereit, C. O., 2003, “Thermoacoustic Modeling and

Control of Multi Burner Combustion Systems,” ASME, Paper No. GT2003-38688.

Schmitt, P., Poinsot, T., Schuermans, B., and Geigle, K. P., 2007, “Large-Eddy Simulation and

Experimental Study of Heat Transfer, Nitric Oxide Emissions and Combustion Instability in a

Swirled Turbulent High-Pressure Burner,” J. Fluid Mech., 570, pp. 17–46.

Caraeni, M. L., Caraeni, D. A., and Fuchs, L., 2003, “Fast Algorithm to Com-pute Resonance

Frequencies of a Combustion Chamber,” 9th AIAA/CEAS Aeroacoustics Conference and

Exhibit, Hilton Head, SC, May 12–14.

Bethke, S., Wever, U., and Krebs, W., 2005, “Stability Analysis of Gas-Turbine Combustion

Chamber,” 11th AIAA/CEAS Aeroacoustics Conference, Monte-rey, CA, May 23–25.

“R1 Compressor-Blade Failures Dominate Discussion at Annual Meeting,” 2007, Combined

Cycle Journal, Second Quarter, http://www.combinedcyclejournal.-

com/webroot/2Q2007/107,%20p%2072-92%20CTOTF.pdf

“CTOTF Tackles the Tough Issues, Including 7FA R0 and Mid-Compressor Fail-ures,” 2007,

Combined Cycle Journal, First Quarter, www.combinedcyclejournal.-

com/webroot/1Q2007/107,%20p%2072-92%20COTF.pdf

Poursaeidi, E., Arablu, M., and Mohammadi Arhani, M. R., 2010, “Root Cause Analysis of Unit

Refinery Powerplant Gas Turbine Compressors 1st Row Rotating Blade Fractures,” South Pars

Gas Company, Iran, Technical Report No. 30557.

“Process Gas Train Results, Final Results for Export Gas,” 2005, Results for UNIT 106SC01,

SPGC R&D Center Archives, Iran, Report No. CF2008009.

FLUENT Inc., 2007, FLUENT 6.3.26 User Manual.

Launder, B. E., and Spalding, D. B., 1972, Lectures in Mathematical Models of Turbulence,

Academic, London.

Jones, W. P., and Whitelaw, J. H., 1985, “Modeling and Measurements in Turbulent

Combustion,” Sym. (Int.) Combust., [Proc.], 20(1), pp. 233–249.