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Analysis of temperature distribution over a gas turbine shaft exposed to a swirl combustor flue

Aghakashi, V ; Sharif University of Technology | 2010

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  1. Type of Document: Article
  2. DOI: 10.1115/IHTC14-22628
  3. Publisher: 2010
  4. Abstract:
  5. Gas turbine shaft is generally exposed to high temperature gases and may seriously be affected and overheated due to temperature fluctuations in the combustion chamber. Considering vortex flow in the combustion chamber, it may increase the heat release rate and combustion efficiency and also control location of energy release. However, this may result in excess temperature on the combustor equipments and gas turbine shaft. Vortex flow in the vortex engine which is created by the geometry of combustion chamber and conditions of flow field is a bidirectional swirl flow that maintains the chamber wall cool. In this study a new gas turbine combustion chamber implementing a liner around the shaft and liquid fuel feeding system is designed and fabricated. Influence of parameters such as axial position in the combustor direction and equivalence ratio are studied. Experimental results are compared with the numerical simulation by the existing commercial software. Swirl number i.e. ratio of angular flux of angular momentum to angular flux of linear momentum multiplied by nozzle radius, in this study is assumed to be constant. In order to measure the temperature along the liner, K type thermocouples are used. Results show that the heat transfer to the liner at the inlet of combustion chamber is enough high and at the outlet of combustion chamber is relatively low. The effect of parameters such as equivalence ratio and the mass flow rate of oxidizer on the temperature of the liner is investigated and compared with the numerical solution. This type of combustion chambers can be used in gas turbine engines due to their low weight and short length of combustion chamber
  6. Keywords:
  7. Angular flux ; Axial positions ; Chamber walls ; Combustion efficiencies ; Commercial software ; Effect of parameters ; Energy release ; Equivalence ratios ; Fuel feeding system ; Gas-turbine combustion ; Heat Release Rate (HRR) ; High temperature ; K-type thermocouples ; Linear momenta ; Low weight ; Mass flow rate ; Nozzle radius ; Numerical solution ; Swirl combustor ; Swirl flow ; Swirl numbers ; Temperature fluctuation ; Combustors ; Gas turbines ; Heat transfer ; Temperature distribution ; Thermocouples ; Vortex flow ; Combustion chambers
  8. Source: 2010 14th International Heat Transfer Conference, IHTC 14 ; Volume 5 , 2010 , Pages 183-190 ; 9780791849408 (ISBN)
  9. URL: http://proceedings.asmedigitalcollection.asme.org/proceeding.aspx?articleid=1620449