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Single-Hole Film Cooling on a Turbine-Blade Leading-Edge Model

MISHRA, SUMAN
http://rave.ohiolink.edu/etdc/view?acc_num=ucin1205156648

Abstract Details

2008, MS, University of Cincinnati, Engineering : Mechanical Engineering.
The present study numerically investigates the effectiveness of film cooling on a turbine blade leading-edge model through a single-hole coolant exit. The model used in this study has the same dimensions as that of an earlier experimental investigation by Ekkad et al., 2006. The cylindrical model, a half cylinder with a flat after-body attached to it, provides a good representation of the leading edge of a turbine blade. The coolant hole is situated approximately at the center of the cylindrical model along the spanwise direction and makes an angle of 21.5 degrees to the true leading edge and 20 degrees to the spanwise direction. A multi-block grid is generated using GridGen, and the flow is simulated using the flow solver FLUENT. Blowing ratio, M, is defined as the mass flux ratio of the coolant and the mainstream. Simulations are carried out for different blowing ratios M, ranging from 0.25 to 1.0, with the k-ε realizable turbulence model and the k-ω SST model. The flow is assumed to have a free-stream turbulence intensity of 0.75%. Additionally, the enhanced wall function approach is used as the near-wall treatment in the computational model for the simulation with k-ε realizable turbulence model. Results obtained indicate an increased film-effectiveness for low blowing ratio in the far downstream region. Also, in the vicinity of the coolant jet exit, it is observed that increase in blowing ratio increases the film cooling effectiveness. It is also concluded that steady RANS-based turbulence models under-predict the interaction between the jet and the mainstream at the jet exit, and the spreading of coolant downstream.
Dr. Urmila Ghia (Advisor)
78 p.
Engineering, Mechanical
Film cooling blowing ratio turbine blade leading edge cylindrical model

Recommended Citations

Citations

  • MISHRA, S. (2008). Single-Hole Film Cooling on a Turbine-Blade Leading-Edge Model [Master's thesis, University of Cincinnati]. OhioLINK Electronic Theses and Dissertations Center. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1205156648

    APA Style (7th edition)

  • MISHRA, SUMAN. Single-Hole Film Cooling on a Turbine-Blade Leading-Edge Model. 2008. University of Cincinnati, Master's thesis. OhioLINK Electronic Theses and Dissertations Center, http://rave.ohiolink.edu/etdc/view?acc_num=ucin1205156648.

    MLA Style (8th edition)

  • MISHRA, SUMAN. "Single-Hole Film Cooling on a Turbine-Blade Leading-Edge Model." Master's thesis, University of Cincinnati, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1205156648

    Chicago Manual of Style (17th edition)

ucin1205156648
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© 2008, all rights reserved.
This open access ETD is published by University of Cincinnati and OhioLINK.