Three-Dimensional Flow Near the Blade/Endwall Junction of a Gas Turbine: Application of a Boundary Layer Fence

Chung, Jin Taek; Simon, Terrence W.; Buddhavarapu, J.

doi:10.1115/91-gt-045

Cited by 42 publications

(28 citation statements)

References 12 publications

(13 reference statements)

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“…The turbulence model was applied because of its effectiveness in simulating for separated, swirling, and secondary flows [3]. Previous studies have also revealed that the turbulence model produced reasonable predictions (Zess and Thole [16]).…”

Section: Computational Fluid Dynamics Simulationsmentioning

confidence: 98%

“…The research reported that the fences diminished the secondary loss by 22 percent, and the gross loss, including kinetic energy dissipation, by 25 percent. Chung et al [3] used a triangular-shaped endwall boundary layer fence in a cascade to improve the likelihood of efficient film cooling on the suction surface near the endwall. They used a laser doppler velocimetry for flow visualization at Re c =2.93x10 5 .…”

Section: Introductionmentioning

confidence: 99%

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Controlling the secondary flows near endwall boundary layer fences in a 90° turning duct using approximate optimization method

Cho

Kim

Kim³

et al. 2011

J Mech Sci Technol

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This paper presents the optimization of an endwall boundary layer fence which improves the aerothermal characteristics of a gas turbine passage. The fence in a gas turbine passage effectively reduces secondary flow loss, which is generated in the cascade of the turbine. The turbine passage was simulated by a 90º turning duct (Re D =360,000). The main purpose of the present investigation was to focus on finding a boundary layer fence with minimum total pressure loss in the passage and heat transfer coefficient on the endwall of the duct. An approximate optimization method was used for the investigation to secure the computational efficiency. Design variables were the fence shape factors (fence thickness, fence height, and fence width) as well as the radial position on the passage endwall. Results indicated that a significant improvement in aerodynamic performance can be achieved through the application of an optimized boundary layer fence. The optimized design reduced the mass-weighted average total pressure loss in the duct by 8.6% relative to the duct without the fence. The area-weighted average maximum Nusselt number on the endwall of the optimized design was decreased by 2.5% in comparison with the duct without the fence.

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Section: Computational Fluid Dynamics Simulationsmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

Controlling the secondary flows near endwall boundary layer fences in a 90° turning duct using approximate optimization method

Cho

Kim

Kim³

et al. 2011

J Mech Sci Technol

View full text Add to dashboard Cite

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“…Contours shown in Fig.2 remain almost the same for both of the Reynolds number used in this experiment. Additional information regarding the flow field in the passage are available in Chung and Simon (1990), Chen and Goldstein (1992), and Jabbari et al (1992).…”

Section: Figure Lb-sampling Tap and Injection Hole Row Designation Tementioning

confidence: 99%

Film Cooling of the Gas Turbine Endwall by Discrete-Hole Injection

Jabbari

Marston

Eckert

et al. 1994

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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Film cooling performance for injection through discrete holes in the endwall of a turbine blade is investigated. The effectiveness is measured at sixty locations in the region covered by injection. Three nominal blowing rates, two density ratios, and two approaching flow Reynolds numbers are examined. Analysis of the data reveals that even sixty locations are insufficient for the determination of the field of film cooling effectiveness with its strong local variations. Visualization of the traces of the coolant jets on the endwall surface, using ammonium-diazo-paper, provides useful qualitative information for the interpretation of the measurements, revealing the paths and interaction of the jets which change with blowing rate and density ratio.distance from downstream edge of injection hole along a row (Fig. lb) Presented at the International Gas Turbine and Aeroengine Congress and Exposition

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“…Chung et al [22] used one streamwise fence to block and change the migration of the pressure side leg of the horseshoe vortex. Comparisons of the flow patterns obtained by flow visualization and LDV measurements showed that the fence is effective in reducing the highly skewed flow motion on the near end-wall suction side surface due to the passage vortex.…”

Section: A End-wall Secondary Flow and Loss Reductionmentioning

confidence: 99%