Measurements and modeling of the flow and heat transfer in a contoured vane-endwall passage

Pasinato, Hugo D.; Squires, Kyle D.; Roy, R. P.

doi:10.1016/j.ijheatmasstransfer.2004.07.032

Cited by 23 publications

(3 citation statements)

References 25 publications

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“…Granser and Schulenberg [18], Colban et al [15], and Zhang and Moon [19] all reported similar adiabatic effectiveness results in that higher values occurred near the suction side of the vane relative to the pressure side. Based on their measurements, Roy et al [20], however, indicated that the coolant migrated toward the pressure side of the vane. Their measurements indicated reduced values of local heat transfer coefficients at the leading edge when slot cooling was present relative to no slot cooling.…”

Section: Endwall Cooling Studiesmentioning

confidence: 99%

Heat transfer and film-cooling for the endwall of a first stage turbine vane

Thole

Knost

2005

International Journal of Heat and Mass Transfer

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Section: Endwall Cooling Studiesmentioning

confidence: 99%

Heat transfer and film-cooling for the endwall of a first stage turbine vane

Thole

Knost

2005

International Journal of Heat and Mass Transfer

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“…Early research carried out by Pasinato et al [1] indicated that it was feasible for a numerical calculation to simulate the flow in turbine cascades with the correct turbulence model and numerical setup. Lynch and Thole [2] studied the leakage from a combustor-turbine gap and presented a pattern of cooling effectiveness (η).…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of Endwall Modification with Micro-Scale Ribs in a Turbine Cascade

Liu,

Song,

et al. 2023

Applied Sciences

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A novel modification method, the ‘micro-scale’ rib, is proposed to expand cooling coverage for turbine endwalls. However, the introduction of the rib will inevitably affect the flow in the near-wall region. Therefore, the variation in the flow pattern for the traditional model of secondary flow needs further exploration. In this paper, to gain a clearer understanding of the micro-scale rib, the original endwall and three types of ribbed endwalls were adopted to numerically present the detailed flow, film cooling, and heat transfer information for the endwall surface and phantom cooling on the suction side (SS) of the blade. The Ansys code CFX was utilized to solve the 3D Reynolds-averaged Navier–Stokes (RANS) equations, and the SST k-ω was selected as the turbulence model after the verification. The results show that the rib-like vortex changed the flow of the coolant and had various impacts on the cooling characteristics. Although the cooling performance of the ribbed endwall improved, it also had a negative impact on heat transfer in most cases. Compared with the original, the vertical rib cases provided optimal film cooling, with increases of 26.9% and 17.4% for rib spacing values of 8 mm and 10 mm, respectively, with little difference in heat transfer (less than 1%). In addition, the horizontal rib cases presented the worse performance for both film cooling and heat transfer, which indicates that the rib layout should consider a mainstream flow direction for future designs.

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“…He also concluded that the downstream cooling effectiveness was enhanced with increasing coolant mass flow rate. Pasinato et al [13] indicated that the lateral pressure difference drives the coolant flow from the upstream slot toward the suction side and the heat transfer near the leading edge was decreased in comparison with the case without upstream slot coolant.…”

Section: Introductionmentioning

confidence: 99%

Influence of the pressure side injection slot on the cooling performance of endwall surface

et al. 2018

Numerical Heat Transfer, Part A: Applications

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In modern gas turbine engines, the first stage vane endwall endures high thermal load with the increase of the turbine inlet temperature and the uniformity of the temperature distribution at combustor outlet. Moreover, the endwall secondary flow forces the coolant flow toward the suction side, resulting in hot regions along the pressure side endwall. In the worst case, hot regions lead to thermal failure. In order to ensure that the gas turbine operates safely, advanced cooling techniques are urgently needed to be implemented to reduce the hot regions along the pressure side endwall. In the current research, the influences of the pressure side injection slot on the film cooling performance of the endwall surface were numerically investigated. The three-dimensional Reynolds-averaged Navier-Stokes (RANS) equations combined with the shear stress transport (SST) k À x turbulence model were solved to conduct the simulations. Cases with different injection slot configurations have been simulated. The results indicate that the hot region along the pressure side endwall is significantly reduced by introducing the pressure side injection slot. The coolant from the pressure side injection slot is assisted by the pressure side vertical flow toward the adjacent vane suction side. Therefore, the coolant coverage and the cooling effectiveness are increased. In this study, the expanded slot (ES) achieves a larger cooling effectiveness than the normal slot (NS) and convergent slot (CS) at a small blowing ratio M ¼ 0.5. In contrast, the CS obtains a larger cooling effectiveness than the NS and ES at M ¼ 1.0 and M ¼ 1.5. In addition, the introduction of the pressure side injection slot has a small influence on the aerodynamic performance of the vane cascade. ARTICLE HISTORY

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Measurements and modeling of the flow and heat transfer in a contoured vane-endwall passage

Cited by 23 publications

References 25 publications

Heat transfer and film-cooling for the endwall of a first stage turbine vane

Heat transfer and film-cooling for the endwall of a first stage turbine vane

Numerical Study of Endwall Modification with Micro-Scale Ribs in a Turbine Cascade

Influence of the pressure side injection slot on the cooling performance of endwall surface

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