Turbine Vane Endwall Film Cooling With Slashface Leakage and Discrete Hole Configuration

Chowdhury, Nafiz H. K.; Shiau, Chao-Cheng; Han, Je-Chin; Zhang, Luzeng; Moon, Hee-Koo

doi:10.1115/1.4035162

Cited by 37 publications

(3 citation statements)

References 33 publications

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“…Thus, an appropriate cooling scheme is important for protecting the vane endwall efficiently. Chowdhury et al 23 measured the endwall film cooling effectiveness under different discrete hole arrangements. Li et al 24 studied the film cooling distribution with six rows of cylindrical holes placed at different axial locations.…”

Section: Introductionmentioning

confidence: 99%

Turbine vane endwall aerothermal and film cooling performance considering realistic swirling inflow conditions

Zhang

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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The turbine vane inlet downstream of the lean premixed combustor presents nonuniform distributions of velocity and temperature. For obtaining swirling inflow profiles close to reality, the simulated non-reacting combustor is designed firstly. Applying these profiles as inflow boundary conditions, the effects of realistic swirling inflow on the turbine vane endwall aerothermal characteristics and film cooling performance are numerically investigated through solving the three-dimensional Reynolds-Averaged Navier-Stokes equations coupled with the shear stress transfer ([Formula: see text]) turbulence model. Two swirling orientations (anticlockwise and clockwise) and five swirling core pitch-wise positions (aligned with vane 1 to vane 2) are considered in the current work. The results indicate that the residual vortices in the vane passage are strengthened and move with the swirling core along the pitch-wise direction. The migration of the horseshoe vortex is controlled by this movement. The shrinkage or expansion of the separation line of the horseshoe vortex can be observed under the anticlockwise and clockwise swirling inflow conditions respectively. The anticlockwise swirling inflow results in a larger aerodynamic loss by a 10%–35% increase of the laterally [Formula: see text]. The high Nu region near the pressure side surface enlarges and the area-averaged Nu at [Formula: see text] increases from 2337.9 to 2878.3. For the cases with clockwise swirling inflow, the area of the hot ring is enlarged and the Nu downstream of the row 3 film holes is decreased. As for the film cooling performance, the endwall coverage area shrinks and the phantom cooling area enlarges when the anticlockwise swirling core is aligned with vane 2. The endwall loses the protection from the row 3 film holes and the cooling failure ([Formula: see text]) occurs at [Formula: see text] when the swirling core is aligned with the vane passage. This is an extremely bad phenomenon that should be avoided. Among all cases, the highest endwall area-averaged [Formula: see text] (0.122) is obtained when the clockwise swirling core is aligned with vane 1. The largest endwall coverage area is achieved when the clockwise swirling core is aligned with vane 2.

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Section: Introductionmentioning

confidence: 99%

Turbine vane endwall aerothermal and film cooling performance considering realistic swirling inflow conditions

Zhang

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…Basically, the cooling jet from the upstream slot is greatly impacted by crossflow. Chowdhury et al [6] investigated the influence of the mass flow ratio of the coolant to the mainstream utilizing pressure-sensitive coating technology (PSP). The results show that increasing the mass flow ratio can improve endwall cooling performance by preventing the development of the horseshoe vortex.…”

Section: Introductionmentioning

confidence: 99%

Influence of the Slot Fillet and Vane Root Fillet on the Turbine Vane Endwall Cooling Performance

Pei

Shan³

et al. 2023

Machines

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Due to machining techniques and dust deposition, gas turbine upstream slots and vane roots are always filleted, significantly affecting the cooling performance of the endwall. The effects of upstream slot fillet and vane root fillet on the cooling performance of the gas turbine endwall were investigated by solving the three-dimensional Reynolds-averaged Navier–Stokes (RANS) equations with the shear stress transport (SST) k–ω turbulence model. The results indicate that the velocity distribution of the slot coolant is effectively changed by introducing the upstream slot fillets. Among the four cases, the largest adiabatic cooling effectiveness was obtained for the case with two similar fillets, with a 42% increase in effective cooling area compared to the traditional slot. At MFR = 0.75%, the horseshoe vortex is weakened by the introduction of the vane fillet with a small radius, with a 53% increase in effective cooling area compared to the baseline. However, the vane fillet with a large radius makes the boundary layer flow separately prematurely, decreasing the cooling performance. The lateral coverage of the coolant jet from the filmhole embedded in the vane root fillet is greatly enhanced by increasing the vane root fillet radius. However, the streamwise coverage is decreased and the thermodynamic loss is increased.

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“…As shown above, the pressure side hot region endures high level of thermal load and needs advanced cooling schemes to ensure the safe operation [16,17]. Chowdhury et al [22] introduced two rows of film holes near the pressure side. The experimental results showed that the typical uncooled region was reduced.…”

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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Turbine Vane Endwall Film Cooling With Slashface Leakage and Discrete Hole Configuration

Cited by 37 publications

References 33 publications

Turbine vane endwall aerothermal and film cooling performance considering realistic swirling inflow conditions

Turbine vane endwall aerothermal and film cooling performance considering realistic swirling inflow conditions

Influence of the Slot Fillet and Vane Root Fillet on the Turbine Vane Endwall Cooling Performance

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

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