Effects of the leading edge injection slot on the film cooling and heat transfer performance of the vane endwall

Du, Kun; Li, Zhigang; Li, Jun

doi:10.1016/j.ijheatmasstransfer.2016.07.033

Cited by 17 publications

(4 citation statements)

References 24 publications

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“…By comparison between engine and wind tunnel conditions, a suitable size of the wax particle is selected. When the particle is made of wax and the other parameters are given, the diameter of the wax particle can be calculated as follows: (5) For accurate simulations based on the turbine leading edge, the Biot number in laboratory conditions is needed to match actual engine conditions. When the dimensionless thickness (b wall /d) in the laboratory conditions is the same as the actual engine conditions, the Biot numbers can be kept consistent as long as the thermal conductivity ratios satisfy the following formula by Albert and Bogard [43]:…”

Section: Matching Of Actual Engine and Simulated Conditionsmentioning

confidence: 99%

A review of multiphase flow and deposition effects in film-cooled gas turbines

2018

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This paper presents a review of particle deposition research in film-cooled gas turbines based on the recent open literature. Factors affecting deposition capture efficiency and film cooling effectiveness are analyzed. Experimental studies are summarized into two discussions in actual and virtual deposition environments. For investigation in virtual deposition environments, available and reasonable results are obtained by comparison of the Stokes numbers. Recent advances in particle deposition modeling for computational fluid dynamics are also reviewed. Various turbulence models for numerical simulations are investigated, and solutions for treatment of the particle sticking probability are described. In addition, analysis of injecting mist into the coolant flow is conducted to investigate gas-liquid two-phase flow in gas turbines. The conclusion remains that considerable research is yet necessary to fully understand the roles of both deposition and multiphase flow in gas turbines.

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Section: Matching Of Actual Engine and Simulated Conditionsmentioning

confidence: 99%

A review of multiphase flow and deposition effects in film-cooled gas turbines

2018

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“…In contrast, when the endwall film-cooling of the leading-edge cylindrical holes in Refs. [12,13] is aided by the leading-edge or upstream slot film-cooling flow to enhance the cooling effectiveness, the leading-edge horseshoe vortex and passage vortex are reduced significantly. The trenched cylindrical holes in the upstream endwall employed by Sundaram and Thole [14] also improve the film-cooling coverage by keeping the coolant stream adjacent to the endwall.…”

Section: Introductionmentioning

confidence: 99%

Upstream Endwall Film-Cooing in a Vane Cascade with Cylindrical Shape Holes

Huyssen

Shote

Mahmood

2023

Journal of Thermophysics and Heat Transfer

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To overcome the disadvantages of cylindrical holes in film cooling, complex geometries of the fan-shaped diffused holes are employed in cascade investigations. The present experiment employs a new design of a diffused hole for film cooling that is formed by diffusing a cylindrical hole smoothly and only in the forward direction. The aerothermal performances in a linear vane cascade are compared between an array of simple cylindrical holes and an array of diffused-cylindrical holes by employing them in the cascade upstream endwall. The objectives are to increase the aerothermal performance of the cylindrical holes in the gas-turbine passage film cooling. The measurements of the temperature, velocity, flow angle, and total-pressure losses are obtained at the inlet Reynolds number of [Formula: see text], as well as the coolant-to-mainstream density ratio of 1.0 and temperature ratios between 0.94 and 1.0. Four inlet blowing ratios of film-cooling flow are tested. The results show less coolant migration into the boundary layer and passage vortex for the diffused holes than for the cylindrical holes. The passage vortex becomes weaker, and the overall total-pressure losses at the passage exit are lower for the diffused holes. The local and average adiabatic film-cooling effectivenesses along the endwall are always higher for the diffused holes.

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“…More importantly, the hot regions near the leading edge and along the pressure side still exist in all above studies, and the presence of the hot regions is a serious threat to the gas turbine operation. To completely remove the hot region around the leading edge, Du et al [21] proposed a leading edge injection slot, introducing the coolant jet from the root of the vane. The results indicated that the hot region near the leading edge was totally removed due to the effective cooling by the coolant jet from the leading edge injection slot.…”

Section: Introductionmentioning

confidence: 99%

“…Although many studies have been conducted to enhance the endwall cooling effectiveness, the region along the vane pressure side still obtains a relatively low level of cooling effectiveness due to the presence of the lateral flow in the vane passage [15,21]. Therefore, the primary issue of interest in this study concerns the effects of the pressure side injection slot on increasing the pressure side endwall cooling effectiveness.…”

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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Effects of the leading edge injection slot on the film cooling and heat transfer performance of the vane endwall

Cited by 17 publications

References 24 publications

A review of multiphase flow and deposition effects in film-cooled gas turbines

A review of multiphase flow and deposition effects in film-cooled gas turbines

Upstream Endwall Film-Cooing in a Vane Cascade with Cylindrical Shape Holes

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

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