Investigation on film cooling performance from a row of round-to-slot holes on flat plate

Zhang, Jingzhou; Xingdan, Zhu; Huang, Ying; Wang, Chunhua

doi:10.1016/j.ijthermalsci.2017.04.029

Cited by 39 publications

(14 citation statements)

References 34 publications

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“…Gas turbine, as one of the most advanced thermal prime mover, has achieved rapid development in aviation, power generation, shipping, petrochemical and other industries [1]. Because of the continuing demand for improvement of thermal efficiency and power, typical turbine inlet temperature has exceeded the highest allowable material temperature of airfoil [2]. Under such harsh running conditions, the turbine vane has to be protected to guarantee safe running conditions [1][2].…”

Section: Introductionmentioning

confidence: 99%

“…Because of the continuing demand for improvement of thermal efficiency and power, typical turbine inlet temperature has exceeded the highest allowable material temperature of airfoil [2]. Under such harsh running conditions, the turbine vane has to be protected to guarantee safe running conditions [1][2]. Typical advanced cooling techniques include internal cooling, film cooling as well as thermal barrier coatings (TBCs) [3].…”

Section: Introductionmentioning

confidence: 99%

“…In the internal cooling technique, coolant from the last stage of the compressor enters the airfoil from the root, through internal cooling channels and exhaust from the tip to cool down the airfoil [1]. In the film cooling technique, coolant from separate rows of film cooling holes forms a protective layer of film cooling to defense the vane against the onslaught of mainstream [2]. Because of the limited gains of further improvement of the film cooling performance, typically advanced gas turbine airfoil usually incorporates TBCs and film cooling techniques [3][4].…”

Section: Introductionmentioning

confidence: 99%

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The Combined Influences of Hot Streak and Swirl on the Cooling Performances of C3X Guide Vane with or without TBCs

Shi¹,

Huang²,

Lu³

et al. 2021

Preprint

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This paper studied the combined influences of the hot streak and swirl on the cooling performances of the NASA C3X guide vane coated with or without TBCs. The results show that: (1) Even under uniform velocity inlet conditions, the hot streak core can be stretched as it impinges the leading edge which causes higher heat load on the suction side of the forward portion. (2) The swirl significantly affects circumferential and radial migration of the hot streak core in the NGV passage. On the passage inlet plane, positive swirl leads to a hotter tip region on the suction side. In comparison, negative swirl leads to a hotter hub region on the pressure side. (3) Under the influence of swirl, migration of coolant improve the coverage of film cooling close to the midspan, while in the regions close to the hub and tip end-wall, the overall cooling performance decrease simultaneously. (4) In the regions with enough internal cooling, the cooling effectiveness increment is always larger than that in other regions. Besides, the overall cooling effectiveness increment decreases on the region covered by film cooling for the coated vane, especially in the region with negative local heat flux.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

The Combined Influences of Hot Streak and Swirl on the Cooling Performances of C3X Guide Vane with or without TBCs

Shi¹,

Huang²,

Lu³

et al. 2021

Preprint

View full text Add to dashboard Cite

show abstract

“…Nowadays, many researchers focus attention on the film cooling technology, and this has played a major role in cooling the vanes and blades of the turbine front stages which are exposed to a higher firing temperature. Research works of film cooling mainly concentrate on changing the geometries of the film holes (Bunker, 2005; Zhang et al , 2017; Kim and Kim, 2018), placing vortex generators upstream or downstream the holes (Abdala et al , 2016; Chen et al , 2011) as well as combining and arranging the positions of the round holes (Lee et al , 2013; Zhang et al , 2018; Zhu et al , 2018a).…”

Section: Introductionmentioning

confidence: 99%

Comparative analysis on the film cooling mechanisms of elliptical and cylindrical holes with 90° compound angle

Zhang

Xie

Sundén

2020

HFF

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Purpose In this study, numerical simulations are performed to compare the adiabatic film cooling effectiveness and reveal the difference of film cooling mechanisms of two models with the same geometries and cross-section areas of film holes’ exits at three typical blowing ratios (M = 0.5, 1 and 1.5). The two models are an elliptical model and a cylindrical model with 90° compound angle, respectively. Design/methodology/approach Three different cases are considered in this work and the baseline is the model with a cylindrical film hole. The same boundary conditions and a validated turbulence model (realizable k-ε) are adopted for all cases. Findings The results show that both the elliptical and cylindrical models with 90° compound angle can enhance the film cooling effectiveness compared with the baseline. However, the elliptical model performs well at lower blowing ratios and in the near region at each blowing ratio because of the wider width of the film hole’s exit. The cylindrical model with 90° compound angle provides better film cooling effectiveness in the further downstream area of the film hole at higher blowing ratio because of the less lift-off and better coolant coverage in the larger x/D region along the mainstream direction. Originality/value Overall, it can be concluded that although the elliptical and cylindrical models with 90° compound angle have identical hole exits, the different inlet direction and cross-sectional geometry affect the flow structures when the coolant enters, moves through and exits the hole and finally different film cooling results appear.

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“…He concluded that conical shape has higher discharge coefficient as compared to cylindrical holes while the effectiveness distribution is almost the same as fan shaped holes. Recently Zhang et al [29] investigated computationally and experimentally different round to slots configuration with α=35° and different s/d(slot width), he concluded that the diffusion round to slot geometry is more favorable close to the exit hole while the converging slot is better as we go further downstream of the exit hole. He also concluded that discharge coefficient decreases as the slot width is decreased.…”

Section: Introductionmentioning

confidence: 99%

Flat plate film cooling with linear and curved round-to-diffusion shaped slots using PSP measurement technique

Ullah

Shiau

Han

2019

International Journal of Heat and Mass Transfer

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Investigation on film cooling performance from a row of round-to-slot holes on flat plate

Cited by 39 publications

References 34 publications

The Combined Influences of Hot Streak and Swirl on the Cooling Performances of C3X Guide Vane with or without TBCs

The Combined Influences of Hot Streak and Swirl on the Cooling Performances of C3X Guide Vane with or without TBCs

Comparative analysis on the film cooling mechanisms of elliptical and cylindrical holes with 90° compound angle

Flat plate film cooling with linear and curved round-to-diffusion shaped slots using PSP measurement technique

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