Multi-objective optimization of laidback fan-shaped film cooling hole on Turbine Vane Suction Surface

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

doi:10.1007/s00231-018-2500-6

Cited by 17 publications

(4 citation statements)

References 35 publications

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“…Despite the widespread use in practical, the challenging subjects in multi-parameter influence and multi-objective optimization of fan-shaped hole film cooling remain unexamined so far. More recently, Huang et al [11] performed a multi-objective optimization of the laidback fan-shaped hole as applied to the turbine guide suction surface by taking the film cooling effectiveness and the discharge coefficient into consideration. Lenzi et al [12] revealed the unsteady flowfield characterization of a shaped-hole effusion system in the swirling mainstream from detailed experimental tests.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Single-Row Double-Jet Film Cooling of a Turbine Guide Vane under High-Temperature and High-Pressure Conditions

et al. 2022

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Single-row double-jet film cooling (DJFC) of a turbine guide vane is numerically investigated in the present study, under a realistic aero-thermal condition. The double-jet units are positioned at specific locations, with 57% axial chord length (Cx) on the suction side or 28% Cx on the pressure side with respect to the leading edge of the guide vane. Three spanwise spacings (Z) in double-jet unit (Z = 0, 0.5d, and 1.0d, here d is the film hole diameter) and four spanwise injection angles (β = 11°, 17°, 23°, and 29°) are considered in the layout design of double jets. The results show that the layout of double jets affects the coupling of adjacent jets and thus subsequently changes the jet-in-crossflow dynamics. Relative to the spanwise injection angle, the spanwise spacing in a double-jet unit is a more important geometric parameter that affects the jet-in-crossflow dynamics in the downstream flowfield. With the increase in the spanwise injection angle and spanwise spacing in the double-jet unit, the film cooling effectiveness is generally improved. On the suction surface, DJFC does not show any benefit on film cooling improvement under smaller blowing ratios. Only under larger blowing ratios does its positive potential for film cooling enhancement start to show. Compared to the suction surface, the positive potential of the DJFC on enhancing film cooling effectiveness behaves more obviously on the pressure surface. In particular, under large blowing ratios, the DJFC plays dual roles in suppressing jet detachment and broadening the coolant jet spread in a spanwise direction. With regard to the DJFC on the suction surface, its main role in film cooling enhancement relies on the improvement of the spanwise film layer coverage on the film-cooled surface.

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Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Single-Row Double-Jet Film Cooling of a Turbine Guide Vane under High-Temperature and High-Pressure Conditions

et al. 2022

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“…Wang et al [23] and Huang et al [24] have employed radial basis function neural network (RBFNN) coupling with the genetic algorithm to optimize the geometry of laidback fan-shaped hole and round-to-slot hole on the flat surface respectively. Furthermore, Huang et al [25] have employed RBFNN coupling with a variant of non-dominated sorting genetic algorithm (NSGA-II) with the film cooling effectiveness and discharge coefficient as the objective function to optimize the geometry of laidback fan-shaped hole on the suction surface of turbine vane. Jiang et al [26] have employed response surface approximation coupled with NSGA-II to perform a multiple objective optimization on the high pressure turbine vane to optimize the geometry of multi-rows film cooling holes with the injection angle and compound angle as the design variables.…”

Section: Introductionmentioning

confidence: 99%

Influence of converging slot-holes (consoles) with different transition surfaces on film cooling performance

Xuan

2022

J. Phys.: Conf. Ser.

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To investigate the influence of the transition surfaces of consoles on film cooling performance, a series of numerical simulations were performed under two typical blowing ratio (M). Four different consoles were designed by changing the transition surface of the console, and their film cooling performance was studied under the same boundary conditions. The purpose of the present work is to determine the best configuration of the transition surface. The results show that whether at M=0.5 or M=1.0, compared with the reference case, the console with anti-s-shaped transition surface has the best spatially-averaged adiabatic film cooling effectiveness (ηad,av ), and the ηad,av is improved by 6.4% and 7.0% respectively, meanwhile, the discharge coefficient (Cd ) is decreased by 2.9% and 3.2% respectively. Besides, the detailed flow and heat transfer mechanism of consoles with different transition surfaces under different blowing ratios are also investigated.

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“…As a result of the influence of the anti-kidney vortices, compared with the conventional film hole, the fan-shaped hole can produce less normal penetration and better span-wise film coverage. As the fan-shaped holes contain many geometric parameters, the influence of multi-parameters about film cooling performance is extremely complicated and still attractive to the researchers so far [10][11][12][13][14].…”

Section: Introductionmentioning

confidence: 99%

“…by Yao et al [32], M=0.91 Present Num., M=0.91 Exp. by Yao et al [32], M=1.55 Present Num., M=1.55 η Mach number distribution (b) Comparison of current simulation and experimental data[13]…”

mentioning

confidence: 99%

Numerical Investigation of Round-to-Slot Holes on Film-Cooling Performance in a Turbine Vane

Huang¹,

Peng²,

Zhang

et al. 2022

J. Phys.: Conf. Ser.

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The numerical investigation of single row holes on suction surface and pressure surface of a scaled turbine guide vane is carried out. In particular, the effects of round-to-slot holes (RTSHs) on film cooling performance are illustrated. Four RTSHs with different exit-to-inlet area ratios are considered under different blowing ratios. The results show that RTSHs can suppress the normal penetration of cooling jet and broadening the lateral coverage of film layer. With the increase of slot aspect ratio, the anti-kidney vortices pair is generally strengthened, making the film cooling improvement more significantly. The film cooling improving effects of shaped holes on the pressure surface is better than that on the suction surface, particularly under high blowing ratios. A key factor affecting the bleed pressure of coolant flow is exit-inlet area ratio of RTSH. The equivalent-area RTSH achieves nearly the same discharge coefficient (Cd) as the cylindrical hole. Viewed from the comprehensive effects of the Cd and adiabatic film cooling effectiveness on shaped hole, the RTSH-3 with a slot aspect of 9 and an exit-inlet area ratio of 1.27 is suggested to be the most favorable film-hole geometry among the current shaped-holes, either on the pressure surface or on the suction surface.

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Multi-objective optimization of laidback fan-shaped film cooling hole on Turbine Vane Suction Surface

Cited by 17 publications

References 35 publications

Numerical Investigation of Single-Row Double-Jet Film Cooling of a Turbine Guide Vane under High-Temperature and High-Pressure Conditions

Numerical Investigation of Single-Row Double-Jet Film Cooling of a Turbine Guide Vane under High-Temperature and High-Pressure Conditions

Influence of converging slot-holes (consoles) with different transition surfaces on film cooling performance

Numerical Investigation of Round-to-Slot Holes on Film-Cooling Performance in a Turbine Vane

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