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Experimental and numerical investigations of overall cooling effectiveness on a vane endwall with jet impingement and film cooling EI
期刊论文 | 2019 , 1148-1163 | Applied Thermal Engineering
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Abstract :

In this paper, a conjugate heat transfer model for the endwall of a turbine four-vane linear cascade is developed to examine the conjugate cooling effects generated by internal jet impingement and external film cooling as well as heat conduction through the metal endwall. Aerodynamic and geometrical parameters are appropriately scaled to match engine conditions. The conjugate model with a maximum Biot number of 1.5 is tested in engine-like oncoming flows with a turbulence intensity of 9.8% and an integral length scale of 10 mm. The effects of varying passage inlet Reynolds numbers from 1.40 × 105 to 4.20 × 105 and coolant-to-mainstream mass flow ratios from 1.5% to 3.8% are investigated by using experimental measurements and numerical simulations in the presence of an upstream slot. Both experimental and numerical results reveal that overall cooling effectiveness on the endwall increases with the increase of coolant mass flow rate. The effects of passage flow inlet Reynolds number on endwall overall cooling performance are more complicated, that depends on competing effects of internal and external heat transfer. Overall cooling effectiveness is found to be significantly enhanced in the vicinity of the film cooling holes due to higher in-hole convective heat transfer levels. Computational results, which show good agreement with measurements, provide additional information of thermal behavior in the endwall and explain why there is improvement with coolant mass flow ratio. © 2018 Elsevier Ltd

Keyword :

Computational results Conjugate heat transfer Convective heat transfer Discharge coefficients End-wall External heat transfer Numerical investigations Overall cooling effectiveness

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GB/T 7714 Yang, Xing , Liu, Zhansheng , Zhao, Qiang et al. Experimental and numerical investigations of overall cooling effectiveness on a vane endwall with jet impingement and film cooling [J]. | Applied Thermal Engineering , 2019 : 1148-1163 .
MLA Yang, Xing et al. "Experimental and numerical investigations of overall cooling effectiveness on a vane endwall with jet impingement and film cooling" . | Applied Thermal Engineering (2019) : 1148-1163 .
APA Yang, Xing , Liu, Zhansheng , Zhao, Qiang , Liu, Zhao , Feng, Zhenping , Guo, Fushui et al. Experimental and numerical investigations of overall cooling effectiveness on a vane endwall with jet impingement and film cooling . | Applied Thermal Engineering , 2019 , 1148-1163 .
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The role of precessing vortex core in two combustion regimes: Numerical simulation studies SCIE
期刊论文 | 2019 , 33 (1) , 433-446 | JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY
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Abstract :

Large Eddy simulation (LES) with finite rate chemistry was used to investigate the combustion dynamics in a lab-scale PRECCINSTA combustion chamber. Transient three dimensional numerical simulations were carried out at two different thermal powers (10 kW and 35 kW) with a fixed equivalence ratio of 0.7. The predicted results were compared with the experimental data and good agreements were found between them. In the cold flow field under both conditions, a precessing vortex core (PVC) in the inner shear layer (ISL) existing between the swirling jet and the inner recirculation zone (IRZ). However, two different flow and combustion dynamics were observed when combustion occurred. At thermal power of 10 kW, there was a V-shaped flame and the combustion of the flame was stable. The PVC disappeared and the vortices arrangement was symmetrical in the ISL. However, at 35 kW, there was a M-shaped flame with a PVC in the ISL and combustion instability triggered. In depth analysis of the characteristics of flow, temperature and heat release field, we found that the flame surface was wrinkled periodically by the PVC which enhanced the mixing between the cold fresh gas and hot burned products. Then, the mixture was ignited locally and heat release was rapid in the middle of the combustion chamber. These effects were directly related to the periodic vortices motion which was induced by PVC. It was confirmed that the influence of PVC on flame surface and heat release is an important factor for triggering the combustion instability at thermal power of 35 kW. The zone division based on different roles of flow/flame and thermoacoustic coupling was also discussed to illustrate the combustion instabilities caused by PVC.

Keyword :

Precessing vortex core Large eddy simulation Combustion instability

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GB/T 7714 Wang, Zhenlin , Li, Xiangsheng , Feng, Zhenping et al. The role of precessing vortex core in two combustion regimes: Numerical simulation studies [J]. | JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY , 2019 , 33 (1) : 433-446 .
MLA Wang, Zhenlin et al. "The role of precessing vortex core in two combustion regimes: Numerical simulation studies" . | JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY 33 . 1 (2019) : 433-446 .
APA Wang, Zhenlin , Li, Xiangsheng , Feng, Zhenping , Yang, Zhao . The role of precessing vortex core in two combustion regimes: Numerical simulation studies . | JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY , 2019 , 33 (1) , 433-446 .
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Endwall film cooling performance for a first-stage guide vane with upstream combustor walls and inlet injection EI Scopus SCIE
期刊论文 | 2019 , 11 (1) | Journal of Thermal Science and Engineering Applications
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Abstract :

Effects of an upstream combustor wall on turbine nozzle endwall film cooling performance are numerically examined in a linear cascade in this paper. Film cooling is by two rows of cooling holes at 20% of the axial chord length upstream of the vane leading edge (LE) plane. The combustor walls are modeled as flat plates with square trailing edges (TE) positioned upstream of the endwall film cooling holes. A combustor wall is in line with the LE of every second vane. The influence of the combustor wall, when shifted in the axial and tangential directions, is investigated to determine effects on passage endwall cooling for three representative film cooling blowing ratios. The results show how shed vortices from the combustor wall greatly alter the flow field near the cooling holes and inside the vane passage. Film cooling distribution patterns, particularly in the entry region and along the pressure side of the passage, are affected. The combustor wall leads to an imbalance in film cooling distribution over the endwalls for adjacent vane passages. Results show a larger effect of tangential shift of the combustor wall on endwall cooling effectiveness than the effect of an equal axial shift. The study provides guidance regarding design of combustor-to-turbine transition ducts. © 2019 by ASME.

Keyword :

Distribution patterns End-wall Film cooling Film cooling hole Film cooling performance Inlet conditions Tangential directions Transition ducts

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GB/T 7714 Yang, Xing , Liu, Zhao , Liu, Zhansheng et al. Endwall film cooling performance for a first-stage guide vane with upstream combustor walls and inlet injection [J]. | Journal of Thermal Science and Engineering Applications , 2019 , 11 (1) .
MLA Yang, Xing et al. "Endwall film cooling performance for a first-stage guide vane with upstream combustor walls and inlet injection" . | Journal of Thermal Science and Engineering Applications 11 . 1 (2019) .
APA Yang, Xing , Liu, Zhao , Liu, Zhansheng , Simon, Terrence , Feng, Zhenping . Endwall film cooling performance for a first-stage guide vane with upstream combustor walls and inlet injection . | Journal of Thermal Science and Engineering Applications , 2019 , 11 (1) .
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Aerodynamic performance and flow characteristics analysis of Tesla turbines with different nozzle and outlet geometries EI Scopus
期刊论文 | 2018 | Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy
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Abstract :

The aerodynamic performance and flow characteristics of a multichannel nozzled Tesla turbine were investigated numerically with different nozzle and outlet geometries at different rotational speeds. Two kinds of nozzle geometries were proposed: one nozzle channel to one disc channel (named as one-to-one turbine) and one nozzle channel to several disc channels (named as one-to-many turbine). Simplified radial outlet and real axial outlet geometries of the Tesla turbines were adopted to research the influence of outlet geometries. The results show that compared with the one-to-many turbine, the isentropic efficiency of the one-to-one turbine is much higher; while the flow coefficient is much lower. In addition, in the middle disc channels (DC1 and DC2) of which two walls are rotating disc walls, the flow fields are almost the same, but different from that in the side channel (DC3) of which one wall is a rotating wall and the other one is a stationary casing wall. DC1 and DC2 generate more torque with less working fluid, thus the disc spacing distance of DC3 should be narrower than that of DC1 and DC2. Compared to the one-to-many turbine, the working fluid flowing through DC1 and DC2 of the one-to-one turbine is much less, and the flow path lines are much longer. The results of different turbine outlet geometries show that compared with the turbines with radial outlet, the isentropic efficiency of the one-to-many turbine with axial outlet is a little higher, while that of the one-to-one turbine with axial outlet is lower. This is due to the larger torque on the disc hole walls, despite a lot more total pressure loss in the exhaust vent of the one-to-many turbine. Therefore, the contribution of disc hole walls to torque cannot be neglected in numerical simulations. © 2018, IMechE 2018.

Keyword :

Aero-dynamic performance Flow charac-teristics Flow coefficients Isentropic efficiency Nozzle geometries outlet Tesla turbines Total-pressure loss

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GB/T 7714 Qi, Wenjiao , Deng, Qinghua , Jiang, Yu et al. Aerodynamic performance and flow characteristics analysis of Tesla turbines with different nozzle and outlet geometries [J]. | Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy , 2018 .
MLA Qi, Wenjiao et al. "Aerodynamic performance and flow characteristics analysis of Tesla turbines with different nozzle and outlet geometries" . | Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy (2018) .
APA Qi, Wenjiao , Deng, Qinghua , Jiang, Yu , Feng, Zhenping , Yuan, Qi . Aerodynamic performance and flow characteristics analysis of Tesla turbines with different nozzle and outlet geometries . | Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy , 2018 .
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Study on cooling characteristics of an internal cooling structure with a sloping sheet for gas turbine blade EI Scopus
会议论文 | 2018 , 5A-2018 | ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, GT 2018
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Abstract :

This study presents a cooling structure with a sloping sheet to improve the internal cooling of gas turbine blades, inspired by the concept of aircraft wing tip vortex. In this paper, the numerical simulation for the sloping sheet cooling structure has been carried out, which takes into account the heat conduction of the metallic material and the heat transfer of the external high temperature flow field. The results indicate that the structure utilizes the pressure difference between two sides of the sloping sheet to produce a strong vortex pair. The vortexes are led to the inner wall surface of the turbine blade by the downwash. Thanks to such a strong pair vortex, the high temperature air close to the inner wall is quickly blown out and the low temperature coolant is induced to impact on the internal surface, thus achieving an efficient cooling effect. Due to the strong vortex strength and the same vortex vector along the coolant flows, the pair vortex will travel a long distance in the cooling channel, and cool larger areas of the inner wall surface. According to the calculation results, such structure can make the overall temperature of the solid region decreased by 40K as compared to the smooth channel. The sloping sheet cooling structure can reduce the total pressure loss by 63% as compared to the array of pin fins which achieve the same cooling effect. Furthermore, the influence of the sloping sheet’s inclination angle, length and width on the cooling characteristics has also been studied. Through the strength analysis by FEM method, the maximum von Mises stress is 21.9 MPa and it verifies that the sloping sheet can work securely and firmly. Copyright © 2018 ASME.

Keyword :

Calculation results Cooling characteristics Gas turbine blades High temperature air High temperature flow field Inclination angles Pressure differences Total-pressure loss

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GB/T 7714 Feng, Zhenping . Study on cooling characteristics of an internal cooling structure with a sloping sheet for gas turbine blade [C] . 2018 .
MLA Feng, Zhenping . "Study on cooling characteristics of an internal cooling structure with a sloping sheet for gas turbine blade" . (2018) .
APA Feng, Zhenping . Study on cooling characteristics of an internal cooling structure with a sloping sheet for gas turbine blade . (2018) .
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Aero-thermal coupled design optimization of the non-axisymmetric endwall for a gas turbine blade EI Scopus
会议论文 | 2018 , 2D-2018 | ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, GT 2018
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Abstract :

Modern gas turbine endwall is operating in harsher conditions for the application of low NOx combustor. Non-axisymmetric endwall has been extensively studied for aerodynamic performance improvement, because endwall contouring can decrease the pressure gradient between the pressure side (PS) and the suction side (SS) in the blade passage. In addition to the influence of pressure gradient on aerodynamic losses, the vortical structures induced by pressure gradient are also the sources of high heat transfer regions in the passage. Consequently, thermal loads might be reduced by decreasing the pressure gradient thus weakening the strength of the secondary flows. In terms of engineering applications, distribution of thermal load is very important for the design of endwall cooling scheme, and it is necessary to take both aerodynamic and heat transfer performances into consideration for the endwall profile design. In this work, aero-thermal coupled design optimization of a turbine blade endwall was carried out. The endwall contour was obtained by multiplying heights of two curves in the streamwise and pitchwise directions. The streamwise curve was controlled by non-uniform B-spline (NUBS) and the pitchwise one was obtained by employing the sinusoidal function. The optimization method adopted in this research was the multi-objective genetic algorithm (MOGA) coupled with Kriging (KRG) model, which has been validated by benchmark functions. Numerical validation shows that static pressure coefficients on the blade surfaces and the Nusselt number (Nu) on the endwall agree well with the experimental results. The design variables were the endwall profile parameters, and the objective functions were maximizing total pressure recovery coefficient (ξ) at the blade outlet and minimizing the Nu on the endwall. Two optimal cases were selected from the Pareto front and analyzed in detail. It is indicated that the turbine blade aerodynamic performance can be improved while the heat transfer is restrained simultaneously. For the optimal Case I, mass flow-averaged ξ increases by 0.88%, and for Case II, area-averaged Nu reduces by about 7.78%. © Copyright 2018 ASME.

Keyword :

Aero-dynamic performance Aerodynamic and heat transfers Engineering applications Multi-objective genetic algorithm Numerical validations Static pressure coefficient Total pressure recovery coefficient Turbine blade aerodynamics

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GB/T 7714 Feng, Zhenping . Aero-thermal coupled design optimization of the non-axisymmetric endwall for a gas turbine blade [C] . 2018 .
MLA Feng, Zhenping . "Aero-thermal coupled design optimization of the non-axisymmetric endwall for a gas turbine blade" . (2018) .
APA Feng, Zhenping . Aero-thermal coupled design optimization of the non-axisymmetric endwall for a gas turbine blade . (2018) .
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Flow and heat transfer characteristics in models of turbine blade tip-walls with three kinds of turning vanes EI Scopus
会议论文 | 2018 , 5A-2018 | ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, GT 2018
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Abstract :

In this paper, effects of three kinds of turning vanes on flow and heat transfer of turbine blade tip-walls with a U-shaped channel have been numerically studied. Numerical simulations are performed to solve three-dimensional, steady, Reynolds-averaged Navier-Stokes equations with the standard k-ω turbulence model. The aspect ratio (AR) and the hydraulic diameter of the channel are 2 and 93.13 mm, respectively. The effects of single-layer, double-layer and double-layer dome-shaped turning vanes in the turn region on the tip-wall heat transfer and overall pressure loss of rectangular U-shaped channels are analyzed. Detailed flow and heat transfer characteristics over the tip-walls, as well as the overall performance, are presented and compared with each other. Results show that the tip-wall heat transfer coefficients with double-layer dome-shaped turning vanes are the highest among the three cases. Double-layer dome-shaped turning vanes can promote the lateral spreading of secondary flow and effectively increase the uniformity of heat transfer on the tip-wall. More importantly, this structure can make the cooling air expand and accelerate at the center region of the top of the U-shaped channel, resulting in more heat to be removed from the tip-wall. Additionally, double-layer dome-shaped turning vanes can effectively reduce the pressure loss of the channel. Copyright © 2018 ASME.

Keyword :

Flow and heat transfer Hydraulic diameter K-Omega turbulence model Overall pressure loss Reynolds Averaged Navier-Stokes Equations Uniformity of heat Wall heat transfer Wall heat transfer coefficients

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GB/T 7714 Feng, Zhenping . Flow and heat transfer characteristics in models of turbine blade tip-walls with three kinds of turning vanes [C] . 2018 .
MLA Feng, Zhenping . "Flow and heat transfer characteristics in models of turbine blade tip-walls with three kinds of turning vanes" . (2018) .
APA Feng, Zhenping . Flow and heat transfer characteristics in models of turbine blade tip-walls with three kinds of turning vanes . (2018) .
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Prediction of Heat Transfer and Film Cooling on Blade Platform With Stator-Rotor Purge Flow in a 1-1/2 Turbine Stage EI CSCD PKU
期刊论文 | 2018 , 39 (1) , 62-67 | Kung Cheng Je Wu Li Hsueh Pao/Journal of Engineering Thermophysics
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Abstract :

Heat transfer and film cooling on a platform from stator-rotor platform purge flow were numerically investigated in a 1-1/2 turbine stage. The effects of coolant mass flow ratio, coolant-to-mainstream density ratio and rotating speed were examined in detail. The results show that higher mass flow rates and density ratios could enhance heat transfer level in the upstream region and the downstream area of the passage vortex lift-off line on the platform, but slightly affected film cooling distributions, particularly in the downstream area. In addition, increasing rotating speed reduced heat transfer over the platform surface. Higher rotating speeds could suppress the passage vortex, but had little effect on film coolant coverage. © 2018, Science Press. All right reserved.

Keyword :

Downstream areas End-wall Film cooling Mass flow rate Mass flow ratios Rotating Turbine stages Upstream region

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GB/T 7714 Yang, Xing , Wang, Yan , Feng, Zhen-Ping . Prediction of Heat Transfer and Film Cooling on Blade Platform With Stator-Rotor Purge Flow in a 1-1/2 Turbine Stage [J]. | Kung Cheng Je Wu Li Hsueh Pao/Journal of Engineering Thermophysics , 2018 , 39 (1) : 62-67 .
MLA Yang, Xing et al. "Prediction of Heat Transfer and Film Cooling on Blade Platform With Stator-Rotor Purge Flow in a 1-1/2 Turbine Stage" . | Kung Cheng Je Wu Li Hsueh Pao/Journal of Engineering Thermophysics 39 . 1 (2018) : 62-67 .
APA Yang, Xing , Wang, Yan , Feng, Zhen-Ping . Prediction of Heat Transfer and Film Cooling on Blade Platform With Stator-Rotor Purge Flow in a 1-1/2 Turbine Stage . | Kung Cheng Je Wu Li Hsueh Pao/Journal of Engineering Thermophysics , 2018 , 39 (1) , 62-67 .
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全三维轴流式透平叶栅离散伴随气动优化设计 PKU
期刊论文 | 2018 , (4) , 1-6,18 | 燃气涡轮试验与研究
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Abstract :

在前期研究的基础上,将三维轴流式透平叶栅参数化方法发展为基于非均匀有理B样条(NURBS)技术的新型叶栅参数化方法.此方法在对叶栅型线进行NURBS曲线拟合的同时,将叶栅各截面重心及安装角也纳入参数化范围,大大扩展了优化设计空间.基于此,应用离散伴随气动优化设计系统,对Aachen第一级静叶栅在无粘、大负攻角流动条件下,以降低叶栅进出口总压损失为目标进行了全三维气动优化设计.优化后叶栅总压系数提高了1.64%,通道内的流动分离状况得到了有效改善.此外,对优化过程是否添加质量流量约束进行的研究表明,约束条件对优化效果有较大影响,实际应用中应根据需要进行具体的优化设置.

Keyword :

参数化 流量约束 叶栅 气动优化 离散伴随方法 非均匀有理B样条

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GB/T 7714 卢娟 , 丰镇平 . 全三维轴流式透平叶栅离散伴随气动优化设计 [J]. | 燃气涡轮试验与研究 , 2018 , (4) : 1-6,18 .
MLA 卢娟 et al. "全三维轴流式透平叶栅离散伴随气动优化设计" . | 燃气涡轮试验与研究 4 (2018) : 1-6,18 .
APA 卢娟 , 丰镇平 . 全三维轴流式透平叶栅离散伴随气动优化设计 . | 燃气涡轮试验与研究 , 2018 , (4) , 1-6,18 .
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Flow and Heat Transfer Characteristics in Models of Turbine Blade Tip-Walls with Three Kinds of Turning Vanes CPCI-S
会议论文 | 2018 | ASME Turbo Expo: Turbomachinery Technical Conference and Exposition
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Abstract :

In this paper, effects of three kinds of turning vanes on flow and heat transfer of turbine blade tip-walls with a U-shaped channel have been numerically studied. Numerical simulations are performed to solve three-dimensional, steady, Reynolds-averaged Navier-Stokes equations with the standard k-w turbulence model. The aspect ratio (AR) and the hydraulic diameter of the channel are 2 and 93.13 mm, respectively. The effects of single-layer, double-layer and double-layer dome-shaped turning vanes in the turn region on the tip-wall heat transfer and overall pressure loss of rectangular U-shaped channels are analyzed. Detailed flow and heat transfer characteristics over the tip-walls, as well as the overall performance, are presented and compared with each other. Results show that the tip-wall heat transfer coefficients with double-layer dome-shaped turning vanes are the highest among the three cases. Double-layer dome-shaped turning vanes can promote the lateral spreading of secondary flow and effectively increase the uniformity of heat transfer on the tip-wall. More importantly, this structure can make the cooling air expand and accelerate at the center region of the top of the U-shaped channel, resulting in more heat to be removed from the tip-wall. Additionally, double-layer dome-shaped turning vanes can effectively reduce the pressure loss of the channel.

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GB/T 7714 Wu, Bin , Yang, Xing , Ye, Lv et al. Flow and Heat Transfer Characteristics in Models of Turbine Blade Tip-Walls with Three Kinds of Turning Vanes [C] . 2018 .
MLA Wu, Bin et al. "Flow and Heat Transfer Characteristics in Models of Turbine Blade Tip-Walls with Three Kinds of Turning Vanes" . (2018) .
APA Wu, Bin , Yang, Xing , Ye, Lv , Liu, Zhao , Jiang, Yu , Zhao, Qiang et al. Flow and Heat Transfer Characteristics in Models of Turbine Blade Tip-Walls with Three Kinds of Turning Vanes . (2018) .
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