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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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Endwall film cooling performance for a first-stage guide vane with upstream combustor walls and inlet injection EI Scopus
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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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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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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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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Heat transfer analyses of film-cooled HP turbine vane considering effects of swirl and hot streak EI SCIE Scopus
期刊论文 | 2018 , 142 , 815-829 | APPLIED THERMAL ENGINEERING
SCOPUS Cited Count: 1
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Abstract :

Conjugate heat transfer (CHT) analyses were conducted on the film-cooled first stage vane of GE-E-3 engine to reveal the influences of inlet swirl and hot streak (HS) on vane film cooling. Two cases with only HS and four cases considering with combined HS and swirl were studied, including the effects of HS/swirl to vane clocking positions (HS/swirl aligned to passage or vane) and swirl orientations (positive/negative). The results indicate that the variations of incidence angle combined with effects of radial transportation of the swirl vortex worsen the film coolant attachment, decrease the film cooling efficiency and increase the heat load onto vane surface. However, for film holes with radial angles toward the outer endwall, negative incidence near hub endwall is beneficial to the leading edge film coolant attachment. Therefore, a negative swirl aligned to the vane leads to lowering the temperature at the leading edge and the pressure side than the other three cases with combined swirl and HS. Heat transfer coefficient (HTC) on the suction surface (SS) is increased due to upwash and downwash of boundary layer fluids caused by swirl. The temperature on SS is therefore increased because the heat energy transferred from fluid to solid is increased.

Keyword :

Gas turbine Conjugate heat transfer Inlet swirl HP turbine first vane film cooling Hot streak

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GB/T 7714 Wang, Zhiduo , Wang, Dian , Wang, Zhihao et al. Heat transfer analyses of film-cooled HP turbine vane considering effects of swirl and hot streak [J]. | APPLIED THERMAL ENGINEERING , 2018 , 142 : 815-829 .
MLA Wang, Zhiduo et al. "Heat transfer analyses of film-cooled HP turbine vane considering effects of swirl and hot streak" . | APPLIED THERMAL ENGINEERING 142 (2018) : 815-829 .
APA Wang, Zhiduo , Wang, Dian , Wang, Zhihao , Feng, Zhenping . Heat transfer analyses of film-cooled HP turbine vane considering effects of swirl and hot streak . | APPLIED THERMAL ENGINEERING , 2018 , 142 , 815-829 .
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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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INTERACTION BETWEEN PRECESSING VORTEX CORE AND THERMOACOUSTIC COUPLING IN A LAB-SCALE LEAN PREMIXED GAS TURBINE COMBUSTOR: NUMERICAL SIMULATION STUDIES EI CPCI-S
会议论文 | 2017 | ASME Turbo Expo: Turbine Technical Conference and Exposition
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Abstract :

To evaluate the complex dynamic phenomena occurring during combustion, Large Eddy Simulations of the swirl-stabilized flame of PRECCINSTA burner were carried out. The existence of a precessing vortex core in the initial stage of unsteady combustion was proved, both in the cold flow and initial stage of the combustion. The PVC flow structure finally disappeared and became a flapping toroidal flowfield structure with the increase in the amplitude of pressure oscillation when combustion instabilities occurred. The LES results indicate the interactions between the PVC and thermoacoustic coupling and the underlying mechanism of the phenomenon. This study evaluated the effect of PVC on the thermoacoustic coupling in the initial stage of unsteady combustion and elucidated the mechanism for the disappearance of PVC under large-scale pressure oscillation. This has a great significance in the practical industrial applications of controlling combustion instabilities.

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GB/T 7714 Wang, Zhenlin , Li, Xiangsheng , Feng, Zhenping . INTERACTION BETWEEN PRECESSING VORTEX CORE AND THERMOACOUSTIC COUPLING IN A LAB-SCALE LEAN PREMIXED GAS TURBINE COMBUSTOR: NUMERICAL SIMULATION STUDIES [C] . 2017 .
MLA Wang, Zhenlin et al. "INTERACTION BETWEEN PRECESSING VORTEX CORE AND THERMOACOUSTIC COUPLING IN A LAB-SCALE LEAN PREMIXED GAS TURBINE COMBUSTOR: NUMERICAL SIMULATION STUDIES" . (2017) .
APA Wang, Zhenlin , Li, Xiangsheng , Feng, Zhenping . INTERACTION BETWEEN PRECESSING VORTEX CORE AND THERMOACOUSTIC COUPLING IN A LAB-SCALE LEAN PREMIXED GAS TURBINE COMBUSTOR: NUMERICAL SIMULATION STUDIES . (2017) .
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Study on continuous adjoint optimization with turbulence models for aerodynamic performance and heat transfer in turbomachinery cascades EI SCIE Scopus
期刊论文 | 2017 , 104 , 1069-1082 | INTERNATIONAL JOURNAL OF HEAT AND MASS TRANSFER | IF: 3.891
WoS CC Cited Count: 1
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Abstract :

A continuous adjoint method for turbomachinery is presented based on the varied turbulence eddy viscosity (VEV), rather than the constant eddy viscosity (CEV) assumption. Firstly, the grid node coordinates variation and Jacobian Matrices is introduced to deduce the general adjoint system. Then, an objective of entropy generation for aerodynamic and heat transfer is proposed to evaluate the loss of both flow and heat transfer. The VEV adjoint systems with Spalart-Alimaras and SST turbulence models are established for the compressible turbulent flow in turbine cascades with the adiabatic blade wall condition. The aerodynamic optimization cases for turbine cascades show that the VEV adjoint system can achieve higher accuracy, quicker convergence and better optimal result than that of the CEV system in turbomachinery. Furthermore, the improvement of the VEV adjoint method to the mass flow rate constraint is analyzed. Finally, the VEV adjoint system with linearized turbulence model is presented for the isothermal blade wall condition. The optimization results demonstrate the ability of these systems in optimizing the flow and heat transfer performance and reducing the turbine total loss. (C) 2016 Elsevier Ltd. All rights reserved.

Keyword :

Turbomachinery cascades Turbulence model Aerodynamic performance and heat transfer Entropy generation Varied turbulence eddy viscosity Adjoint method

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GB/T 7714 Zhang, Pengfei , Lu, Juan , Song, Liming et al. Study on continuous adjoint optimization with turbulence models for aerodynamic performance and heat transfer in turbomachinery cascades [J]. | INTERNATIONAL JOURNAL OF HEAT AND MASS TRANSFER , 2017 , 104 : 1069-1082 .
MLA Zhang, Pengfei et al. "Study on continuous adjoint optimization with turbulence models for aerodynamic performance and heat transfer in turbomachinery cascades" . | INTERNATIONAL JOURNAL OF HEAT AND MASS TRANSFER 104 (2017) : 1069-1082 .
APA Zhang, Pengfei , Lu, Juan , Song, Liming , Feng, Zhenping . Study on continuous adjoint optimization with turbulence models for aerodynamic performance and heat transfer in turbomachinery cascades . | INTERNATIONAL JOURNAL OF HEAT AND MASS TRANSFER , 2017 , 104 , 1069-1082 .
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Effect of purge flow on endwall flow and heat transfer characteristics of a gas turbine blade EI SCIE Scopus
期刊论文 | 2017 , 110 , 504-520 | APPLIED THERMAL ENGINEERING | IF: 3.771
WoS CC Cited Count: 4
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This paper presents a numerical investigation on the influence of purge flow on endwall flow and heat transfer characteristics of a gas turbine blade. Upon the numerical validation with experiment data, the Reynolds-averaged Navier-Stokes equations coupled with standard k-omega turbulence model are utilized in this study. Five mass flow ratios (MFR) of the purge flow (MFR = 0.5%, 0.75%, 1.0%, 1.25%, 1.5%) and four ejection angles a of the upstream slot (alpha = 30 degrees, 45 degrees, 60 degrees, 90 degrees) are selected to investigate the effects of purge flow on endwall flow structure and their thermal behaviors. The results indicate that the purge flow provides some cooling effectiveness and increases the heat transfer on the endwall. The reduction of the ejection angle cc improves the film cooling effectiveness and increases the heat transfer coefficient of the endwall. The averaged film cooling effectiveness of the endwall is reduced by 53.4% and the heat transfer coefficient at the leading edge is increased by 18.89% when the ejection angle a is increased from 30 degrees to 90 degrees at MFR = 1.5%. Comparing to another case without purge flow, the purge flow increases the aerodynamic losses, and as the increasing of MFR, the aerodynamic losses is increased first and reduced afterwards, obtaining the largest aerodynamic losses at MFR = 1.0% for the ejection angle alpha = 30 degrees. (C) 2016 Elsevier Ltd. All rights reserved.

Keyword :

Numerical simulation Endwall heat transfer Gas turbine blade Film cooling Purge flow Secondary vortexes

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GB/T 7714 Song, Liming , Zhu, Peiyuan , Li, Jun et al. Effect of purge flow on endwall flow and heat transfer characteristics of a gas turbine blade [J]. | APPLIED THERMAL ENGINEERING , 2017 , 110 : 504-520 .
MLA Song, Liming et al. "Effect of purge flow on endwall flow and heat transfer characteristics of a gas turbine blade" . | APPLIED THERMAL ENGINEERING 110 (2017) : 504-520 .
APA Song, Liming , Zhu, Peiyuan , Li, Jun , Feng, Zhenping . Effect of purge flow on endwall flow and heat transfer characteristics of a gas turbine blade . | APPLIED THERMAL ENGINEERING , 2017 , 110 , 504-520 .
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