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< Page ,Total 72 >
Heat transfer enhancement of impingement cooling with corrugated target surface EI
期刊论文 | 2022 , 171 | International Journal of Thermal Sciences
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Abstract :

Impingement cooling is an important turbine blades cooling technique, but it is often not as efficient as required due to the deflection of downstream jets caused by crossflow. In this paper, a novel corrugated target surface is proposed to convert downstream oblique impingement into orthogonal impingement for higher heat transfer. To prove this design, the flow and heat transfer characteristics of impingement cooling with conventional flat target surface (Baseline case), full-corrugated (FC) target surface, and semi-corrugated (SC) target surface are compared over the jet Reynolds number ranging from 15,000 to 45,000. Results show that the Nusselt number of full-corrugated target surface is almost the same as that of flat target surface at the region corresponding to the first five jets, but its peak value and uniformity are significantly improved at the region corresponding to the last four jets, especially under high jet Reynolds numbers. In addition, with the increase of corrugation depth (H), the total heat transfer capacity and area-averaged Nusselt number increase, but this comes at the cost of increased friction loss. Comprehensively evaluating heat transfer and friction loss, only the FC with H = 0.8D case always has better thermal performance than Baseline case under all computed conditions, and the maximum improvement can reach 5.8%. Last but not least, the SC with H = 0.8D case is proposed based on the FC with H = 0.8D case to further reduce the friction loss, and results show that its thermal performance is improved significantly due to the decreased friction loss and almost unchanged heat transfer. © 2021 Elsevier Masson SAS

Keyword :

Cooling Friction Heat transfer coefficients Reynolds number Nusselt number Turbomachine blades

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GB/T 7714 He, Juan , Deng, Qinghua , Feng, Zhenping . Heat transfer enhancement of impingement cooling with corrugated target surface [J]. | International Journal of Thermal Sciences , 2022 , 171 .
MLA He, Juan 等. "Heat transfer enhancement of impingement cooling with corrugated target surface" . | International Journal of Thermal Sciences 171 (2022) .
APA He, Juan , Deng, Qinghua , Feng, Zhenping . Heat transfer enhancement of impingement cooling with corrugated target surface . | International Journal of Thermal Sciences , 2022 , 171 .
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Study on heat transfer characteristics of NGVs influenced by non-reacting lean burn combustor simulator flow EI
期刊论文 | 2022 , 172 | International Journal of Thermal Sciences
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Abstract :

Modern lean burn combustors are developed to meet environmental requirements of low NOx emissions. Comparing with the rich quench lean combustor, lean burn combustor can produce aggressive swirl fields, higher turbulence intensities and different hot streak patterns at the combustor and turbine interface. The flow structures and heat transfer characteristics of high pressure turbine, especially the nozzle guide vanes (NGVs), are significantly affected by the flow patterns from the upstream combustor. In this paper, unsteady integrated calculations are performed for the full geometry contained two NGVs and a non-reacting swirl combustor. The results of three cases of the full geometry, including positive swirler aligned with passage (Case PSW1), positive swirler aligned with leading edge (Case PSW2) and negative swirler aligned with passage (Case NSW), are compared with a baseline case of only NGV simulations with uniform condition (Case UNF). The results indicate that the core of the swirl migrates near the right NGV pressure side in Case PSW1, and near the left NGV suction side in Cases PSW2 and NSW. Higher intensity of the horse shoe vortices and passage vortices is generated in the three non-uniform cases. Hot streak is closer to the hub in Case NSW than Cases PSW1 and PSW2 at NGV exit. Adiabatic wall temperature distributions are influenced by the hot streak and cold fluid migrations. Nusselt number distributions are influenced by the boundary layer accumulation on the NGV surfaces, and by the secondary flow variations on the endwalls. The flow structure and Nusselt number show the similar distribution patterns in Cases PSW1 and PSW2, especially near the endwalls. While, the Nusselt number and the adiabatic wall temperature are obviously changed by the swirl orientation. © 2021 Elsevier Masson SAS

Keyword :

Flow structure Nozzles Nusselt number Combustors Boundary layers Vortex flow

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GB/T 7714 Zhang, Wenhao , Wang, Zhiduo , Wang, Zhihao et al. Study on heat transfer characteristics of NGVs influenced by non-reacting lean burn combustor simulator flow [J]. | International Journal of Thermal Sciences , 2022 , 172 .
MLA Zhang, Wenhao et al. "Study on heat transfer characteristics of NGVs influenced by non-reacting lean burn combustor simulator flow" . | International Journal of Thermal Sciences 172 (2022) .
APA Zhang, Wenhao , Wang, Zhiduo , Wang, Zhihao , Li, Ruocheng , Feng, Zhenping . Study on heat transfer characteristics of NGVs influenced by non-reacting lean burn combustor simulator flow . | International Journal of Thermal Sciences , 2022 , 172 .
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Leakage and Rotordynamic Characteristics for Three Types of Annular Gas Seals Operating in Supercritical CO2Turbomachinery EI SCIE
期刊论文 | 2021 , 143 (10) | Journal of Engineering for Gas Turbines and Power
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Abstract :

The balance piston seal in multiple-stage centrifugal compressors and axial turbines sustains the largest pressure drop through the machines and therefore plays an important role in successful full load operation at high rotational speed. This is especially true for power dense turbomachines in supercritical CO2 power cycles that generate or expend higher fluid pressures (above the critical value 7.3 MPa) and density (close to water 1000 kg/m3), because the fluid forces generated by the balance piston seals are directly proportional to the fluid density and the pressure drop across the seal. This paper presents a comprehensive assessment and comparison on the leakage and rotordynamic performance of three types of annular gas seals for application in a 14 MW supercritical CO2 turbine. These three seals represent the main seal types used in high-speed rotating machines at the balance piston location in efforts to limit internal leakage flow and achieve rotordynamic stability, including a labyrinth seal (LABY), a fully partitioned pocket damper seal (FPDS), and a hole-pattern damper seal (HPS). These three seals were designed to have the same sealing clearance and similar axial lengths. To enhance the seal net damping capability at high inlet preswirl condition, a straight swirl brake was also designed and employed at seal entrance for each type seal to reduce the seal inlet preswirl velocity. Numerical results of leakage flow rates, rotordynamic force coefficients, cavity dynamic pressure, and swirl velocity developments were analyzed and compared for three seal designs at high positive inlet preswirl (in the direction of shaft rotation), using a proposed transient computational fluid dynamic (CFD)-based perturbation method based on the multiple-frequency elliptical-orbit rotor whirling model and the mesh deformation technique. To take into account of real gas effect with high accuracy, a table look-up procedure based on the National Institute of Standards and Technology reference fluid properties database was implemented, using an in-house code, for the fluid properties of CO2 in both supercritical and subcritical conditions. Results show that the inlet swirl brake can significantly reduce the preswirl velocity at seal entrance, lowering the effective damping crossover frequency fco (or even fco = 0) to maximize the full operational frequency range of the machines. In stability analysis phase of a MW-scale supercritical CO2 turbine/compressor, the seal stiffness effects on the rotor mode shape must be evaluated carefully, where the seal stiffness is sufficiently large (comparable to the bearing stiffness). From a rotordynamic viewpoint, the HPS seal with entrance swirl brake is a better seal concept for the balance piston seal in supercritical CO2 turbomachinery, which possesses the largest positive effective damping throughout the entire subsynchronous frequency range. © 2021 by ASME.

Keyword :

Drops Perturbation techniques Carbon dioxide Seals Centrifugal compressors Damping Pressure drop Numerical methods Table lookup Stiffness Brakes Computational fluid dynamics Pistons

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GB/T 7714 Li, Zhigang , Li, Zhuocong , Li, Jun et al. Leakage and Rotordynamic Characteristics for Three Types of Annular Gas Seals Operating in Supercritical CO2Turbomachinery [J]. | Journal of Engineering for Gas Turbines and Power , 2021 , 143 (10) .
MLA Li, Zhigang et al. "Leakage and Rotordynamic Characteristics for Three Types of Annular Gas Seals Operating in Supercritical CO2Turbomachinery" . | Journal of Engineering for Gas Turbines and Power 143 . 10 (2021) .
APA Li, Zhigang , Li, Zhuocong , Li, Jun , Feng, Zhenping . Leakage and Rotordynamic Characteristics for Three Types of Annular Gas Seals Operating in Supercritical CO2Turbomachinery . | Journal of Engineering for Gas Turbines and Power , 2021 , 143 (10) .
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Static and Rotordynamic Characteristics for Two Types of Novel Mixed Liquid Damper Seals With Hole-Pattern/Pocket-Textured Stator and Helically Grooved Rotor EI SCIE
期刊论文 | 2021 , 143 (4) | JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME
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Abstract :

Noncontacting liquid annular seals, such as helical groove seals, are widely used at the impeller interstage and shaft end in the liquid turbomachinery to reduce the fluid leakage and stabilize the rotor-bearing system. However, previous literatures have expounded that the helical groove seal possesses the poor sealing property at low rotational speed condition and suffers the rotor instability problem inducing by negative stiffness and damping, which is undesirable for the liquid turbomachinery. In this paper, to obtain the high sealing performance and the reliable rotordynamic capability throughout full operational conditions of machines, two novel mixed liquid damper seals, which possess a hole pattern/pocket-textured stator matching with a helically grooved rotor, were designed and assessed for the balance piston location in a multiple-stage high-pressure centrifugal liquid pump. To assess the static and rotordynamic characteristics of these two types of mixed liquid damper seals, a three-dimensional (3D) steady computational fluid dynamics (CFD)-based method with the multiple reference frame theory was used to predict the seal leakage and drag power loss. Moreover, a novel 3D transient CFD-based perturbation method, based on the multifrequency one-dimensional stator whirling model, the multiple reference frame theory, and the mesh deformation technique, was proposed for the predictions of liquid seal rotordynamic characteristics. The reliability and accuracy of the present numerical methods were demonstrated based on the published experiment data of leakage and rotordynamic force coefficients of a helical groove liquid annular seal and a hole-pattern liquid annular seal. The leakage and rotordynamic force coefficients of these two mixed liquid damper seals were presented at five rotational speeds (0.5 krpm, 2.0 krpm, 4.0 krpm, 6.0 krptn, and 8.0 kpm) with large pressure drop of 25 MPa, and compared with three types of conventional helical groove seals (helical grooves on rotor, stator or both), two typical damper seals (hole-pattern seal, pocket damper seal with smooth rotor), and a mixed helical groove seal. Numerical results show that two novel mixed liquid damper seals both possess generally better sealing capacity than the conventional helical groove seals, especially at lower rotational speeds. The circumferentially isolated cavities (hole/pocket types) on the stator can enhance the "pumping effect" of the helical grooves for mixed helical groove seals, by weakening the swirl flow in seal clearance (which results in the increase of the fluid velocity gradient near the helically grooved rotor). What is more, the helical grooves on rotor also strengthen the dissipation of fluid kinetic energy in the isolated cavities, so the mixed liquid damper seals offer less leakage. Although the mixed liquid damper seals possess a slightly larger (less than 40%) drag power loss, it is acceptable in consideration of the reduced (similar to 60%) leakage for the high-power turbomachinery, such as the multiple-stage high-pressure centrifugal liquid pump. The present novel mixed liquid damper seals have pronounced rotordynamic stability advantages over the conventional helical groove seals, due to the obviously larger positive stiffness and damping. The mixed liquid damper seal with the hole-pattern stator and the helically grooved rotor (HPSIGR) possesses the lowest leakage and the largest effective damping, especially for higher rotational speeds. From the viewpoint of sealing capacity and rotor stability, the present two novel mixed liquid damper seals have the potential to become the attractive alternative seal designs for the future liquid turbomachinery.

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GB/T 7714 Li, Zhigang , Fang, Zhi , Li, Jun et al. Static and Rotordynamic Characteristics for Two Types of Novel Mixed Liquid Damper Seals With Hole-Pattern/Pocket-Textured Stator and Helically Grooved Rotor [J]. | JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME , 2021 , 143 (4) .
MLA Li, Zhigang et al. "Static and Rotordynamic Characteristics for Two Types of Novel Mixed Liquid Damper Seals With Hole-Pattern/Pocket-Textured Stator and Helically Grooved Rotor" . | JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME 143 . 4 (2021) .
APA Li, Zhigang , Fang, Zhi , Li, Jun , Feng, Zhenping . Static and Rotordynamic Characteristics for Two Types of Novel Mixed Liquid Damper Seals With Hole-Pattern/Pocket-Textured Stator and Helically Grooved Rotor . | JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME , 2021 , 143 (4) .
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Film Cooling Patterns over an Aircraft Engine Turbine Endwall with Slot Leakage and Discrete Hole Injection EI SCIE
期刊论文 | 2021 , 165 | International Journal of Heat and Mass Transfer
WoS CC Cited Count: 2
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Abstract :

Detailed characteristics of film cooling from discrete injection and purge flow, and associated coolant injection patterns are presented over a turbine endwall for wide engine-representative coolant flow rate ranges. Measurements, in combination with numerical simulations, are performed in a linear cascade that is geometrically and aerodynamically scaled up from the hub section of the turbine vane. Reynolds numbers at the vane cascade inlet are varied from 1.40 × 105 to 4.20 × 105, representing the variations of real engine operating conditions (from take-off to cruise conditions). In order to examine the isolated and combined cooling effects, discrete coolant injection and purge flow for the endwall cooling can be injected separately or simultaneously. Numerical simulations are conducted to gain further insight into interactions between endwall-nearby secondary flows and coolant injection. Additionally, a net heat flux reduction parameter is used to evaluate overall film cooling performance of the cooling scheme, that takes heat transfer enhancement by coolant injection into consideration. Results show that endwall-nearby flow structures dictate thermal protection patterns. Increasing coolant flow rates decreases effectiveness values of discrete film cooling but improves cooling effectiveness of purge flow. In spite of no direct interactions between discrete injection and purge flow, adding purge flow could help enhance discrete film cooling effectiveness. Higher passage inlet Reynolds number leads to reduced mixing of coolant injection and mainstream flows, resulting in improved effectiveness values. Changing trends of overall cooling performance for purge flow and discrete film cooling by increasing coolant flow rates are opposite but those are the same by increasing Reynold numbers. © 2020 Elsevier Ltd

Keyword :

Engines Heat flux Aircraft Coolants Aircraft engines Numerical models Reynolds number Aerodynamics Cooling Heat transfer performance

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GB/T 7714 Yang, Xing , Zhao, Qiang , Liu, Zhansheng et al. Film Cooling Patterns over an Aircraft Engine Turbine Endwall with Slot Leakage and Discrete Hole Injection [J]. | International Journal of Heat and Mass Transfer , 2021 , 165 .
MLA Yang, Xing et al. "Film Cooling Patterns over an Aircraft Engine Turbine Endwall with Slot Leakage and Discrete Hole Injection" . | International Journal of Heat and Mass Transfer 165 (2021) .
APA Yang, Xing , Zhao, Qiang , Liu, Zhansheng , Liu, Zhao , Feng, Zhenping . Film Cooling Patterns over an Aircraft Engine Turbine Endwall with Slot Leakage and Discrete Hole Injection . | International Journal of Heat and Mass Transfer , 2021 , 165 .
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Film Cooling Performance Enhancement by Upstream V-shaped Protrusion/Dimple Vortex Generator EI SCIE
期刊论文 | 2021 , 180 | INTERNATIONAL JOURNAL OF HEAT AND MASS TRANSFER
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Film cooling is an effective technique to isolate the heat flux from high-temperature mainstream, but the counter-rotating vortex pair (CRVP) generated by the interaction between film jet and mainstream leads to serious jet-off and poor film coverage. To enhance film cooling performance, a v-shaped protru-sion/dimple vortex generator is arranged at the upstream location of film hole for suppressing the CRVP. The flow and heat transfer characteristics of film cooling with four kinds of vortex generators, v-shaped protrusion vortex generator (VSPVG), v-shaped dimple vortex generator (VSDVG), anti-v-shaped protru-sion vortex generator (AVSPVG) and anti-v-shaped dimple vortex generator (AVSDVG), are investigated in detail over the blowing ratio ranging from 0.5 to 1.5 by solving three dimensional Reynolds-Averaged Navier-Stokes (RANS) equations with Realizable k-epsilon turbulence model. Results indicate that both the v-shaped vortex generators can generate additional anti-counter-rotating vortex pairs (ACRVP) to weaken the CRVP, while both the anti-v-shaped vortex generators will enlarge the CRVP. The arrangement of VSPVG or VSDVG is proved to enhance film cooling performance significantly, especially the VSPVG, which improves the adiabatic film cooling effectiveness by 82.3%, 187.9%, 157.7%, 162.2% and 145.2% re-spectively corresponding to the BR = 0.5, 0.75, 1, 1.25 and 1.5 compared with Baseline case. Considering the total pressure loss, it is found that the enhancement of film cooling effectiveness comes at the cost of slightly increased total pressure loss. In further study, the effect of VSPVG height on film cooling per-formance is also discussed. It is observed that the adiabatic film cooling effectiveness increases with an increase of the height, and the total pressure loss also inescapably increases, but it is worth celebrat-ing that compared with Baseline case, the higher film cooling effectiveness and lower total pressure loss coefficient is obtained when the height is lower than 0.15 D . (c) 2021 Elsevier Ltd. All rights reserved.

Keyword :

Film cooling Vortex generator Total pressure loss Counter-rotating vortex pair

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GB/T 7714 He, Juan , Deng, Qinghua , Feng, Zhenping . Film Cooling Performance Enhancement by Upstream V-shaped Protrusion/Dimple Vortex Generator [J]. | INTERNATIONAL JOURNAL OF HEAT AND MASS TRANSFER , 2021 , 180 .
MLA He, Juan et al. "Film Cooling Performance Enhancement by Upstream V-shaped Protrusion/Dimple Vortex Generator" . | INTERNATIONAL JOURNAL OF HEAT AND MASS TRANSFER 180 (2021) .
APA He, Juan , Deng, Qinghua , Feng, Zhenping . Film Cooling Performance Enhancement by Upstream V-shaped Protrusion/Dimple Vortex Generator . | INTERNATIONAL JOURNAL OF HEAT AND MASS TRANSFER , 2021 , 180 .
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Effects of novel turning vanes on pressure loss and tip-wall heat transfer in an idealized U-bend channel EI SCIE
期刊论文 | 2021 , 121 | International Communications in Heat and Mass Transfer
WoS CC Cited Count: 1
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In this paper, the pressure loss and tip-wall heat transfer are presented in an idealized U-bend channel with novel turning vanes. The cross-sectional area variation, flow separation, mainstream and secondary flow, pressure distribution in different turning vane(s) channels are studied. Moreover, the mechanism of heat transfer enhancement is analyzed by studying the distribution of parameters. Computational fluid dynamics technology is used for solving the steady RANS equations. Results revealed that the double-layer turning vanes channel overcomes the unfavorable factors such as flow separation, recirculation and impingement in the bend region, reducing the pressure loss in the channel by 70%. The double-layer, dome shaped turning vanes channel is a novel cooling structure based on the double-layer turning vanes. The upper wall of the upper layer turning vane is improved into a three dimensional domed structure similar to the hemispherical shell. By main flow and secondary flow acceleration and the special flow pattern caused by the surface of the dome-shaped turning vane, the pressure distribution is more uniform and more coolant flows attached to the tip wall at high velocity. The tip-wall heat transfer performance is improved by 21.77%, and Performance Evaluation Criteria increased by 71.64%. The traditional internal cooling channel guiding devices only play a single role in reducing pressure loss or improving heat transfer. While the double-layer, dome-shaped turning vanes combine can not only improve the heat transfer but also reduce the pressure loss. © 2020 Elsevier Ltd

Keyword :

Flow separation Computational fluid dynamics Domes Heat transfer performance Flow patterns Secondary flow Pressure distribution

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GB/T 7714 Wu, Bin , Yang, Xing , Liu, Zhao et al. Effects of novel turning vanes on pressure loss and tip-wall heat transfer in an idealized U-bend channel [J]. | International Communications in Heat and Mass Transfer , 2021 , 121 .
MLA Wu, Bin et al. "Effects of novel turning vanes on pressure loss and tip-wall heat transfer in an idealized U-bend channel" . | International Communications in Heat and Mass Transfer 121 (2021) .
APA Wu, Bin , Yang, Xing , Liu, Zhao , Feng, Zhenping . Effects of novel turning vanes on pressure loss and tip-wall heat transfer in an idealized U-bend channel . | International Communications in Heat and Mass Transfer , 2021 , 121 .
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Effects of Turning Angle and Turning Internal Radius on Channel Impingement Cooling for a Novel Internal Cooling Structure EI SCIE
期刊论文 | 2021 , 143 (9) | Journal of Turbomachinery
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Leading-edge multi-channel double-wall design, a novel internal cooling structure, has been presented recently to enable higher overall cooling effectiveness with less penalty of coolant and pressure loss. Our previous work has proved the advantages of the design under operating condition relative to conventional internal cooling methods, including impingement cooling and swirl cooling. Channel impingement cooling structure, which is utilized at the turning region of the leading edge, is the critical factor to realize the high cooling performance of the design. Hence, the turning angle and turning internal radius of the cooling channel are two key parameters for the novel design, and this paper focuses on the effects of these two parameters on the flow and heat transfer characteristics of the design. Nine simplified single-channel models with different turning angles (45 deg, 60 deg, and 75 deg) and radii (0.6 mm, 0.9 mm, and 1.2 mm) were adopted to conduct the study, and the jet Reynolds number ranges from 10,000 to 40,000. The results show that the turning angle and turning internal radius affect the jet form significantly for the same mechanism. Small turning angle means large impingement, which leads to stream-wise counter-rotational vortices and high turbulence intensity, but increasing turning internal radius transfers the jet form from impingement jet to laminar layer attaching the target surface with low heat transfer. The turning internal radius has stronger effect than turning angle. With higher jet Reynolds number, both the heat transfer and total pressure loss increase dramatically, and the effects of geometrical parameters are clearer. © 2021 American Society of Civil Engineers (ASCE). All rights reserved.

Keyword :

Geometry Structural design Reynolds number Cooling

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GB/T 7714 He, Wei , Deng, Qinghua , Yang, Guoying et al. Effects of Turning Angle and Turning Internal Radius on Channel Impingement Cooling for a Novel Internal Cooling Structure [J]. | Journal of Turbomachinery , 2021 , 143 (9) .
MLA He, Wei et al. "Effects of Turning Angle and Turning Internal Radius on Channel Impingement Cooling for a Novel Internal Cooling Structure" . | Journal of Turbomachinery 143 . 9 (2021) .
APA He, Wei , Deng, Qinghua , Yang, Guoying , Feng, Zhenping . Effects of Turning Angle and Turning Internal Radius on Channel Impingement Cooling for a Novel Internal Cooling Structure . | Journal of Turbomachinery , 2021 , 143 (9) .
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Effects of Mass Flow Ratio and Film Hole Orientation Angle on Turbine Endwall Film Cooling Characteristics EI
期刊论文 | 2021 , 55 (4) , 107-115 | Journal of Xi'an Jiaotong University
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The film cooling characteristics of the endwall surface of a turbine engine vane are numerically simulated to improve the cooling efficiency of the gas turbine endwall film. Firstly, the endwall film cooling performance with only discrete film holes is studied. Turbulence models are checked by experimental results, and the mesh independence of the models is verified. On this basis, the film cooling characteristics of the discrete film holes at the endwall under five mass flow ratios (1.4%, 2.1%, 2.7%, 3.1%, and 3.8%) and five film hole orientation angles (20°, 25°, 30°, 35°, and 40°) are studied. The heat transfer coefficients of the entire endwall are calculated by using the given experimental endwall heat flux input conditions. Calculation results show that the average adiabatic film cooling efficiency reaches to 0.21 when the mass flow ratio is 1.4% at the same injection angle (40°). A larger mass flow ratio over than 1.4% leads the coolant detach from the endwall surface, and then the film cooling efficiency of the endwall decreases. The total pressure loss of the cascade increases with the increase of the mass flow ratio. The increase of the mass flow ratio strengthens the flow mixing at the outlet of the hole and increases the heat exchange efficiency. Because of the influence of secondary endwall flow and the structure of film holes, the adiabatic film cooling effect is the highest when the film hole injection angle is 20°. Under the same mass flow ratio (1.4%), the average film cooling efficiency of the end wall reaches 0.27. Reducing the injection angle has little effect on the heat exchange efficiency of the endwall surface. © 2021, Editorial Office of Journal of Xi'an Jiaotong University. All right reserved.

Keyword :

Heat flux Cooling Efficiency Mass transfer Heat exchangers Turbulence models

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GB/T 7714 Zhang, Weixin , Liu, Zhansheng , Yang, Xing et al. Effects of Mass Flow Ratio and Film Hole Orientation Angle on Turbine Endwall Film Cooling Characteristics [J]. | Journal of Xi'an Jiaotong University , 2021 , 55 (4) : 107-115 .
MLA Zhang, Weixin et al. "Effects of Mass Flow Ratio and Film Hole Orientation Angle on Turbine Endwall Film Cooling Characteristics" . | Journal of Xi'an Jiaotong University 55 . 4 (2021) : 107-115 .
APA Zhang, Weixin , Liu, Zhansheng , Yang, Xing , Liu, Zhao , Feng, Zhenping . Effects of Mass Flow Ratio and Film Hole Orientation Angle on Turbine Endwall Film Cooling Characteristics . | Journal of Xi'an Jiaotong University , 2021 , 55 (4) , 107-115 .
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Rectification Characteristics of Tab-Type Elbow Flow Conditioner EI
期刊论文 | 2021 , 55 (6) , 92-101 | Journal of Xi'an Jiaotong University
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The rectification characteristics of a tab-type elbow flow conditioner under three incoming flow conditions are investigated by numerical methods, and the flow mechanism, rectification performance, application range and pressure loss characteristics are analyzed. The results show that the elbow tabs form a counter-rotating induced vortex through the influence of pressure difference, and guide the outside fluid to the inside in elbows, thus greatly enhancing the momentum exchange between the fluids, and achieving the effect of disturbing the original velocity distribution and forming a uniform flow. Compared with the smooth tube elbow, the tab-type flow conditioner has little effect on the pressure uniformity, but increases the velocity uniformity by 21%-36%, and the influence on the flow angle uniformity varies with the inlet conditions. The flow resistance of the tab-type flow conditioner is higher than that of the blade-type flow conditioner, lower than that of the orifice-plate flow conditioner, and equivalent to the tube bundle flow conditioner. © 2021, Editorial Office of Journal of Xi'an Jiaotong University. All right reserved.

Keyword :

Numerical methods Pressure effects

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GB/T 7714 Deng, Qinghua , He, Wei , Zhang, Liang et al. Rectification Characteristics of Tab-Type Elbow Flow Conditioner [J]. | Journal of Xi'an Jiaotong University , 2021 , 55 (6) : 92-101 .
MLA Deng, Qinghua et al. "Rectification Characteristics of Tab-Type Elbow Flow Conditioner" . | Journal of Xi'an Jiaotong University 55 . 6 (2021) : 92-101 .
APA Deng, Qinghua , He, Wei , Zhang, Liang , Peng, Aoran , Zhao, Zhuobin , Feng, Zhenping . Rectification Characteristics of Tab-Type Elbow Flow Conditioner . | Journal of Xi'an Jiaotong University , 2021 , 55 (6) , 92-101 .
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