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< Page ,Total 65 >
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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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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Film cooling and aerodynamic performances of a turbine nozzle guide vane with trenched cooling holes SCIE
期刊论文 | 2019 , 150 , 150-163 | APPLIED THERMAL ENGINEERING
WoS CC Cited Count: 1
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Abstract :

The numerical investigation on shaped trench film cooling was carried out using Reynolds averaged Navier-Stokes simulation to test its practical utility. The cooling performance of three kinds of film holes (standard cylindrical film holes, transverse trenched and segmented trenched film holes) on a flat plate was studied firstly to verify the numerical method and illustrate the vortex structures in detail. Then the cooling characteristics of the three kinds of film holes, which are located at five single row positions around a turbine vane, were compared in operating conditions. The parameters of adiabatic film cooling effectiveness, discharge coefficient and total pressure losses are analyzed with the blowing ratios from 0.5 to 3.0, and the optimal position on turbine vanes for the novel trenched film hole was confirmed. The results show that the trenched cooling holes produces more uniform coolant distribution laterally at all positions, leading to higher cooling performance particularly at high blowing ratios. The unique vortex configuration generated by segmented trench shows clear advantages at the small curvature positions on the pressure side, where the mainstream influence is minimum and is more suitable for the novel structure. The flow resistances in trenched film holes are less than that in cylindrical holes. The magnitude of the total pressure losses of the three cooling holes are almost the same.

Keyword :

Total pressure loss Turbine vane Adiabatic film cooling effectiveness Discharge coefficient Trenched cooling holes

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GB/T 7714 He, Wei , Deng, Qinghua , Zhou, Weilun et al. Film cooling and aerodynamic performances of a turbine nozzle guide vane with trenched cooling holes [J]. | APPLIED THERMAL ENGINEERING , 2019 , 150 : 150-163 .
MLA He, Wei et al. "Film cooling and aerodynamic performances of a turbine nozzle guide vane with trenched cooling holes" . | APPLIED THERMAL ENGINEERING 150 (2019) : 150-163 .
APA He, Wei , Deng, Qinghua , Zhou, Weilun , Gao, Tieyu , Feng, Zhenping . Film cooling and aerodynamic performances of a turbine nozzle guide vane with trenched cooling holes . | APPLIED THERMAL ENGINEERING , 2019 , 150 , 150-163 .
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Influence of Disc Tip Geometry on the Aerodynamic Performance and Flow Characteristics of Multichannel Tesla Turbines SCIE
期刊论文 | 2019 , 12 (3) | ENERGIES
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Abstract :

As a competitive small-scale turbomachinery option, Tesla turbines have wide potential in various fields, such as renewable energy generation systems and small power equipment. This paper investigates the influence of disc tip geometry, including its profile and relative height, on the aerodynamic performance and flow characteristics of one-to-one and one-to-many multichannel Tesla turbines. The results indicate that compared to the turbine with blunt tips, the isentropic efficiency of the one-to-one turbine with sharp tips has a little decrease, which is because the relative tangential velocity gradient near the rotational disc walls decreases a little and additional vortices are generated at the rotor inlet, while that of the one-to-many turbine with sharp tips increases significantly, resulting from an increase in the relative tangential velocity in the disc channels and a decrease in the low Mach number and vortex area; for instance the turbine efficiency for the former relatively decreases by 3.6% and that for the latter increases by 13.5% at 30,000 r/min. In addition, the isentropic efficiency of the one-to-many turbine with sharp tips goes up with increasing relative height due to increasing improvement of flow status, and its increment rate slows down. A circular or elliptic tip performs better with lower relative height and a triangular tip behaves better with higher relative height. To sum up, a blunt disc tip is recommended for the one-to-one turbine, and a sharp disc tip is for the one-to-many turbine. The relative height and tip profile of the one-to-many turbine should be determined according to their effects on turbine performance, manufacturing difficulty and mechanical deformation.

Keyword :

isentropic efficiency Tesla turbine fluid dynamics disc tip

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GB/T 7714 Qi, Wenjiao , Deng, Qinghua , Chi, Zhinan et al. Influence of Disc Tip Geometry on the Aerodynamic Performance and Flow Characteristics of Multichannel Tesla Turbines [J]. | ENERGIES , 2019 , 12 (3) .
MLA Qi, Wenjiao et al. "Influence of Disc Tip Geometry on the Aerodynamic Performance and Flow Characteristics of Multichannel Tesla Turbines" . | ENERGIES 12 . 3 (2019) .
APA Qi, Wenjiao , Deng, Qinghua , Chi, Zhinan , Hu, Lehao , Yuan, Qi , Feng, Zhenping . Influence of Disc Tip Geometry on the Aerodynamic Performance and Flow Characteristics of Multichannel Tesla Turbines . | ENERGIES , 2019 , 12 (3) .
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Experimental and numerical investigations of overall cooling effectiveness on a vane endwall with jet impingement and film cooling EI SCIE
期刊论文 | 2019 , 148 , 1148-1163 | Applied Thermal Engineering
WoS CC Cited Count: 1
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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 , 148 : 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 148 (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 , 148 , 1148-1163 .
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Disc Thickness and Spacing Distance Impacts on Flow Characteristics of Multichannel Tesla Turbines SCIE
期刊论文 | 2019 , 12 (1) | ENERGIES
WoS CC Cited Count: 1
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Abstract :

Tesla turbines are a kind of unconventional bladeless turbines, which utilize the viscosity of working fluid to rotate the rotor and realize energy conversion. They offer an attractive substitution for small and micro conventional bladed turbines due to two major advantages. In this study, the effects of two influential geometrical parameters, disc thickness and disc spacing distance, on the aerodynamic performance and flow characteristics for two kinds of multichannel Tesla turbines (one-to-one turbine and one-to-many turbine) were investigated and analyzed numerically. The results show that, with increasing disc thickness, the isentropic efficiency of the one-to-one turbine decreases a little and that of the one-to-many turbine reduces significantly. For example, for turbine cases with 0.5 mm disc spacing distance, the former drops less than 7% and the latter decreases by about 45% of their original values as disc thickness increases from 1 mm to 2 mm. With increasing disc spacing distance, the isentropic efficiency of both kinds of turbines increases first and then decreases, and an optimal value and a high efficiency range exist to make the isentropic efficiency reach its maximum and maintain at a high level, respectively. The optimal disc spacing distance for the one-to-one turbine is less than that for the one-to-many turbine (0.5 mm and 1 mm, respectively, for turbine cases with disc thickness of 1 mm). To sum up, for designing a multichannel Tesla turbine, the disc spacing distance should be among its high efficiency range, and the determination of disc thickness should be balanced between its impacts on the aerodynamic performance and mechanical stress.

Keyword :

disc spacing distance Tesla turbine isentropic efficiency disc thickness fluid dynamics

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GB/T 7714 Qi, Wenjiao , Deng, Qinghua , Jiang, Yu et al. Disc Thickness and Spacing Distance Impacts on Flow Characteristics of Multichannel Tesla Turbines [J]. | ENERGIES , 2019 , 12 (1) .
MLA Qi, Wenjiao et al. "Disc Thickness and Spacing Distance Impacts on Flow Characteristics of Multichannel Tesla Turbines" . | ENERGIES 12 . 1 (2019) .
APA Qi, Wenjiao , Deng, Qinghua , Jiang, Yu , Yuan, Qi , Feng, Zhenping . Disc Thickness and Spacing Distance Impacts on Flow Characteristics of Multichannel Tesla Turbines . | ENERGIES , 2019 , 12 (1) .
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Effects of location, shape and width of a suction slot on the water removal performance of a hollow stator blade EI CPCI-S SCIE Scopus
会议论文 | 2018 , 232 (5) , 461-472 | Wet Steam Conference
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Abstract :

Experimental tests were implemented on a wet steam test rig to investigate the effects of location, shape and width of a suction slot on the water removal performance of a hollow stator blade. A straight cascade with varying outlet Mach numbers and suction pressure differences was used for the tests. The inlet flow conditions were consistent with the real running condition before the last stage stator of a 1000-MW nuclear steam turbine. Results show that the flow Mach number and suction pressure difference affect the amount of water removed. A moderate increase in the suction pressure difference triggers water film vaporisation, which decreases water removal performance. The amount of water removed continuously increases, as the slot location moves from 0.24 to 0.42 times the axial chord in the suction surface. Compared with the straight slot, the step-shaped slot cannot improve the water removal performance. On the contrary, the result is poor when the Mach number is above 0.7 because additional sharp corner leads to more serious water vaporisation. A suction slot with an arc-shaped inlet significantly improves the water removal performance by eliminating water film vaporisation under the test conditions. A 0.35-mm-width suction slot is apt to allow water film across, and a 2-mm-width suction slot cannot form an effective suction pressure difference along the slot height, both leading to poor water removal performance. Meanwhile, 0.7- and 1-mm-width suction slots promote good water removal performance, but the latter is less affected by water vaporisation.

Keyword :

experimental measurement Hollow stator blade water removal performance suction slot

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GB/T 7714 Li, Liang , Wu, Xiaoming , Yang, Jiandao et al. Effects of location, shape and width of a suction slot on the water removal performance of a hollow stator blade [C] . 2018 : 461-472 .
MLA Li, Liang et al. "Effects of location, shape and width of a suction slot on the water removal performance of a hollow stator blade" . (2018) : 461-472 .
APA Li, Liang , Wu, Xiaoming , Yang, Jiandao , Feng, Zhenping . Effects of location, shape and width of a suction slot on the water removal performance of a hollow stator blade . (2018) : 461-472 .
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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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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
SCOPUS Cited Count: 2
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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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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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