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< Page ,Total 64 >
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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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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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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Optimization and Knowledge Discovery of a Three-Dimensional Parameterized Vane with Nonaxisymmetric Endwall EI SCIE Scopus
期刊论文 | 2018 , 34 (1) , 234-246 | JOURNAL OF PROPULSION AND POWER
WoS CC Cited Count: 3 SCOPUS Cited Count: 4
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Abstract :

The optimization and knowledge discovery of a low-aspect-ratio cascade was conducted. The techniques of nonaxisymmetric endwall contouring, section profiling, and compound lean were combined for cascade parameterization. Their effects on cascade performance were investigated through analysis of flow details and well-designed scatter plot. It is found that nonaxisymmetric endwall contouring is helpful to reduce the profile loss while also inhibiting the secondary flow. Section profiling is an effective technique to reduce the profile loss. And the lean structure is responsible for the multimodality of the loss function because it makes the reduction of profile loss and endwall loss in severe conflicting relation. The combination of the techniques is shown to effectively improve the cascade performance. In addition, through the analysis of self-organizing map and Pearson's correlation, the mass flow rate and outlet flow angle are found to be linearly correlated, whereas the relation between the loss and mass flow rate is complex. Finally, because the optimal solution is sensitive to the objective function as shown by the two optimization processes, the data mining of interactions among performance functions and design variables becomes very important, which can help to achieve the desirable design performance in the prescribed design space.

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GB/T 7714 Song, Liming , Guo, Zhendong , Li, Jun et al. Optimization and Knowledge Discovery of a Three-Dimensional Parameterized Vane with Nonaxisymmetric Endwall [J]. | JOURNAL OF PROPULSION AND POWER , 2018 , 34 (1) : 234-246 .
MLA Song, Liming et al. "Optimization and Knowledge Discovery of a Three-Dimensional Parameterized Vane with Nonaxisymmetric Endwall" . | JOURNAL OF PROPULSION AND POWER 34 . 1 (2018) : 234-246 .
APA Song, Liming , Guo, Zhendong , Li, Jun , Feng, Zhenping . Optimization and Knowledge Discovery of a Three-Dimensional Parameterized Vane with Nonaxisymmetric Endwall . | JOURNAL OF PROPULSION AND POWER , 2018 , 34 (1) , 234-246 .
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Numerical Investigation on the Leakage and Static Stability Characteristics of Pocket Damper Seals at High Eccentricity Ratios EI SCIE Scopus
期刊论文 | 2018 , 140 (4) | JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME
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Abstract :

Annular gas seals for compressors and turbines are designed to operate in a nominally centered position in which the rotor and stator are at concentric condition, but due to the rotor-stator misalignment or flexible rotor deflection, many seals usually are suffering from high eccentricity. The centering force (represented by static stiffness) of an annular gas seal at eccentricity plays a pronounced effect on the rotordynamic and static stability behavior of rotating machines. The paper deals with the leakage and static stability behavior of a fully partitioned pocket damper seal (FPDS) at high eccentricity ratios. The present work introduces a novel mesh generation method for the full 360 deg mesh of annular gas seals with eccentric rotor, based on the mesh deformation technique. The leakage flow rates, static fluid-induced response forces, and static stiffness coefficients were solved for the FPDS at high eccentricity ratios, using the steady Reynolds-averaged Navier-Stokes solution approach. The calculations were performed at typical operating conditions including seven rotor eccentricity ratios up to 0.9 for four rotational speeds (0 rpm, 7000 rpm, 11,000 rpm, and 15,000 rpm) including the nonrotating condition, three pressure ratios (0.17, 0.35, and 0.50) including the choked exit flow condition, two inlet preswirl velocities (0 m/s, 60 m/s). The numerical method was validated by comparisons to the experiment data of static stiffness coefficients at choked exit flow conditions. The static direct and cross-coupling stiffness coefficients are in reasonable agreement with the experiment data. An interesting observation stemming from these numerical results is that the FPDS has a positive direct stiffness as long as it operates at subsonic exit flow conditions; no matter the eccentricity ratio and rotational speed are high or low. For the choked exit condition, the FPDS shows negative direct stiffness at low eccentricity ratio and then crosses over to positive value at the crossover eccentricity ratio (0.5-0.7) following a trend indicative of a parabola. Therefore, the negative static direct stiffness is limited to the specific operating conditions: choked exit flow condition and low eccentricity ratio less than the crossover eccentricity ratio, where the pocket damper seal (PDS) would be statically unstable.

Keyword :

static stability characteristic pocket damper seal leakage characteristic high eccentricity ratio crossover eccentricity ratio

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GB/T 7714 Li, Zhigang , Li, Jun , Feng, Zhenping . Numerical Investigation on the Leakage and Static Stability Characteristics of Pocket Damper Seals at High Eccentricity Ratios [J]. | JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME , 2018 , 140 (4) .
MLA Li, Zhigang et al. "Numerical Investigation on the Leakage and Static Stability Characteristics of Pocket Damper Seals at High Eccentricity Ratios" . | JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME 140 . 4 (2018) .
APA Li, Zhigang , Li, Jun , Feng, Zhenping . Numerical Investigation on the Leakage and Static Stability Characteristics of Pocket Damper Seals at High Eccentricity Ratios . | JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME , 2018 , 140 (4) .
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Discussions on problem analysis and solutions of a micro turbine test EI SCIE Scopus
期刊论文 | 2018 , 24 (3) , 1433-1442 | MICROSYSTEM TECHNOLOGIES-MICRO-AND NANOSYSTEMS-INFORMATION STORAGE AND PROCESSING SYSTEMS
SCOPUS Cited Count: 1
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Abstract :

The performance test of the millimeter-scale turbine has many difficulties and challenges because of its inherent characteristics and its indispensable equipment. The test needs ultra-high rotational speed, compact structure, high machining accuracy, correct assembly clearance, allowable material strength, high temperature, sufficiently stable bearing, small dimensions and high accuracy measuring equipment, etc. In order to conduct the performance test of a millimeter-scale radial turbine, this paper mainly presents the problem analysis and solutions on exploratory experiment of a micro radial turbine by using the cold model. Firstly, the performance test platform was established. The test methods and test process was introduced. Then, the overall performance test was carried out and operation problems arising in the experiment was analyzed. Thirdly, the solutions for the test problems were proposed and discussed in details. After two stage tests, the maximum stabilized rotational speed of micro radial turbine has been increased to 359,900 rpm. This paper not only exhibits the specific and detailed difficulties and challenges, but also presents the solutions and other potential countermeasures or suggestions of ultra-high rotational speed experiment, which can be taken as engineering guidance and reference for other designers.

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GB/T 7714 Fu, Lei , Feng, Zhenping , Li, Guojun . Discussions on problem analysis and solutions of a micro turbine test [J]. | MICROSYSTEM TECHNOLOGIES-MICRO-AND NANOSYSTEMS-INFORMATION STORAGE AND PROCESSING SYSTEMS , 2018 , 24 (3) : 1433-1442 .
MLA Fu, Lei et al. "Discussions on problem analysis and solutions of a micro turbine test" . | MICROSYSTEM TECHNOLOGIES-MICRO-AND NANOSYSTEMS-INFORMATION STORAGE AND PROCESSING SYSTEMS 24 . 3 (2018) : 1433-1442 .
APA Fu, Lei , Feng, Zhenping , Li, Guojun . Discussions on problem analysis and solutions of a micro turbine test . | MICROSYSTEM TECHNOLOGIES-MICRO-AND NANOSYSTEMS-INFORMATION STORAGE AND PROCESSING SYSTEMS , 2018 , 24 (3) , 1433-1442 .
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Investigation on design flow of a millimeter-scale radial turbine for micro gas turbine EI SCIE Scopus
期刊论文 | 2018 , 24 (5) , 2333-2347 | MICROSYSTEM TECHNOLOGIES-MICRO-AND NANOSYSTEMS-INFORMATION STORAGE AND PROCESSING SYSTEMS
SCOPUS Cited Count: 2
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Abstract :

As compared to the conventional large scale gas turbines, the aerothermodynamics design of a micro gas turbine will be quite different not only due to the small scale effects, but also due to the constraints associated with many considerations. As a major component and main work unit of the micro gas turbine, the design flow and the design results of the micro radial turbine directly determine the physical realization of the micro gas turbine. This paper mainly presents the investigation and discussion on scaling considerations and the design flow through a micro radial turbine which with diameter of 10 mm for a 50 W-class micro gas turbine. Firstly, theoretical analysis of scaling effects, thermodynamics, fluid mechanics, turbomachinery aerothermodynamics, heat transfer and rotor dynamics are described. Secondly, four sub-modules of different design considerations are constructed and the periodical design results are presented. Finally, the design flow of millimeter-scale radial turbine is proposed. The results indicate that the distinctive design principles and design challenges are not negligible and the discussions and definitions of the design flow for the micro turbine are essential. These works not only methodize the design details, but also define the basic design flow as the reference for the new designer.

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GB/T 7714 Fu, Lei , Feng, Zhenping , Li, Guojun . Investigation on design flow of a millimeter-scale radial turbine for micro gas turbine [J]. | MICROSYSTEM TECHNOLOGIES-MICRO-AND NANOSYSTEMS-INFORMATION STORAGE AND PROCESSING SYSTEMS , 2018 , 24 (5) : 2333-2347 .
MLA Fu, Lei et al. "Investigation on design flow of a millimeter-scale radial turbine for micro gas turbine" . | MICROSYSTEM TECHNOLOGIES-MICRO-AND NANOSYSTEMS-INFORMATION STORAGE AND PROCESSING SYSTEMS 24 . 5 (2018) : 2333-2347 .
APA Fu, Lei , Feng, Zhenping , Li, Guojun . Investigation on design flow of a millimeter-scale radial turbine for micro gas turbine . | MICROSYSTEM TECHNOLOGIES-MICRO-AND NANOSYSTEMS-INFORMATION STORAGE AND PROCESSING SYSTEMS , 2018 , 24 (5) , 2333-2347 .
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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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Effects of location and profile of upstream slot on the endwall aerothermal performance of a gas turbine blade EI SCIE Scopus
期刊论文 | 2018 , 140 , 637-656 | APPLIED THERMAL ENGINEERING
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The effects of location and profile of an upstream slot on endwall flow and heat transfer characteristics of a gas turbine blade are numerically investigated in this paper. On the basis of validation of the numerical method, the Reynolds-averaged Navier-Stokes equations and the standard k-omega turbulence model are used in the current study. Slots located at 10%, 20% and 30% of the axial chord length upstream of the leading edge plane and three convergent slot profiles are analyzed to reveal their effects on endwall fluid flow and thermal behavior. The results indicate that the slot at 10% of C-ax upstream has the best cooling performance for most of the endwall, but there is a cooling failure region on the middle part of the endwall when the coolant to main flow mass flow ratio is lower than 1.0%, while the slot at 30% of C-ax prevents the cooling failure region from appearing. Besides, as the distance between the slot and the blade leading edge is reduced, the aerodynamic losses are reduced. Compared with a normal slot, the convergent slots proposed in this paper provide better cooling protection for the endwall and prevents cooling failure on the endwall if both the film cooling effectiveness and heat transfer coefficient on the endwall are taken into account. Convergent slots also reduced aerodynamic losses when mass flow ratio is higher than 1.0%. Among the convergent slots, the convergent slot A has the greatest cooling and least aerodynamic loss.

Keyword :

Numerical simulation Film cooling Gas turbine Upstream slot Blade endwall Aerothermal performance

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GB/T 7714 Song, Liming , Zhu, Peiyuan , Li, Jun et al. Effects of location and profile of upstream slot on the endwall aerothermal performance of a gas turbine blade [J]. | APPLIED THERMAL ENGINEERING , 2018 , 140 : 637-656 .
MLA Song, Liming et al. "Effects of location and profile of upstream slot on the endwall aerothermal performance of a gas turbine blade" . | APPLIED THERMAL ENGINEERING 140 (2018) : 637-656 .
APA Song, Liming , Zhu, Peiyuan , Li, Jun , Feng, Zhenping . Effects of location and profile of upstream slot on the endwall aerothermal performance of a gas turbine blade . | APPLIED THERMAL ENGINEERING , 2018 , 140 , 637-656 .
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