Volume 5C: Heat Transfer最新文献

An Experimental Investigation of Full-Coverage Film Cooling Characteristics of a Turbine Guide Vane 涡轮导叶全覆盖气膜冷却特性的实验研究

Volume 5C: Heat Transfer Pub Date : 2018-06-11 DOI: 10.1115/GT2018-76088

Jin Wu, Li Zhang, Lijian Cheng, R. Jiang, Zhong-yi Fu, Hui-ren Zhu

{"title":"An Experimental Investigation of Full-Coverage Film Cooling Characteristics of a Turbine Guide Vane","authors":"Jin Wu, Li Zhang, Lijian Cheng, R. Jiang, Zhong-yi Fu, Hui-ren Zhu","doi":"10.1115/GT2018-76088","DOIUrl":"https://doi.org/10.1115/GT2018-76088","url":null,"abstract":"This paper researches on the effects of Reynolds number and mass flow ratio on the film cooling characteristics at high turbulence intensity (Tu = 15%). The experiment adopted an actual three-dimensional twisted vane and presents the film cooling characteristics on full-coverage film surface in a two-passage, linear cascade. The cooling effectiveness and heat transfer coefficient of the vane’s whole surface were obtained by using transient liquid crystal measurement technique. The transient liquid crystal is SPN/R35C1W, whose bandwidth is 2°C. There are fifteen rows of film cooling holes which have different diameter, injection angle and yaw angle. The secondary flow was supplied by two cavities. The front cavity supplied the secondary flow to thirteen rows of film cooling holes that were arranged in the suction surface, the leading edge and the front half of the pressure surface. The rear cavity supplied the secondary flow to the rear half of pressure surface which included two rows of film cooling holes. The investigated parameters are Reynolds number of 1 × 105, 1.3 × 105 and 1.6 × 105 and the mass flow ratio of MFR = 5.5%∼12.5% (6 cases). The data recorded in the experiment was analyzed with MATLAB.\u0000 Results show that the combined effects of mass flow ratio and channel vortex are the maintain reasons that influence the distribution of cooling effectiveness in the contour. Increasing the mass flow ratio can improve the film cooling effectiveness on leading edge and pressure surface, while that presents complex rule on suction surface. Increasing the Reynolds number can improve the heat transfer coefficient at the same mass flow ratio. When increasing the mass flow ratio, the heat transfer coefficient increases on leading edge and pressure surface at Re = 1.6 × 105. However, the decreases at film hole outlet region on the suction side, and not obviously changes at the film hole downstream region.","PeriodicalId":239866,"journal":{"name":"Volume 5C: Heat Transfer","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125806502","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Aerodynamic and Heat Transfer Experimental Investigation of Platform Cooling on a HP Nozzle Vane Cascade 高压喷嘴叶片叶栅平台冷却的气动与传热实验研究

Volume 5C: Heat Transfer Pub Date : 2018-06-11 DOI: 10.1115/GT2018-75038

G. Barigozzi, S. Mosconi, A. Perdichizzi, L. Abba, S. Vagnoli

{"title":"Aerodynamic and Heat Transfer Experimental Investigation of Platform Cooling on a HP Nozzle Vane Cascade","authors":"G. Barigozzi, S. Mosconi, A. Perdichizzi, L. Abba, S. Vagnoli","doi":"10.1115/GT2018-75038","DOIUrl":"https://doi.org/10.1115/GT2018-75038","url":null,"abstract":"The present paper reports on an experimental investigation carried out at Bergamo University Energy system and turbomachinery laboratory aiming to assess the aerodynamic and heat transfer performance of a high pressure nozzle vane cascade without and with platform cooling. Information collected from solid vane testing was used to design a first platform cooling scheme made of cylindrical holes. The cooling scheme was first aerodynamically tested to quantify its impact on secondary flows and related losses for variable injection condition. Heat transfer performances were then assessed through the measurement of the adiabatic film cooling effectiveness and of the convective heat transfer coefficient. From these data, the Net Heat Flux Reduction (NHFR) parameter was computed to critically assess the cooling scheme. The collected data set is significant for the design process, as it is useful for CFD validation and for the setting up of correlations. In particular, a MFR = 0.7% resulted to be the best injection condition for this geometry, being a compromise between aerodynamic loss augmentation, a good thermal protection inside of the passage and a limited heat load increase to the end wall.","PeriodicalId":239866,"journal":{"name":"Volume 5C: Heat Transfer","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114174451","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 3

Mathematical Simulation of the Gas Turbine Packages Thermal State 燃气轮机机组热状态的数学模拟

Volume 5C: Heat Transfer Pub Date : 2018-06-11 DOI: 10.1115/GT2018-77194

O. Kyrylash, V. Kostiuk, A. Smirnov, D. Tkachenko, Igor Loboda

引用次数: 1

CFD Investigation of the Flow of Trailing Edge Cooling Slots 后缘冷却槽流动的CFD研究

Volume 5C: Heat Transfer Pub Date : 2018-06-11 DOI: 10.1115/GT2018-75906

Yuewen Jiang, Niharika Gurram, E. Romero, P. Ireland, L. Mare

{"title":"CFD Investigation of the Flow of Trailing Edge Cooling Slots","authors":"Yuewen Jiang, Niharika Gurram, E. Romero, P. Ireland, L. Mare","doi":"10.1115/GT2018-75906","DOIUrl":"https://doi.org/10.1115/GT2018-75906","url":null,"abstract":"Slot film cooling is a popular choice for trailing edge cooling in high pressure (HP) turbine blades because it can provide more uniform film coverage compared to discrete film cooling holes. The slot geometry consists of a cut back in the blade pressure side connected through rectangular openings to the internal coolant feed passage. The numerical simulation of this kind of film cooling flows is challenging due to the presence of flow interactions like step flow separation, coolant-mainstream mixing and heat transfer.\u0000 The geometry under consideration is a cutback surface at the trailing edge of a constant cross-section aerofoil. The cutback surface is divided into three sections separated by narrow lands. The experiments are conducted in a high speed cascade in Oxford Osney Thermo-Fluids Laboratory at Reynolds and Mach number distributions representative of engine conditions. The capability of CFD methods to capture these flow phenomena is investigated in this paper. The isentropic Mach number and film effectiveness are compared between CFD and pressure sensitive paint (PSP) data. Compared to steady k–ω SST method, Scale Adaptive Simulation (SAS) can agree better with the measurement. Furthermore, the profiles of kinetic energy, production and shear stress obtained by the steady and SAS methods are compared to identify the main source of inaccuracy in RANS simulations. The SAS method is better to capture the unsteady coolant-hot gas mixing and vortex shedding at the slot lip.\u0000 The cross flow is found to affect the film significantly as it triggers flow separation near the lands and reduces the effectiveness. The film is non-symmetric with respect to the half-span plane and different flow features are present in each slot. The effect of mass flow ratio (MFR) on flow pattern and coolant distribution is also studied. The profiles of velocity, kinetic energy and production of turbulent energy are compared among the slots in detail. The MFR not only affects the magnitude but also changes the sign of production.","PeriodicalId":239866,"journal":{"name":"Volume 5C: Heat Transfer","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128886293","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Flowfield of a Shaped Film Cooling Hole Over a Range of Compound Angles 在复合角度范围内的形膜冷却孔流场

Volume 5C: Heat Transfer Pub Date : 2018-06-11 DOI: 10.1115/GT2018-75728

Shane Haydt, S. Lynch

{"title":"Flowfield of a Shaped Film Cooling Hole Over a Range of Compound Angles","authors":"Shane Haydt, S. Lynch","doi":"10.1115/GT2018-75728","DOIUrl":"https://doi.org/10.1115/GT2018-75728","url":null,"abstract":"Film cooling holes are a well-established cooling technique used in gas turbines to keep component metal temperatures in an acceptable range. A streamwise-oriented film cooling hole creates a symmetric counter-rotating vortex pair (CRVP) due to the jet interaction with the crossflow. As the orientation of the film cooling hole is incrementally misaligned with the streamwise direction (known as a compound angle), one of the vortices in the CRVP gains strength at the expense of the other until there is a single streamwise vortex that dominates the flowfield. This vortex diffuses the coolant jet and impinges hot gas onto the surface, which can augment heat transfer coefficients in a region uncovered by coolant. Although this has been well studied for cylindrical holes, there is less understanding about the nature of this phenomenon for shaped holes, which are intended to diffuse coolant laterally to minimize flowfield interaction. In the present study, particle image velocimetry (PIV) was used to measure the flowfield of compound angled shaped film cooling holes at several downstream planes normal to the streamwise direction. Five compound angled 7-7-7 holes were tested, from a streamwise oriented hole (0° compound angle) to a 60° compound angle hole, in increments of 15°. All cases were tested at a density ratio of 1.0 and blowing ratios ranging from 1.0 to 4.0. Experimental data shows that the circulation increases as compound angle increases because the flowfield transitions from a CRVP to a single streamwise vortex. For large compound angles, the streamwise vortex lifts the core of the jet off of the surface, isolating the coolant from the endwall. Measurements also indicate hole-to-hole interaction downstream for cases with high blowing ratio and large compound angle. Flowfield results are compared with adiabatic effectiveness results from a companion study in order to explain hole-to-hole interaction trends.","PeriodicalId":239866,"journal":{"name":"Volume 5C: Heat Transfer","volume":"355 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124052494","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 9

A Review of Impingement Jet Cooling in Combustor Liner 燃烧室尾管冲击射流冷却研究进展

Volume 5C: Heat Transfer Pub Date : 2018-06-11 DOI: 10.1115/GT2018-76335

Rong-rong Xie, Hao Wang, Baopeng Xu, Wei Wang

{"title":"A Review of Impingement Jet Cooling in Combustor Liner","authors":"Rong-rong Xie, Hao Wang, Baopeng Xu, Wei Wang","doi":"10.1115/GT2018-76335","DOIUrl":"https://doi.org/10.1115/GT2018-76335","url":null,"abstract":"Impingement jet cooling is a promising cooling method in modern dry low emission combustor because of its high local heat transfer coefficient. This paper investigates the recent research progress on impingement jet cooling in combustor liner. Firstly, the different flow characteristics in the different impingement jet flow regions are described. Then, the factors influencing impingement jet cooling are discussed, including flow factor and geometry factor. The researches in a large range of flow parameters, including Reynolds number, Mach number and temperature ratio, are reported. The researches in different geometry parameters, such as nozzle geometry, nozzle-to-nozzle spacing, nozzle-to-target distance and inclined angle, are presented. Next, the crossflow effect in array impingement jet is considered. Due to the crossflow decreases the heat transfer performance, varieties of structures which can restrict the crossflow and improve the channel flow are introduced. Finally, the methods to enhance the impingement jet cooling are presented. These methods focus on retrofitting the nozzle and target surface. The combination of impingement jet cooling with other methods, such as effusion cooling, rib roughened surface, is important development direction in combustor liner in the future.","PeriodicalId":239866,"journal":{"name":"Volume 5C: Heat Transfer","volume":"50 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114230960","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 7

Numerical Investigation of Fluid Flow Parameters in a Combustor Simulator 燃烧室模拟器流体流动参数的数值研究

Volume 5C: Heat Transfer Pub Date : 2018-06-11 DOI: 10.1115/GT2018-75018

D. G. Barhaghi, Lars Hedlund

{"title":"Numerical Investigation of Fluid Flow Parameters in a Combustor Simulator","authors":"D. G. Barhaghi, Lars Hedlund","doi":"10.1115/GT2018-75018","DOIUrl":"https://doi.org/10.1115/GT2018-75018","url":null,"abstract":"In recent years computational fluid dynamics (CFD) is substantially employed in the design process of gas turbines. To increase the performance of the turbines an efficient cooling system design is essential. This is largely dependent on the accuracy of the predicted temperature at the exit of the combustor. Lack of accuracy of the predicted temperature at the combustor-turbine interface results in using large safety factors which affect the performance negatively.\u0000 It is believed that the RANS methods are incapable of predicting the mixing process in highly swirling flows in the combustors. In this study the flow in a none-reactive model combustor simulator is investigated numerically using RANS, SAS and LES turbulence models in ANSYS CFX code. The model combustor consists of three swirling mixers through which the hot air passes. The cold air that goes through many small effusion holes of the outer and inner liners mixes up with the swirling hot air. The computational domain however consists only of one sector and periodic boundary condition is applied in the circumferential direction.\u0000 The numerical results are compared with the experimental results that are provided by the University of Florence as part of the European FACTOR project. It is confirmed that the RANS or URANS methods are not capable of reproducing the experimental results.","PeriodicalId":239866,"journal":{"name":"Volume 5C: Heat Transfer","volume":"200 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121674613","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

Investigation on the Leading Edge Film Cooling of Counter-Inclined Cylindrical and Laid-Back Holes With and Without Impingement: Part II — Heat Transfer Coefficient 有和无碰撞时反斜圆柱孔和斜孔前缘气膜冷却的研究:第二部分——传热系数

Volume 5C: Heat Transfer Pub Date : 2018-06-11 DOI: 10.1115/GT2018-76066

Rui-dong Wang, Cun-liang Liu, Hai-yong Liu, Hui-ren Zhu, Qi-ling Guo, Chao Gao

{"title":"Investigation on the Leading Edge Film Cooling of Counter-Inclined Cylindrical and Laid-Back Holes With and Without Impingement: Part II — Heat Transfer Coefficient","authors":"Rui-dong Wang, Cun-liang Liu, Hai-yong Liu, Hui-ren Zhu, Qi-ling Guo, Chao Gao","doi":"10.1115/GT2018-76066","DOIUrl":"https://doi.org/10.1115/GT2018-76066","url":null,"abstract":"Heat transfer of the counter-inclined cylindrical and laid-back holes with and without impingement on the turbine vane leading edge model are investigated in this paper. To obtain the film cooling effectiveness and heat transfer coefficient, transient temperature measurement technique on complete surface based on double thermochromic liquid crystals is used in this research. A semi-cylinder model is used to model the vane leading edge which is arranged with two rows of holes. Four test models are measured under four blowing ratios including cylindrical film holes with and without impingement tube structure, laid-back film holes with and without impingement tube structure. This is the second part of a two-part paper, the first part paper GT2018-76061 focuses on film cooling effectiveness and this study will focus on heat transfer. Contours of surface heat transfer coefficient and laterally averaged result are presented in this paper. The result shows that the heat transfer coefficient on the surface of the leading edge is enhanced with the increase of blowing ratio for same structure. The shape of the high heat transfer coefficient region gradually inclines to span-wise direction as the blowing ratio increases. Heat transfer coefficient in the region where the jet core flows through is relatively lower, while in the jet edge region the heat transfer coefficient is relatively higher. Compared with cylindrical hole, laid-back holes give higher heat transfer coefficient. Meanwhile, the introduction of impingement also makes heat transfer coefficient higher compared with cross flow air intake. It is found that the heat transfer of the combination of laid-back hole and impingement tube can be very high under large blowing ratio which should get attention in the design process.","PeriodicalId":239866,"journal":{"name":"Volume 5C: Heat Transfer","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130363302","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Computational Analysis of an Additively Manufactured Cooled Ultra Compact Combustor Vane 一种增材制造的冷却超紧凑燃烧室叶片计算分析

Volume 5C: Heat Transfer Pub Date : 2018-06-11 DOI: 10.1115/GT2018-75392

Kevin J. DeMarco, Brian T. Bohan, M. Polanka, J. L. Rutledge, P. Akbari

引用次数: 1

Film Cooling Effectiveness From Two-Row of Compound Angled Cylindrical Holes Using PSP Technique 用PSP技术对两排复合角度圆柱孔的气膜冷却效果

Volume 5C: Heat Transfer Pub Date : 2018-06-11 DOI: 10.1115/GT2018-75167

Nian Wang, Mingjie Zhang, Chao-Cheng Shiau, Je-Chin Han

{"title":"Film Cooling Effectiveness From Two-Row of Compound Angled Cylindrical Holes Using PSP Technique","authors":"Nian Wang, Mingjie Zhang, Chao-Cheng Shiau, Je-Chin Han","doi":"10.1115/GT2018-75167","DOIUrl":"https://doi.org/10.1115/GT2018-75167","url":null,"abstract":"This study investigates the combined effects of blowing ratio and density ratio on flat plate film cooling effectiveness from two-row of compound angled cylindrical holes. Two arrangements of two-row compound angled cylindrical holes are tested: the first row and second row are oriented in staggered but same compound angled direction (β = +45° for the first row, +45° for the second row); the first row and second row are oriented in inline but opposite direction (β = +45° for the first row, −45° for the second row). Each cooling hole is 4 mm in diameter with an inclined angle 30°. The streamwise distance between the two rows is fixed at 4d and the spanwise pitch between the two holes (p) is 4d, 6d, and 8d, respectively. The experiments are performed at four blowing ratios (M = 0.5, 1.0, 1.5, 2.0) and three density ratios (DR = 1.0, 1.5, 2.0). The free stream turbulence intensity is kept at 6%. Detailed film cooling effectiveness distributions are obtained using the steady state pressure-sensitive paint (PSP) technique. The detailed film cooling effectiveness contours are presented and the spanwise averaged film effectiveness results are compared over the range of flow parameters. Film cooling effectiveness correlations are developed for both inline and staggered compound angled cylindrical holes. The results provide baseline information for the flat plate film cooling analysis with two-row of compound angled cylindrical holes.","PeriodicalId":239866,"journal":{"name":"Volume 5C: Heat Transfer","volume":"24 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124015491","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 3