Analysis and Optimization of Film Cooling Effectiveness PDF Download

Author: Hessam Babaee
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Author: Shahin Salimi
Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 140

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Author: Ara Manuel Demirjian
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 330

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Author: Debashis Dutta
Publisher: Springer Nature
ISBN: 981153215X
Category : Technology & Engineering
Languages : en
Pages : 569

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Book Description
This book presents select peer-reviewed papers presented at the International Conference on Numerical Optimization in Engineering and Sciences (NOIEAS) 2019. The book covers a wide variety of numerical optimization techniques across all major engineering disciplines like mechanical, manufacturing, civil, electrical, chemical, computer, and electronics engineering. The major focus is on innovative ideas, current methods and latest results involving advanced optimization techniques. The contents provide a good balance between numerical models and analytical results obtained for different engineering problems and challenges. This book will be useful for students, researchers, and professionals interested in engineering optimization techniques.

Author: Mohammed Aref Al-Hemyari
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 58

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"Cooling gas turbine blades is a crucial technique to allow higher turbine inlet temperatures. A higher turbine inlet temperature allows boosting gas turbine efficiency, which reduces fuel consumption. One of the main cooling techniques of the turbine blades is film cooling where a relatively low air temperature is used to form a blanket of cool air around the blade to shield it from high temperature gases. Many complex interrelated geometry and flow parameters affect the effectiveness of the film cooling. The complex interrelations between these parameters are considered the main challenge in properly understanding the effect of these parameters on film cooling. Testing such cooling techniques under actual engine conditions is even more challenging due to difficulty of installing proper instrumentations. Numerical techniques are viable analysis techniques that are used to better understand film cooling techniques. In this study, a simplified 2D film cooling jet blown from the slot jet is investigated under multiple variable parameters, mainly, the blowing ratio, jet angle, density ratio and centrifugal force. The performance of the film cooling is reported using local and average adiabatic film effectiveness. The main contribution of this study is exploring the effect of the centrifugal force and wall material selection using conjugate heat transfer on film cooling effectiveness. The centrifugal force reduces the overall adiabatic film effectiveness. A correlation between the blowing ratio, density ratio and injection angle is developed in this work. The highest film cooling performance was founded at a blowing ratio of 0.8, an injection angle of 30° and density ratio of 1.2."--Abstract.

Author: Daniel Gutierrez (M.S. in Engineering)
Publisher:
ISBN:
Category :
Languages : en
Pages : 0

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Advancement in additive manufacturing (AM) methods along with the application to gas turbine component manufacturing has expanded the feasibility of creating complex hole geometries to be used in gas turbines. The design possibilities for new hole geometries have become unlimited as these improved AM methods allow for the creation of holes with complex hole geometries such as rounded inlets, protrusions in the surface of the inlet and outlet of holes, among others. This advancement in such technology has sparked interest among turbine research groups for the design and creation of optimized versions of holes that showcase sophisticated geometries, which would otherwise not be possible to be manufactured using conventional manufacturing methods. Recently, a computational adjoint based optimization method by a past student in our lab (Fraser B. Jones) was used to design shaped film cooling holes fed by internal co-flow and cross-flow channels. The CFD simulations for said hole geometries predicted that the holes optimized for use with cross-flow (X-AOpt) and co-flow (Co-AOpt) would significantly increase adiabatic effectiveness. However, only the X-AOpt hole was tested experimentally in this previous study. In this study, adiabatic and matched Biot number models were built for 5X engine scale models of the X-AOpt and Co-AOpt shaped holes and tested experimentally in a low speed wind tunnel facility. The optimized shaped holes are experimentally evaluated using measurements of adiabatic effectiveness and overall cooling effectiveness. Coolant was fed to the holes with an internal co-flow channel and tested at various blowing ratios (M=0.5-4). For reference, experiments were also conducted with 5X engine scale models for the baseline 7-7-7 sharp inlet (SI) shaped hole, and a 15-15-1 rounded inlet (RI) shaped hole (shown in a previous parametric optimization study by Jones to be the optimum expansion angles for a shaped hole). Discharge coefficient, C [subscript d], measurements for the Co-AOpt geometry are analyzed in greater detail and compared against the other hole geometries tested for the study. In addition, computational predictions of C [subscript d] for a 15-15-1 RI hole will be compared against experimental measurements from this study. Results from the experiments performed at the low speed facility for 5X scale models confirmed that the X-AOpt hole had a 75% increase in adiabatic effectiveness compared to the 7-7-7 SI shaped hole. However, the Co-AOpt hole had only a 30% increase in adiabatic effectiveness, which is substantially less than had been computationally predicted

Author: Dale Wilson Fox (III)
Publisher:
ISBN:
Category :
Languages : en
Pages : 0

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Film cooling literature is concentrated in subsonic experimental measurements, despite the common occurrence of high Mach numbers within gas turbine engines. This dissertation focuses on the extension of analytical, numerical, and experimental methodologies to the compressible regime, for the accurate understanding of film cooling in these transonic conditions. It discusses the design and construction of a new experimental facility for the measurement of film cooling effectiveness, as well as the complications of extending traditional film cooling analysis into compressible flow regimes

Author: Vera Murgul
Publisher: Springer Nature
ISBN: 3030574539
Category : Technology & Engineering
Languages : en
Pages : 723

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Book Description
This book is intended to assist to improve energy efficiency in the industrial sector. The book offers case studies for industrial energy efficiency improvement and contains brief reports on cutting-edge research in all fields of the energy industry. This book, which is composed of select research proceedings of the EMMFT 2019 conference, covers such issues as: good quality energy use, energy generation technologies, materials used for energy generation, and storage technologies, as well as materials for water purification, petroleum engineering, and digital energy systems. The case studies discussed comprise the use of fossil fuel and non-fossil fuel energy resources, novel materials with advanced heat transport or heat resistance, and energy digitalization. Coverage extends to all theoretical and applied aspects of the field. This book is an ideal resource for scientists and energy analysts, industrial practitioners, engineers, researchers, and postgraduate students working in the field of management and technology for improving energy efficiency in the industry. Also, the book is of interest to researchers, engineers, and laboratory personnel in the fields of power systems and smart grids.

Author: Lamyaa El-Gabry
Publisher: BiblioGov
ISBN: 9781289236779
Category :
Languages : en
Pages : 40

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Book Description
Computational Fluid Dynamics is used in the analysis of a film cooling jet in crossflow. Predictions of film effectiveness are compared with experimental results for a circular jet at blowing ratios ranging from 0.5 to 2.0. Film effectiveness is a surface quantity which alone is insufficient in understanding the source and finding a remedy for shortcomings of the numerical model. Therefore, in addition, comparisons are made to flow field measurements of temperature along the jet centerline. These comparisons show that the CFD model is accurately predicting the extent and trajectory of the film cooling jet; however, there is a lack of agreement in the near-wall region downstream of the film hole. The effects of main stream turbulence conditions, boundary layer thickness, turbulence modeling, and numerical artificial dissipation are evaluated and found to have an insufficient impact in the wake region of separated films (i.e. cannot account for the discrepancy between measured and predicted centerline fluid temperatures). Analyses of low and moderate blowing ratio cases are carried out and results are in good agreement with data.

Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0

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An analytical model has been developed for two problems of gun barrel cooling: a. film cooling with wear reducing additives and b. liquid film cooling. The governing equations were derived from an integral method and the solutions of the film-cooling effectiveness were obtained by application of the characteristic method. The results found earlier are: (a) with the additives, the effectiveness is very significant in a region where the erosion is most series and (b) with liquid cooling, the effectiveness is in general high. It is, however, smaller in that region.