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Author: Yehia A. Eldrainy Publisher: Penerbit UTM Press ISBN: 9835208530 Category : Combustion, Theory of Languages : en Pages : 5
Book Description
This book describes the new innovation of gas turbine swirler. The novel swirler is a multiple entry swirler which allows the swirl number to vary on the same value of Reynolds number, by regulating the ratio between the axial and tangential flow momentum. Three–dimensional turbulence and isothermal flow characteristics of an abrupt combustor model with different type of swirler (axial, radial and multiple inlet) were simulated with Reynolds–Averaged Navier–Stokes (RANS) using ANSYS Fluent 12 software. Results of the different turbulence models used in swirling flow were reviewed and compared. The different swirler’ aerodynamic performance was investigated through Computational Fluid Dynamics (CFD) simulations. The aerodynamics performance includes shape and size of the Central Recirculation Zone (CRZ), turbulence intensity and pressure losses. It was found that the size of then CRZ and turbulence strength is directly proportional to the tangential axial air flow rate ratio. Therefore, proper selection of a swirler is needed to enhance combustor performance and to reduce exhaust emissions.
Author: Yehia A. Eldrainy Publisher: Penerbit UTM Press ISBN: 9835208530 Category : Combustion, Theory of Languages : en Pages : 5
Book Description
This book describes the new innovation of gas turbine swirler. The novel swirler is a multiple entry swirler which allows the swirl number to vary on the same value of Reynolds number, by regulating the ratio between the axial and tangential flow momentum. Three–dimensional turbulence and isothermal flow characteristics of an abrupt combustor model with different type of swirler (axial, radial and multiple inlet) were simulated with Reynolds–Averaged Navier–Stokes (RANS) using ANSYS Fluent 12 software. Results of the different turbulence models used in swirling flow were reviewed and compared. The different swirler’ aerodynamic performance was investigated through Computational Fluid Dynamics (CFD) simulations. The aerodynamics performance includes shape and size of the Central Recirculation Zone (CRZ), turbulence intensity and pressure losses. It was found that the size of then CRZ and turbulence strength is directly proportional to the tangential axial air flow rate ratio. Therefore, proper selection of a swirler is needed to enhance combustor performance and to reduce exhaust emissions.
Author: Meredith Colket Publisher: ISBN: 9781624106033 Category : Fuel switching Languages : en Pages : 0
Book Description
In summarizing the results obtained in the first five years of the National Jet Fuel Combustion Program (NJFCP), this book demonstrates that there is still much to be learned about the combustion of alternative jet fuels.
Author: Sashi Kanta Panigrahi Publisher: CRC Press ISBN: 1138032840 Category : Technology & Engineering Languages : en Pages : 156
Book Description
The book is focused on theoretical and experimental investigation aimed at detecting and selecting proper information related to the fundamental aspect of combustion casing design,performance and life evaluation parameters. A rational approach has been adopted to the analysis domain underlying the complexities of the process.
Author: Kenneth C. Hall Publisher: Springer Science & Business Media ISBN: 1402046057 Category : Technology & Engineering Languages : en Pages : 605
Book Description
This textbook is a collection of technical papers that were presented at the 10th International Symposium on Unsteady Aerodynamics, Aeroacoustics, and Aeroelasticity of Turbomachines held September 8-11, 2003 at Duke University in Durham, North Carolina. The papers represent the latest in state of the art research in the areas of aeroacoustics, aerothermodynamics, computational methods, experimental testing related to flow instabilities, flutter, forced response, multistage, and rotor-stator effects for turbomachinery.
Author: Publisher: ISBN: Category : Aeronautics Languages : en Pages : 980
Book Description
Two-volume collection of case studies on aspects of NACA-NASA research by noted engineers, airmen, historians, museum curators, journalists, and independent scholars. Explores various aspects of how NACA-NASA research took aeronautics from the subsonic to the hypersonic era.-publisher description.
Author: Jushan Chin Publisher: Nova Science Publishers ISBN: 9781685071097 Category : Technology & Engineering Languages : en Pages : 165
Book Description
"The aim of this book is to identify that extra high-pressure ratio (such as about 70) civil aero engine low emissions combustors and extra high fuel air ratio (FAR) (such as FAR greater than 0.051) military aero engine combustors make up the next generation of aero combustors. The aero thermal design of these combustors is very different from previous combustors and the major design points are proposed. Two types of high-pressure low emissions combustor design have been suggested: one is without fuel staging and the other is with fuel staging. The high FAR combustor design is brand new. The layout of the next-generation aero combustor is very different. There are no primary holes, no intermediate holes, and no dilution holes. They all have direct mixing combustion. For low-emissions combustors, it is lean direct mixing (LDM) combustion. For high-FAR combustors, it is stoichiometric direct mixing combustion. Combustion air fraction is very high (such as greater than 75%). That will induce idle condition lean blow out (LBO) issue. The present book has proposed several design approaches to solve idle LBO issue, which are effective. Pilot fuel air combustion is designed at idle condition. For civil combustor, maximum condition is designed for low emissions, while for high FAR combustor, maximum condition is designed for non-visible smoke, low luminous flame radiation and good combustion efficiency. For each type of combustor, the fuel air module configuration is designed, which is the most essential part of combustor design. The brand-new combustor cooling design has used a compound angle tangential inlet cooling hole configuration. Such a cooling design provides high cooling effectiveness. The diffuser configuration is totally new. It is an air bleeding diffuser, directly stretching forward to contact the dome. The bled air flows to the annular channel as cooling air. Aero combustor development is discussed in this book. In particular, the combustor developments from technology readiness level (TRL) 3 to TRL level 6 have been discussed in detail. Also reported is the technology to run combustor development tests correctly. Three topics of related combustion research by the present author are summarized in the brochure. They are: a. Fuel injection and co-flowing air combination. The key point is, for next generation combustor development, the designer should not only think about atomization. The combination of fuel injection and co-flowing air should be considered together as a whole device. b. Fuel spray evaporation calculation, the key is an engineering calculation of multi-component fuel evaporation shall be used. c. Non-luminous flame radiation calculation, which has been significantly updated. The present book is a summary of the author's ten years of study on next-generation aero combustors after retirement. It represents advanced aero combustor technology level"--
Author: Dan Zhao Publisher: Academic Press ISBN: 0323899188 Category : Technology & Engineering Languages : en Pages : 1145
Book Description
Thermoacoustic Combustion Instability Control: Engineering Applications and Computer Codes provides a unique opportunity for researchers, students and engineers to access recent developments from technical, theoretical and engineering perspectives. The book is a compendium of the most recent advances in theoretical and computational modeling and the thermoacoustic instability phenomena associated with multi-dimensional computing methods and recent developments in signal-processing techniques. These include, but are not restricted to a real-time observer, proper orthogonal decomposition (POD), dynamic mode decomposition, Galerkin expansion, empirical mode decomposition, the Lattice Boltzmann method, and associated numerical and analytical approaches. The fundamental physics of thermoacoustic instability occurs in both macro- and micro-scale combustors. Practical methods for alleviating common problems are presented in the book with an analytical approach to arm readers with the tools they need to apply in their own industrial or research setting. Readers will benefit from practicing the worked examples and the training provided on computer coding for combustion technology to achieve useful results and simulations that advance their knowledge and research. Focuses on applications of theoretical and numerical modes with computer codes relevant to combustion technology Includes the most recent modeling and analytical developments motivated by empirical experimental observations in a highly visual way Provides self-contained chapters that include a comprehensive, introductory section that ensures any readers new to this topic are equipped with required technical terms
Author: Yehia A. Eldrainy
Author: Yehia A. Eldrainy
Author: Meredith Colket
Author: János Miklós Beér
Author: Sashi Kanta Panigrahi
Author: Kenneth C. Hall
Author: 
Author: Janós M. Beér
Author: Jushan Chin
Author: Dan Zhao
Author: United States. National Advisory Committee for Aeronautics