DOCSLIB.ORG

Durham E-Theses

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Durham E-Theses Durham E-Theses The Application of Non-Axisymmetric Endwall Contouring in a 1 Stage, Rotating Turbine SNEDDEN, GLEN,CAMPBELL How to cite: SNEDDEN, GLEN,CAMPBELL (2011) The Application of Non-Axisymmetric Endwall Contouring in a 1 Stage, Rotating Turbine, Durham theses, Durham University. Available at Durham E-Theses Online: http://etheses.dur.ac.uk/3343/ Use policy The full-text may be used and/or reproduced, and given to third parties in any format or medium, without prior permission or charge, for personal research or study, educational, or not-for-prot purposes provided that: • a full bibliographic reference is made to the original source • a link is made to the metadata record in Durham E-Theses • the full-text is not changed in any way The full-text must not be sold in any format or medium without the formal permission of the copyright holders. Please consult the full Durham E-Theses policy for further details. Academic Support Oce, Durham University, University Oce, Old Elvet, Durham DH1 3HP e-mail: [email protected] Tel: +44 0191 334 6107 http://etheses.dur.ac.uk 2 The Application of Non-Axisymmetric Endwall Contouring in a 1½ Stage, Rotating Turbine Glen Campbell Snedden A thesis presented for the degree of Doctor of Philosophy School of Engineering Durham University England 2011 ii The Application of Non-Axisymmetric Endwall Contouring in a 1½ Stage, Rotating Turbine Glen Campbell Snedden Submitted for the degree of Doctor of Philosophy 2011 Abstract Today gas turbines are a crucial part of the global power generation and aviation industries. Small improvements to the efficiencies of individual components within the gas flow path can, over time, lead to dramatic cost savings for the operator and at the same time improve on the amount of carbon dioxide gas emissions to the environment. One such technology is the reduction of secondary flow losses in individual blade rows within the compressor or turbine section of the gas turbine through the use of non-axisymmetric endwall contouring. By introducing subtle geometrical features onto the endwall it has been shown to be possible to improve the efficiency of individual blade rows by between 1 and 2%. Few studies of these non-axisymmetric endwalls have been performed outside of the two dimensional cascade and computational domain, in addition these endwalls have been designed and tested to improve the performance of blade rows at a single design point with the off design performance having been ignored. The work presented here is aimed at investigating the use of such endwalls in a rotating blade row both at design and off-design conditions and in the presence of an upstream blade row. To this end a 1½ stage, low speed, turbine test rig has been refurbished and a new set of blades was designed to accommodate the profile of the Durham cascade at the hub. The Durham cascade is a de facto industry test case for non-axisymmetric endwall applications and therefore a generic, cascade proven, endwall design is available from the literature. The design of this new blade set is unique in that it is openly available. The results include steady-state 5-hole pressure probe measurements between blade rows and computational fluid dynamics solutions to provide detailed analysis of the flow quality found within the turbine. These results are reproduced for a turbine with annular or reference endwalls and one with the generic P2 endwall design obtained from the Durham cascade. Experimentally a 1.5% improvement in mixed out stage efficiency at the design condition has been found with a positive trend with increasing load. Additionally the rotor exit flows are show to be generally more uniform in the presence of profiled endwalls. The rotor torque is however reduced by as much as 3.5% and the improved flow uniformity does not always translate into a improved performance in the downstream row. iii Insight into the overall performance and fluid mechanics of the generic non-axisymmetric endwall at a variety of load conditions has been gained and an analysis of the parameters commonly used in optimising these endwalls is discussed with Cske being clearly shown to be the superior parameter in this case. CFD evidence suggests that while the cross passage pressure gradient is reduced by endwall profiling the extent of the effect of the change in hub endwalls reaches as far as the tip. The mechanism by which the overall loss is reduced appears to be a through a change in the relative strengths of the suction and pressure side horseshoe vortices and through the delayed migration of the passage cross flow, this change the relationship of these two vortex structures; dispersing the vortex structures as they leave the row and reducing the potential for mixing losses downstream. iv “They hadn‟t dreamed, in the way that people usually used the word, but they‟d imagined a different world, and bent metal round it.” Terry Pratchett v Declaration The work in this thesis is based on research carried out at the Council for Scientific and Industrial Research (CSIR), South Africa by the author, while enrolled at the University of Durham. No part of this thesis has been submitted elsewhere for any other degree or qualification and it is all my own work unless referenced to the contrary in the text. Copyright © 2011 CSIR vi Acknowledgements The author would like to thank the following people and institutions for their contributions to the completion of this work: My supervisors Dr David Gregory-Smith and Dr Grant Ingram for their invaluable input and support in particular taking the time and trouble to travel out to South Africa during the course of this study. Dwain Dunn for willingly taking the role of research assistant, programming the data reduction software and performing the CFD runs. Thomas Roos for his expertise with NREC‟s design codes. Professor Jeffery Bindon and the University of KwaZulu Natal for willingly giving the CSIR the 1½ stage test rig and their assistance with it. Central University of Technology, and in particular Gerrie Booysen for providing the manufacturing technology that enabled this work, with skill and efficiency. Abacus Automation for the installation of the test rig control systems. Siemens Automation and Control for supplying the equipment at cost. The European Union and Project VITAL who by funding the parallel effort to look at unsteady measurements provided the author with the support and momentum required to make this thesis a reality. Rhulani Mathebula and the staff at Maintenance Services for their constant willingness to help with the refurbishment and maintenance of the test rig. Douggie van der Walt of ProMech Engineering also deserves thanks for his innovative solution to the traverse problem and providing us with a network of competent engineering services providers from his vast experience in the industry. The CSIR and the Department of Science and Technology for funding the effort and sustaining the funding long enough to make it possible to complete a PhD degree. For this I also owe a special thanks to Beeuwen Gerryts. Thomas Hildebrandt and the NUMECA Ingenieursburo for their software, friendship and assistance. Jonathan Bergh for challenging me when I needed it most. Finally I wish to thank Cynthia my wife and children Robert and Julia for their patience and love throughout the extended period of this study and the many hours that I could not spend with them. vii Contents Abstract ................................................................................................................................. ii Declaration ............................................................................................................................. v Acknowledgements .............................................................................................................. vi Contents .............................................................................................................................. vii List of Figures ...................................................................................................................... ix Nomenclature ..................................................................................................................... xiv 1 Introduction................................................................................................................... 1 2 Literature Review ......................................................................................................... 4 2.1 The development of gas turbines 4 2.2 Turbine endwall secondary flows 7 2.2.1 Main features of turbine endwall secondary flows 8 2.2.2 Other features of interest 10 2.3 Tip clearance flows 12 2.3.1 Effect of rotation on tip clearance flows 15 2.4 Methods of limiting the generation of endwall loss 15 2.4.1 Air injection or suction 15 2.4.2 Three-dimensional airfoil design 16 2.4.3 Endwall modifications 19 2.4.4 Combined approaches 25 2.5 Overview 26 3 Experimental Method ................................................................................................. 28 3.1 The 1½ stage test rig 28 3.1.1 Origins and refurbishment 28 3.2 General assembly 29 3.3 Instrumentation and control 30 3.3.1 Transducer Calibrations 30 3.3.2 Inlet measurement ring 32 3.3.3 Hot-film probe 33 3.3.4 Inlet turbulence intensity measurements 33 3.3.5 Control philosophy 34 3.4 Blade and Profiled Endwall Design 36 3.4.1 Design Constraints 36 3.4.2 Aerofoil design 36 3.4.3 Test conditions 39 3.4.4 Blade attachment design 40 3.4.5 Endwall
Load more

Recommended publications
  • Numerical Simulations of Unsteady, Multi-Phase Flows in Aero-Engine Like Combustors
    XX International Symposium on Air Breathing Engines 2011 (ISABE 2011) Gothenburg, Sweden 12-16 September 2011 Volume 1 of 3 ISBN: 978-1-61839-180-3 Printed from e-media with permission by: Curran Associates, Inc. 57 Morehouse Lane Red Hook, NY 12571 Some format issues inherent in the e-media version may also appear in this print version. The contents of this work are copyrighted and additional reproduction in whole or in part are expressly prohibited without the prior written permission of the Publisher or copyright holder. The resale of the entire proceeding as received from CURRAN is permitted. For reprint permission, please contact AIAA’s Business Manager, Technical Papers. Contact by phone at 703-264-7500; fax at 703-264-7551 or by mail at 1801 Alexander Bell Drive, Reston, VA 20191, USA. TABLE OF CONTENTS Volume 1 Numerical Simulations of Unsteady, Multi-Phase Flows in Aero-Engine like Combustors ............................................1 Massimiliano Di Domenico, Patrick Le Clercq, Michael Rachner Effect of Internal Two-Phase Flow on Effervescent Sprays............................................................................................. 11 Hrishikesh Gadgil, B. N. Raghunandan Effect of Combustor Geometry on the Performance of an Airblast Atomizer under Sub-Atmospheric Conditions ............................................................................................................................................................................ 19 Ahad Mehdi, Vassilios Pachidis, Riti Singh, Pavlos Zachos, N. Grech
    [Show full text]
  • Turbine Geometry
    Durham E-Theses The Application of Non-Axisymmetric Endwall Contouring in a 1 Stage, Rotating Turbine SNEDDEN, GLEN,CAMPBELL How to cite: SNEDDEN, GLEN,CAMPBELL (2011) The Application of Non-Axisymmetric Endwall Contouring in a 1 Stage, Rotating Turbine, Durham theses, Durham University. Available at Durham E-Theses Online: http://etheses.dur.ac.uk/3343/ Use policy The full-text may be used and/or reproduced, and given to third parties in any format or medium, without prior permission or charge, for personal research or study, educational, or not-for-prot purposes provided that: • a full bibliographic reference is made to the original source • a link is made to the metadata record in Durham E-Theses • the full-text is not changed in any way The full-text must not be sold in any format or medium without the formal permission of the copyright holders. Please consult the full Durham E-Theses policy for further details. Academic Support Oce, Durham University, University Oce, Old Elvet, Durham DH1 3HP e-mail: [email protected] Tel: +44 0191 334 6107 http://etheses.dur.ac.uk 2 The Application of Non-Axisymmetric Endwall Contouring in a 1½ Stage, Rotating Turbine Glen Campbell Snedden A thesis presented for the degree of Doctor of Philosophy School of Engineering Durham University England 2011 ii The Application of Non-Axisymmetric Endwall Contouring in a 1½ Stage, Rotating Turbine Glen Campbell Snedden Submitted for the degree of Doctor of Philosophy 2011 Abstract Today gas turbines are a crucial part of the global power generation and aviation industries.
    [Show full text]
  • Activity Report from the Division of Combustion Physics 2009-2011
    Activity Report from the Division of Combustion Physics 2009-2011 Lund University Lund, Sweden Editor: Zhongshan Li LRCP-156 Lund Reports on Combustion Physics 2012 Lund Reports on Combustion Physics, LRCP-156 Division of Combustion Physics Lund University Box 118 SE-221 00 Lund Sweden Telephone + 46 (0) 46 222 1422 Fax + 46 (0) 46 222 4542 WWW http://www.forbrf.lth.se Printed at Media-Tryck, Lund, Sweden 2012 Cover illustration: Simultaneous visualization of four species, OH, CH, CH2O and toluene, in a jet flame by PLIF technique. Left: OH (red) and CH (green); middle: CH2O (red) and CH (green); right: CH2O (red) and toluene (green). TABLE OF CONTENTS 1 INTRODUCTION .................................................................................................................................. 1 2 GENERAL INFORMATION................................................................................................................ 3 2.1 STAFF ........................................................................................................................................................ 3 2.2 VISITORS ................................................................................................................................................... 4 2.3 ACADEMIC DEGREES DURING 2009-2011 ................................................................................................. 4 2.4 SEMINARS ................................................................................................................................................
    [Show full text]
  • I GRADUATION PROJECT JULY, 2020 COMPUTATION of DESING
    ISTANBUL TECHNICAL UNIVERSITY FACULTY OF AERONAUTICS AND ASTRONAUTICS COMPUTATION OF DESING LOADS ASSOCIATED WITH ENGİNE SURGE FOR A SUPERSONIC AIRCRAFT GRADUATION PROJECT Elif YILDIRIM Department of Aeronautical Engineering ThesisAnabilim Advisor Dalı: Prof. : He Dr.rhangi Melike Mühendislik, NİKBAY Bilim Programı : Herhangi Program JULY, 2020 i ISTANBUL TECHNICAL UNIVERSITY FACULTY OF AERONAUTICS AND ASTRONAUTICS COMPUTATION OF DESING LOADS ASSOCIATED WITH ENGİNE SURGE FOR A SUPERSONIC AIRCRAFT GRADUATION PROJECT Elif YILDIRIM (110170601) Department of Aeronautıcal Engineering Thesis Advisor: Prof. Dr. Melike NİKBAY Anabilim Dalı : Herhangi Mühendislik, Bilim Programı : Herhangi Program JULY, 2020 ii Elif Yıldırım, student of ITU Faculty of Aeronautics and Astronautics student ID 110170601, successfully defended the graduation entitled COMPUTATION OF DESING LOADS ASSOCIATED WITH ENGİNE SURGE FOR A SUPERSONIC AIRCRAFT”, which she prepared after fulfilling the requirements specified in the associated legislations, before the jury whose signatures are below. Thesis Advisor : Prof. Dr. Melike NİKBAY .............................. İstanbul Technical University jury Members : Doç. Dr. Ayşe Gül GÜNGÖR ............................. İstanbul Technical University Doç. Öğr. Üyesi Kemal Bülent YÜCEİL .............................. İstanbul Technical University Date of Submission : 13 July 2020 Date of Defense : 23 July 2020 iii To my family, iv FOREWORD I would like to thank my advisor Prof. Dr. Melike NİKBAY for her support and kindness during the preparation process of this thesis. I would also like to thank my advisor in TUSAŞ, Ali Han YILDIRIM, who did not withhold his help and patiently answered every question I asked during my internship and preparation of my project. Special thanks for my dear friends Kübra TEZCAN and Gamze ÖZEN for their wonderful frienship and support throughout my university life.
    [Show full text]
  • Publishable Final Activity Report Page 1
    THE SIXTH FRAMEWORK PROGRAMME Priority 4: Aeronautic and Space, Call FP6-2005-Aero-1 RTD-Project: - HEATTOP – Contract no. AST5-CT-2006- 030696 Publishable Final Activity Report page 1 Project title: “Accurate High Temperature Engine Aero-Thermal Measurements for Gas-Turbine Life Optimization, Performance and Condition Monitoring” Project acronym: “HEATTOP” Contract number: AST5-CT-2006- 030696 Type of Instrument: STREP Publishable Final Activity Report Period covered: from August 01, 2006 to April 30, 2010 Issuing date: July 30, 2010 Start date of project: August 01, 2006 Duration: 45 months List of contractors: No Role Country Partner name Acronym 1 Coordinator, Germany Siemens SIE WP Lead 2 WP Lead U.K. Rolls Royce R-R 3 WP Lead Sweden Volvo Aero VAC 4 Switzerland Vibro-Meter CH VM-CH 5 U.K Vibro-Meter UK VM-UK 6 WP Lead Netherlands KEMA KEMA 7 Italy CESI RICERCA CESI-R 8 Ireland Farran FARR 9 WP Lead Belgium Von-Karman Institute for Fluid Dynamics VKI 10 U.K. Oxsensis OXS 11 Germany Advanced Optical Solutions AOS 12 France Auxitrol AUX 13 Germany Institute of Photonic Technology IPHT 14 U.K. Univ. Cambridge (2 depts : MAT & DENG) UCAM 15 Sweden Univ. Lund ULUND 16 France Onera ONERA 17 U.K. Univ. Oxford UOXF Project coordinator: Patrick R. Flohr Siemens AG, Energy Sector, Fossil Power Generation Coordinator email: [email protected], Telephone: +49-208-456-4757 Fax: +49-208-456-2773 Document name: HEATTOP Publishable Final Activity Report_6.doc Authors: Patrick Flohr & All Contractors THE SIXTH FRAMEWORK PROGRAMME Priority 4: Aeronautic and Space, Call FP6-2005-Aero-1 RTD-Project: - HEATTOP – Contract no.
    [Show full text]
  • Development of High Temperature Cooled and Uncooled Fast Response Probes for Gas Turbine Applications
    DEVELOPMENT OF HIGH TEMPERATURE COOLED AND UNCOOLED FAST RESPONSE PROBES FOR GAS TURBINE APPLICATIONS Mehmet Mersinligil, Turkey Supervisor: Associate Prof. J-F. Brouckaert Promoters: Prof. M. Papalexandris (UCL, Belgium) and Prof. T. Arts (VKI-UCL, Belgium) Accurate hot gas path measurements (including combustion diagnostics) are recognized as a major need for the assessment of engine component health and performance. Regarding unsteady pressure measurements above temperatures of 1300K (~1000°C), little, if any, accurate and reliable technique exists to measure the time- resolved gas path total pressure. Among various approaches to create a solution to this problem, cooling of a standard off-the-shelf sensor is found to be the most feasible solution. The design of a pressure probe and its cooling system constructs the basis of this study. Emphasize is given on heat transfer and aerodynamics around the probe. Following the manufacturing of the cooled probe designed, it has been tested in Rolls-Royce Viper Mk201 turbojet engine (aft of the turbine disc), and at Rolls-Royce Intermediate Pressure Combustion Rig at high temperatures. A second prototype has been built with several improvements and tested in a Volvo Aero RM-12 low bypass military turbofan engine (aft of the LP Turbine rotor). The probe is water cooled by a high pressure cooling system and uses a conventional piezo-resistive pressure sensor which yields therefore both time-averaged and time-resolved pressures. The initial design target was to gain the capability of performing measurements at the temperature conditions typically found at high pressure turbine exit (1100-1400K) with a bandwidth of at least 40kHz and in the long term at combustor exit (2000K or higher).
    [Show full text]
  • III/2014 Saab in Super Mode at the Crossroads Depleting Air Assets Life Beyond LCA IOC Powering the Future Helicopter Modernisa
    III/2014 Saab in Super Mode Life beyond LCA IOC At the Crossroads Powering the Future Depleting Air Assets Helicopter Modernisation Dassault III/2014 III/2014 At the Crossroads Angad Singh traces Saab’s Helicopter 35 Air Marshal Brijesh D Jayal writes success story, with 66 years 80 separating the J-29 of 1948 and Modernisation that there is a choice for Indian With rising prices and shrinking Aeronautics between ‘Reveille the Gripen E of 2014, history in motion ! defence budgets, armed forces and the Last Post’, referring to are looking at alternatives to reports that HAL and the IAF induction of new equipment. Saab in Super Mode Life beyond LCA IOC have worked out joint plans Vijay Matheswaran reviews cost At the Crossroads Powering the Future to deal with military aircraft Depleting Air Assets Helicopter Modernisation effective solutions for operators projects that are underway in of military rotorcraft. the country. New Generation Gripen (photo courtesy Saab) EDITORIAL PANEL MANAGING EDITOR Vikramjit Singh Chopra 70 Lessons from EDITORIAL ADVISOR the Kaveri Admiral Arun Prakash Professor Prodyut Das makes an ‘open source’ assessment of EDITORIAL PANEL Depleting Air Assets the Kaveri engine and attributes 102 A Manner of Pushpindar Singh 44 Considering the declining IAF failures to leadership which is actually, the failure of knowledge. Numbers Air Marshal Brijesh Jayal fighter aircraft strength, Air No.5 Squadron (‘Tuskers’) of the In rebooting the mindset, he Dr. Manoj Joshi Marshal Anil Chopra urges that Indian Air Force are amongst makes some practical suggestions it is ‘Time For Full Throttle’. Fast those formations which are Lt.
    [Show full text]
  • Vayu Issue III May Jun 2016
    III/2016 Aerospace & Defence Review Enter the Gripen E Dream Aircraft Carrier Iron Fist 2016 Red Star over Syria Defexpo 2016 review Hinds of the Hindu Kush Meeting your operational needs is our mission IAI Lahav IAI – your one-stop address for helicopter avionics and upgrades • Modular integrated avionics packages tailored to meet operational requirements • Optimized integration of advanced mission equipment and sensors • Mission-driven displays and controls for enhanced air crew performance and safety • Comprehensive helicopter support www.iai.co.il [email protected] III/2016 III/2016 Aerospace & Defence Review “Weapons … On briefings during the event, some of that such a ‘Gnat Redux’ could well go 42 which briefly appeared in the Special into service within 6-7 years, and all that Target …. On Time !” Show Dailies issued by Vayu on the first is needed is ‘faith’! three days of Defexpo 2016. 95 Red Star over Syria 73 Dream Aircraft Enter the Gripen E Dream Aircraft Carrier Carrier : Will it Iron Fist 2016 Red Star over Syria Defexpo 2016 review Hinds of the Hindu Kush ever be built ? Cover: Saab’s next generation Gripen E fighter, which was rolled out on 18 May 2016 This special Vayu-on-the-spot (photo: Saab) report by Angad Singh covers the Iron Fist firepower demonstration at EDITORIAL PANEL the Pokhran range in Rajasthan, the mammoth day-night event featuring At the tip of Russia’s designs for MANAGING EDITOR over 180 IAF aircraft, ranging from domination in Syria is the might of the transports and UAVs to fighters and Vikramjit Singh Chopra Vice Admiral Subhash Chopra, one resurgent Russian Air and Space Forces.
    [Show full text]
  • Encyclopédie Aéronautique Électronique
    Encyclopédie aéronautique électronique AviationsMilitaires.net 10 août 2010 Ce livre électronique est régulièrement mis à jour, et est le fruit de la collaboration de nombreuses personnes. Édition actuelle : 10 août 2010. 2 Table des matières 3 4 Première partie Avions et hélicoptères 5 Chapitre 1 Avions de combat 1.1 Aerospace Industrial De- également de CDVE à triple redondance conçus par velopment Corp BAe Systems, d'un système de navigation inertielle Honeywell H423, de deux écrans multi-fonctions Bendix, d'un afficheur tête haute Elbit, d'un HO- 1.1.1 AIDC F-CK-1 Ching-Kuo TAS. Premier vol : 28 mai 1989 Enfin, le programme autour de l'armement, prin- Rôle : Chasse, Attaque au sol, Lutte anti-navires cipalement les missiles, fut nommé Tien Chien (épée du ciel). Il aboutit à deux missiles, les Tien Constructeur : AIDC (Taïwan) Chien I à courte portée (5 km) et à guidage in- A la fin des années 1970, les Etats-Unis se rap- frarouge, dérivé de l'AIM-9L Sidewinder, et les Tien prochèrent de la Chine continentale, délaissant Chen II, à moyenne portée (60 km) à guidage radar Taïwan et stoppant les livraisons d'armes. C'est et extrapolé de l'AIM-120 AMRAAM. Ils furent es- ainsi que Tchang Ching-Kuo, le fils de Tchang Kaï- sayés respectivement en 1992 et 1994. Il peut aussi Chek, chargea AIDC (Aerospace Industrial Devel- emporter 3 missiles antinavires Hsuing-Feng II ou opment Corp) de concevoir un appareil s'affran- des missiles AGM-65 Maverick. chissant de la tutelle américaine, et destiné à rem- Le prototype monoplace 77-8001 sorti d'usine le placer ses F-5 et F-104.
    [Show full text]
  • XX International Symposium ... ; Vol. 1
    XX International Symposium on Air Breathing Engines 2011 (ISABE 2011) Gothenburg, Sweden 12-16 September 2011 Volume 1 of 3 ISBN: 978-1-61839-180-3 TABLE OF CONTENTS Volume 1 Numerical Simulations of Unsteady, Multi-Phase Flows in Aero-Engine like Combustors 1 Massimiliano Di Domenico, Patrick Le Clercq, Michael Rachner Effect of Internal Two-Phase Flow on Effervescent Sprays 11 Hrishikesh Gadgil, B. N. Raghunandan Effect of Combustor Geometry on the Performance of an Airblast Atomizer under Sub-Atmospheric Conditions 19 Ahad Mehdi, Vassilios Pachidis, Riti Singh, Pavlos Zachos, N. Grech Numerical Investigation of Reacting Spray in a Lean Direct Injection Combustor 26 Dipanjay Dewanji, Mathieu Powquie, Arvind G. Rao, J. P. Van Buijtenen Investigations of a Combustor Using a 9-Point Swirl-Venturi Fuel Injector: Recent Experimental Results 38 Robert C. Anderson, Christopher M. Heath, Yolanda R. Hicks, Kathleen M. Tacina Development of a Lean Direct Injection Fuel Nozzle for Small Aircraft Engines 48 Atsushi Horikawa, Masayoshi Kobayashi, Takeo Oda, Hideki Ogata Assessment and Improvement of Engineering Simulation for Multiphase Turbulent Combustion in a Lean Direct Injection Combustor 55 Nan-Suey Liu Numerical Simulation and Validation of a Spray Combustion Field in a Scaled Sector Model for a Jet Engine Combustor 66 FumiteruAkamatsu, Satoru Komori, Ryoichi Kurose, Hideki Moriai V-Gutter Stabilized Turbulent Premixed Flame and Lean Blowout 71 Alejandro Briones, Balu Sekar, Hugh Thornburg, K. Granlund Modeling of a Premixed Propane Flame behind a Triangular Bluff Body Using S AS-SST Model and an Optimized Two-Step Global Reaction Mechanism 83 Lars-Erik Eriksson, Bernhard Gustafsson, ErikR.
    [Show full text]
  • Studiu Despre Volvo Aero Company Si Motoarele Sale
    STEM Educational Lab Studiu despre Volvo Aero Company si motoarele sale Chiorean Răzvan Published on: Jan 24, 2021 License: Creative Commons Attribution 4.0 International License (CC-BY 4.0) STEM Educational Lab Studiu despre Volvo Aero Company si motoarele sale VOLVO AERO COMPANY SI MOTOARELE SALE Răzvan-Nicolae CHIOREAN Academia Fortelor Aeriene ,,Henri Coanda” Brasov Abstract: O aeronava are nevoie de energie mecanica pentru a fi propulsata, aceasta energie este obtinuta in urma arderilor interne dintr-un motor de aviatie. Acest articol ofera o perspectiva generala referindu-se la caracteristicile motoarelor de aviatie produse de catre compania Volvo Aero. Prima parte cuprinde o scurta introducere in ceea ce inseamna aceasta companie si o mica parte din istoria sa. A doua parte consta in prezentarea generala a patru motoare de aviatie construite de catre Volvo Aero, fiind urmata de catre un tabel ce contine specificatiile fiecarui motor in parte. +. INTRODUCERE SI ISTORIE Volvo Aero a fost o companie specializata in motoare de aviatie, rachete si avioane. In urma cumpararii companiei de catre compania engleza GKN, numele companiei a devenit GKN Aerospace Engine Systems. Inițial a fost înființată ca Nohab Flygmotorfabriker AB în 1930 pentru a produce motoare aero. Firma a devenit parte din SAAB în 1937. Ulterior, Volvo a achiziționat o mare parte din stoc, astfel schimbandu-si numele in Svenska Flygmotor AB (SFA) iar mai târziu Volvo Flygmotor. A devenit principalul furnizor de motoare al Forțelor Aeriene Suedeze în perioada postbelică. În anii ’70, Volvo Flygmotor s-a încadrat în sectorul aerospațial comercial, oferind revizii și producție de subcomponente pentru mai mulți producători internaționali de motoare, precum și în sectorul spațial european.
    [Show full text]
  • 01 Warbirds Ii Prelims
    International Warbirds ✪ International Warbirds ✪ An Illustrated Guide to World Military Aircraft, 1914–2000 BY JOHN C. FREDRIKSEN FOREWORD BY WALTER BOYNE B Santa Barbara, California Denver, Colorado Oxford, England Copyright © 2001 by John C. Fredriksen All rights reserved. No part of this publication may be reproduced, stored in a retrieval system, or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, except for the inclusion of brief quotations in a review, without prior permission in writing from the publishers. Library of Congress Cataloging-in-Publication Data Fredriksen, John C. International warbirds : an illustrated guide to world military aircraft, 1914–2000 / by John C. Fredriksen. p. cm. Includes bibliographical references. ISBN 1-57607-364-5 (hardcover : alk. paper) — ISBN 1-57607-551-6 (e-book) 1. Airplanes, Military—Dictionaries. I. Title. UG1240.F74 2001 623.7'46—dc21 2001002280 06050403020110987654321 This book is also available on the World Wide Web as an e-book. Visit abc-clio.com for details. ABC-CLIO, Inc. 130 Cremona Drive, P.O. Box 1911 Santa Barbara, California 93116–1911 This book is printed on acid-free paper I. Manufactured in the United States of America C ONTENTS List of Aircraft by Era and Country of Manufacture ix Foreword, by Walter Boyne xiii Introduction xv AEG C IV 1 Avro Lancaster 37 Dassault Mirage 2000 78 AEG G IV 2 Avro Shackleton 38 Dassault Mirage F 1 79 Aermacchi MB 339 3 Avro Vulcan 39 Dassault Mirage III 80 Aero L 29 Delfin 4 Avro Canada CF
    [Show full text]