DOCSLIB.ORG

Cranfield University Michael J Sefain Hydrogen Aircraft

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Cranfield University Michael J Sefain Hydrogen Aircraft CRANFIELD UNIVERSITY MICHAEL J SEFAIN HYDROGEN AIRCRAFT CONCEPTS & GROUND SUPPORT SCHOOL OF ENGINEERING PhD CRANFIELD UNIVERSITY SCHOOL OF ENGINEERING Aerospace Vehicle Design PhD THESIS Academic Year 2000 MICHAEL J SEFAIN HYDROGEN AIRCRAFT CONCEPTS & GROUND SUPPORT Supervisor: Dr. R. I. Jones November 2005 ©Cranfield University, 2006. All rights reserved. No part of this publication may be reproduced without the written permission of the copyright holder. 2 ABSTRACT As worldwide petroleum supplies diminish and prices escalate, the aviation industry will be forced to consider relying on energy resources other than kerosene for its aviation fuel needs. Additionally, there is growing environmental concern regarding greenhouse emissions particularly as aircraft cause pollution in sensitive layers of the atmosphere. These are serious implications necessitating prudence in seeking alternative fuels sooner rather than later. Liquid Hydrogen (LH2) combustion produces zero CO2 emissions, very little NOx, and water providing a solution to sustain air traffic growth whilst preventing further atmospheric pollution. Hydrogen itself is abundant and can be produced from renewable sources meaning worldwide availability and sustainability permitting sustainable growth of aviation at high rates (typically 4-5% per year). Despite these major advantages, there are compromises to be made. The low density fuel means ingenuity must be exercised to design an aircraft configuration which will accommodate a fuel volume more than four times that which would normally be required. Practical unconventional aircraft conceptual designs providing solutions to this problem are presented including estimates of performance, mass, and relative cost- and energy-effectiveness. To provide a means to produce, store and transport the fuel safely and efficiently, ground support operations have been systematically checked and the required airport infrastructure defined. Technical issues such as safety, airworthiness certification, environmental issues and system synergies are also discussed, and an outline plan is presented providing the R&D necessary to introduce LH2-fuelled civil aircraft into service. This Thesis proves that LH2 has sufficient long term promise to justify more substantial R&D offering possible improvement in performance and engine 3 reliability. The overall cost for a LH2 aircraft are within reasonable values, and the requirement for new equipment to maintain and support LH2-fuelled aircraft is not extensive. Importantly LH2 is at least as safe. 4 Acknowledgements I am indebted to my supervisor Dr. Robert Jones who provided me with excellent support, advice, suggestions and invaluable information on a continuous basis throughout and without whom, this study would not have been possible. I would also like to express my sincere appreciation to Professor J.P. Fielding, and Professor D Howe who also took a lot of time out of their very busy schedules to contribute to this work providing me with invaluable advice that only years of experience and expertise could have provided. I would also like to express my gratitude to the staff and students at the College of Aeronautics (now part of the School of Engineering) for their continual support. I also acknowledge the support given to me by my family and friends who have provided an endless source of encouragement. Above all my thanks must go to God without Whom nothing is possible. 5 CONTENTS ABSTRACT ............................................................................................................... 3 Acknowledgements .................................................................................................... 5 CONTENTS............................................................................................................... 6 List of Figures .......................................................................................................... 10 List of Tables............................................................................................................ 13 ABBREVIATIONS/NOMENCLATURE ............................................................... 17 Preface...................................................................................................................... 23 1.0 SCOPE OF THESIS..................................................................................... 24 1.1 Thesis Chapter Content .........................................................................24 2.0 HYDROGEN FUEL..................................................................................... 26 2.1 Introduction...........................................................................................26 2.2 Background...........................................................................................26 2.2.1 Renewable Energy.............................................................................26 2.2.2 Environmental and Greenhouse Effect...............................................27 2.2.3 Candidate fuels..................................................................................29 2.2.4 Characteristics of Hydrogen fuel .......................................................30 2.2.4.1 Advantages of hydrogen.................................................................33 2.2.4.2 Disadvantages of hydrogen............................................................34 2.2.4.3 Summary of LH2 characteristics and effects on aircraft design.......35 2.3 Objectives .............................................................................................37 3.0 UNCONVENTIONAL AIRCRAFT DESIGN ............................................ 40 3.1 Development of passenger jet configurations – Challenges faced by designers ..........................................................................................................40 3.2 What drives a unique configuration?.....................................................41 3.2.1 Very Large Aircraft .......................................................................42 3.2.2 Multi-Body Concept.......................................................................43 3.2.3 Oblique wing .................................................................................46 3.2.4 Transonic biplane..........................................................................47 3.2.5 Joined Wing...................................................................................49 3.2.6 Multirole Global Range Transport.................................................50 3.2.7 Forward Swept Wing and application in high aspect ratio aircraft configurations...............................................................................................51 3.3 Aircraft Configuration Design...............................................................51 3.3.1 Brainstorming................................................................................52 3.3.2 Results of Brainstorming Session – Configurations........................55 3.3.3 Configuration assessment ..............................................................63 3.3.4 Design attributes ...........................................................................64 3.3.5 Final concepts ...............................................................................66 6 3.4 Conceptual Design ................................................................................69 3.4.1 Medium-Range Aircraft Specification (JAR/FAR 25) ....................69 3.4.2 Twin-Boom Conceptual design......................................................72 3.5 Results................................................................................................. 122 3.6 Configuration description....................................................................131 3.6.1 Fuselage Layout ..........................................................................131 3.6.2 Wing and Tail layout ...................................................................132 3.6.3 Mass and balance........................................................................134 3.6.4 Lift and Drag...............................................................................137 3.6.5 Powerplant and Installation.........................................................138 3.6.6 Performance................................................................................139 3.6.7 Fuel Tank Structure .....................................................................139 3.6.8 LH2-fuel tank pylon structure (twin boom) ...................................143 3.6.9 Safety...........................................................................................144 4.0 HYDROGEN SAFETY.............................................................................. 146 4.1 Characteristics of Liquid Hydrogen.....................................................147 4.2 Risks related to low temperatures ........................................................148 4.3 Phenomena associated with combustion ..............................................149 4.3.1 Danger zones of spilled liquid gases ............................................149 4.4 Specific hydrogen hazards...................................................................150 4.5 Infrastructure-specific safety aspects...................................................152 4.5.1 Hydrogen production methods .....................................................152 4.5.2 Hydrogen liquefaction ................................................................. 152 4.5.3
Load more

Recommended publications
  • A Study of Transport Airplane Crash Resistant
    DOT/FAA/AR-01/76 A Study of Helicopter Crash- Office of Aviation Research Washington, D.C. 20591 Resistant Fuel Systems February 2002 Final Report This document is available to the U.S. public through the National Technical Information Service (NTIS), Springfield, Virginia 22161. U.S. Department of Transportation Federal Aviation Administration NOTICE This document is disseminated under the sponsorship of the U.S. Department of Transportation in the interest of information exchange. The United States Government assumes no liability for the contents or use thereof. The United States Government does not endorse products or manufacturers. Trade or manufacturer's names appear herein solely because they are considered essential to the objective of this report. This document does not constitute FAA certification policy. Consult your local FAA aircraft certification office as to its use. This report is available at the Federal Aviation Administration William J. Hughes Technical Center's Full-Text Technical Reports page: actlibrary.tc.faa.gov in Adobe Acrobat portable document format (PDF). Technical Report Documentation Page 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. DOT/FAA/AR-01/76 4. Title and Subtitle 5. Report Date A STUDY OF HELICOPTER CRASH-RESISTANT FUEL SYSTEMS February 2002 6. Performing Organization Code 7. Author(s) 8. Performing Organization Report No. S.H. Robertson, N.B. Johnson, D.S. Hall and I.J. Rimson RA-FAA-01-130 9. Performing Organization Name and Address 10. Work Unit No. (TRAIS) Robertson Aviation, L.L.C. 1024 East Vista Del Cerro Drive Tempe, AZ 85281 11. Contract or Grant No.
    [Show full text]
  • Afsc 2A6x4 Career Field Education and Training Plan
    DEPARTMENT OF THE AIR FORCE CFETP 2A6X4 Headquarters US Air Force Parts I and II Washington, DC 20330-1030 APRIL 1999 AFSC 2A6X4 AIRCRAFT FUEL SYSTEMS CAREER FIELD EDUCATION AND TRAINING PLAN CAREER FIELD EDUCATION AND TRAINING PLAN AIRCRAFT FUEL SYSTEMS SPECIALTY AFSC 2A6X4 Table of Contents PART I Preface......................................................................................................................................... 2 Abbreviations/Terms Explained.................................................................................................. 3 Section A--General Information..................................................................................................5 Purpose of the CFETP Use of the CFETP Coordination and Approval of the CFETP Section B--Career Progression and Information ......................................................................... 6 Specialty Description Skill/Career Progression Apprentice Level (3) Journeyman Level (5) Craftsman Level (7) Superintendent Level (9) Training Decisions Community College of the Air Force Career Field Path Section C--Skill Level Training Requirements........................................................................... 12 Purpose Training Requirements Apprentice Level (3) Journeyman Level (5) Craftsman Level (7) Superintendent Level (9) Section D--Resource Constraints ................................................................................................ 14 Section E--Transitional Training Guide.....................................................................................
    [Show full text]
  • Subject: FUEL TANK IGNITION SOURCE PREVENTION
    Subject: FUEL TANK IGNITION Date: 9/19/08 AC No: 25.981-1C SOURCE PREVENTION GUIDELINES Initiated By: ANM-112 1. Purpose. This advisory circular (AC) provides guidance for demonstrating compliance with the certification requirements for prevention of ignition sources within the fuel tanks of transport category airplanes. This guidance is applicable to transport category airplanes for which a new, amended, or supplemental type certificate is requested. 2. Applicability. a. The guidance provided in this document is directed to airplane manufacturers, modifiers, foreign regulatory authorities, and Federal Aviation Administration (FAA) transport airplane type certification engineers, and their designees. b. This material is neither mandatory nor regulatory in nature and does not constitute a regulation. It describes acceptable means, but not the only means, for demonstrating compliance with the applicable regulations. The FAA will consider other methods of demonstrating compliance that an applicant may elect to present. While these guidelines are not mandatory, they are derived from extensive FAA and industry experience in determining compliance with the relevant regulations. On the other hand, if we become aware of circumstances that convince us that following this AC would not result in compliance with the applicable regulations, we will not be bound by the terms of this AC, and we may require additional substantiation or design changes as a basis for finding compliance. c. This material does not change, create any additional, authorize changes in, or permit deviations from, regulatory requirements. 3. Cancellation. Advisory Circular 25.981-1B, Fuel Tank Ignition Source Prevention Guidelines, dated April 18, 2001, is cancelled. 4. Related Documents.
    [Show full text]
  • Sealant Joints in Aircraft Integral Fuel Tanks Aerospace Engineering
    a a Sealant Joints in Aircraft Integral Fuel Tanks João Pedro Róis Policarpo Thesis to obtain the Master of Science Degree in Aerospace Engineering Supervisor: Prof. Luís Filipe Galrão dos Reis Examination Committee Chairperson: Prof. Fernando José Parracho Lau Supervisor: Prof. Luís Filipe Galrão dos Reis Members of the Committee: Prof. Filipe Szolnoky Ramos Pinto Cunha Eng. Marco Frederico Espanhol November 2014 Acknowledgements I would like to express my gratitude to my Professor Luis Reis and my supervisor Engineer Marco Espanhol for their valuable advice, encouragement and availability throughout this research. I also would like to thank Engineers Carlos Rodrigues and Andreia Mendonça for their important input and time serving as well as valuable advice in performing experimental work. A special thanks to all my friends and teachers who directly or indirectly contributed towards this study. Above all, my sincere gratitude to my parents, family and my girlfriend for their encouragement, support, patience and love that arouses me each day to continue my investigation. i ii Abstract Leaks arising from aircraft fuel tanks have constantly represented a problem for aircraft manufacturers, operators and maintenance crews. The integral fuel tanks within aircraft structures are in general located within the wings and they rely on sealant materials to prevent leakage through joints and fasteners. However, aircraft integral fuel tanks are designed from a structural point of view first and as a fuel tank second. There are numerous potential leak paths for the fuel on these complex wing structures. The overall aim of the current research was to reduce the fuel leaks in the aircraft fuel tanks at the delivery.
    [Show full text]
  • Aircraft Fuel Systems
    Aircraft Fuel Systems Aerospace Series List The Global Airline Industry Belobaba April 2009 Computational Modelling and Simulation of Diston April 2009 Aircraft and the Environment, Volume 1: Platform Kinematics and Synthetic Environment Aircraft Performance Theory and Practice for Pilots Swatton August 2008 Aircraft Systems, 3rd Edition Moir & Seabridge March 2008 Introduction to Aircraft Aeroelasticity and Loads Wright & Cooper December 2007 Stability and Control of Aircraft Systems Langton September 2006 Military Avionics Systems Moir & Seabridge February 2006 Design and Development of Aircraft Systems Moir & Seabridge June 2004 Aircraft Loading and Structural Layout Howe May 2004 Aircraft Display Systems Jukes December 2003 Civil Avionics Systems Moir & Seabridge December 2002 Aircraft Fuel Systems Roy Langton Retired Group VP Engineering, Parker Aerospace, USA Chuck Clark Retired Marketing Manager, Air & Fuel Division, Parker Aerospace, USA Martin Hewitt Retired Director of Marketing, Electronic Systems Division, Parker Aerospace, USA Lonnie Richards Senior Expert, Fuel Systems, Airbus UK, Filton, UK A John Wiley and Sons, Ltd, Publication This edition first published 2009 © 2009 John Wiley & Sons, Ltd Registered office John Wiley & Sons Ltd, The Atrium, Southern Gate, Chichester, West Sussex, PO19 8SQ, United Kingdom For details of our global editorial offices, for customer services and for information about how to apply for permission to reuse the copyright material in this book please see our website at www.wiley.com. The right of the author to be identified as the author of this work has been asserted in accordance with the Copyright, Designs and Patents Act 1988. 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 as permitted by the UK Copyright, Designs and Patents Act 1988, without the prior permission of the publisher.
    [Show full text]
  • Ac 25.981-2A
    Advisory U.S. Department of Transportation Federal Aviation Administration Circular Subject: FUEL TANK FLAMMABILITY Date: 9/19/08 AC No. 25.981-2A REDUCTION MEANS Initiated by: ANM-112 1. Purpose. This advisory circular (AC) provides information and guidance on compliance with the airworthiness standards for transport category airplanes about limiting the time a fuel tank may be flammable or mitigation of hazards from flammable fuel air mixtures within fuel tanks. This guidance is applicable to transport category airplanes for which a new, amended, or supplemental type certificate is requested, and for which Amendment 25-125 applies. It is also applicable to certain existing design approval holders and certain pending applications for new type certificates, supplemental type certificates and amended type certificates where required by §§ 26.33, 26.35, 26.37, and 26.39, contained in a subpart D to Title 14, Code of Federal Regulations (CFR) part 26, “Fuel Tank Flammability.” Guidance on compliance with the associated requirements for operators of affected airplanes that must comply with requirements in 14 CFR parts 121, 125 and 129, to incorporate flammability reduction or ignition mitigation means by specified dates, will be contained in a separate document. 2. Applicability. a. This guidance provided in this document is for design approval applicants and holders, airplane manufacturers, modifiers, foreign regulatory authorities, and Federal Aviation Administration (FAA) transport category airplane type certification engineers and their designees. b. This material is neither mandatory nor regulatory in nature and does not constitute a regulation. It describes acceptable means, but not the only means, for demonstrating compliance with the applicable regulations.
    [Show full text]
  • Fuel Contamination on the Large Transport Airplanes Behbahani-Pour MJ* and Radice G Department of Aerospace Engineering, Glasgow University, G12 8QQ, UK
    cs & Aero ti sp au a n c o e r E Behbahani-Pour and Radice, J Aeronaut Aerospace Eng 2017, 6:4 e n A g f i o n Journal of Aeronautics & Aerospace DOI: 10.4172/2168-9792.1000200 l e a e r n i r n u g o J Engineering ISSN: 2168-9792 Review Article Open Access Fuel Contamination on the Large Transport Airplanes Behbahani-Pour MJ* and Radice G Department of Aerospace Engineering, Glasgow University, G12 8QQ, UK Abstract There have been different cases of aircraft accidents, due to the water contamination in the aviation fuel. Since large transport airplanes fly at very high altitudes, where ambient temperature can reach -6°C, water may freeze causing blockages in the fuel lines, filters, booster pumps, etc., and lead to engine thrust reduction and or engine shut down. Microbiological contamination of the fuel, due to microbial growth in the fuel, it can result in fuel tank structure corrosion, and in turn, leads to fuel leak. Fuel leak on hot engine surfaces or hot brakes can result into fire or explosion. In addition, the biological microorganisms in aviation fuel, can cause other technical problems such as it leads to fuel quantity gauge malfunctions, and fuel filter clogging. Therefore, it is important to eliminate or reduce the presence of the water and microbial growth in the in the fuel. The aim of this paper is to increase flight safety by minimizing the effect of water and biological contamination in the jet fuel. The proposed methodology, water contamination is eliminated by extracting water from fuel by using water/fuel separator and in addition, microbial contamination eliminated by uses the ultrasonic technology to destroy the bacteria in the fuel.
    [Show full text]
  • Electrical Ignition of Fuel-Air Mixture in Aircraft Fuel Tanks
    Jacek F. GIERAS1 University of Technology and Life Sciences, Bydgoszcz Electrical Ignition of Fuel-Air Mixture in Aircraft Fuel Tanks Abstract. The fuel system, electric equipment of fuel tank and wiring, fuel flammability, mechanisms of electrical ignition and possibility of explosion of fuel-air mixture as a result of arcing and/or static electricity in fuel tanks of commercial aircraft has been analyzed. Approximate equations for minimum ignition energy (MIE) in fuel tanks have been derived. Examples of explosions of fuel tanks include the air crash of Boeing 747-131 TWA 800 on June 17, 1996 and explosion of Boeing 727-200 at Bangalore Airport on May 4, 2006. Although probability of explosion of fuel in the wing tanks due the electric short circuit, arcing or static electricity is low, this problem should be always carefully considered in examinations of air crashes. Streszczenie. Przedstawiono analize ukladu paliwowego, wyposazenia elektrycznego i przewodow zbiornikow paliwa, zapalnosci paliwa, mechanizmow zaplonu elektrycznego oraz mozliwosci wybuchu mieszanki paliwo-powietrze na skutek luku elektrycznego lub ladunkow statycznych w samolotach pasazers- kich. Zostaly wyprowadzone zaleznosci do obliczen przyblizonych minimalnej energii zaplonu w zbiornikach paliwa. Do wybuchow zbiornikow paliwa doszlo podczas lotu Boeinga 747-131 TWA 800 17 czerwca, 1996 oraz podczas postoju Boeinga 727-200 na lotnisku w Bangalore 4 maja 2006. Cho- ciaz prawdopodobienstwo wybuchu oparow paliwa w zbiornikach paliwa na skutek zwarcia instalacji, luku elektrycznego czy tez ladunkow statycznych jest niskie, problem ten powinien byc zawsze dokladnie rozwazony podczas badan wypadkow lotniczych. (Zaplon elektryczny mieszanki paliwo-powietrze w zbiornikach paliwa samolotow) Keywords: aircraft, air-fuel mixture, electrical wiring, electrical equipment, explosion, fuel system, fuel tank Słowa kluczowe: samolot, mieszanka paliwo-powietrze, przewody elektryczne, wyposazenie elektryczne, wybuch, uklad paliwowy, zbiornika paliwa Introduction a wing fuel tank is shown in Fig.
    [Show full text]
  • TWA Flight 800 Fueling Information
    PB2000-910403 NTSB/AAR-00/03 DCA96MA070 NATIONAL TRANSPORTATION SAFETY BOARD WASHINGTON, D.C. 20594 AIRCRAFT ACCIDENT REPORT In-flight Breakup Over the Atlantic Ocean Trans World Airlines Flight 800 Boeing 747-131, N93119 Near East Moriches, New York July 17, 1996 6788G Aircraft Accident Report In-flight Breakup Over The Atlantic Ocean Trans World Airlines Flight 800 Boeing 747-131, N93119 Near East Moriches, New York July 17, 1996 NTSB/AAR-00/03 DCA96MA070 PB2000-910403 National Transportation Safety Board Notation 6788G 490 L’Enfant Plaza, S.W. Adopted August 23, 2000 Washington, D.C. 20594 National Transportation Safety Board. 2000. In-flight Breakup Over The Atlantic Ocean, Trans World Airlines Flight 800, Boeing 747-131, N93119, Near East Moriches, New York, July 17, 1996. Aircraft Accident Report NTSB/AAR-00/03. Washington, DC. Abstract: This report explains the accident involving Trans World Airlines, Inc. flight 800, which experienced an in-flight breakup and then crashed into the Atlantic Ocean near East Moriches, New York, on July 17, 1996. Safety issues in the report focus on fuel tank flammability, fuel tank ignition sources, design and certification standards, and the maintenance and aging of aircraft systems. Safety recommendations concerning these issues are addressed to the Federal Aviation Administration. The National Transportation Safety Board is an independent Federal agency dedicated to promoting aviation, railroad, highway, marine, pipeline, and hazardous materials safety. Established in 1967, the agency is mandated by Congress through the Independent Safety Board Act of 1974 to investigate transportation accidents, determine the probable causes of the accidents, issue safety recommendations, study transportation safety issues, and evaluate the safety effectiveness of government agencies involved in transportation.
    [Show full text]