Case Study the Sustainable and Green Engine
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Signature Redacted Department of Civil and Envirnmental Engineering, MIT Sloan School of Management May 11,2018
Next Generation Commercial Aircraft Engine Maintenance, Repair, and Overhaul Capacity Planning and Gap Analysis by Amanda J. Knight B. S. Mechanical Engineering, The University of Texas at Austin, 2006 M.S. Aerospace Engineering, The University of Southern California, 2011 Submitted to the MIT Sloan School of Management and the Department of Civil and Environmental Engineering in Partial Fulfillment of the Requirements for the Degrees of Master of Business Administration and Master of Science in Civil and Environmental Engineering In conjunction with the Leaders for Global Operations Program at the Massachusetts Institute of Technology June 2018 2018 Amanda J. Knight. All rights reserved. The author hereby grants MIT permission to reproduce and to distribute publicly paper and electronic copies of this thesis document in whole or in part in any medium now known or hereafter created. Signature of Author: Signature redacted Department of Civil and Envirnmental Engineering, MIT Sloan School of Management May 11,2018 Certified by: Signature redacted __ DI Roy Welsch, Thesis Supervisor Professor of Statistics and Engineering Systems Certified by: Signature redacted Dr. Daniel Wh The i Supervisor Senior Research ScientisU/Eyneritust Lecturer, IVVT Leaders for obal Operations Certified by: _____Signature redacted _ _ _ _ _ _ Dr. David Simchi-Levi, Thesis Supervisor Prof"or,9 C ppdEnvironmental Engineering Accepted by: Signature redacted____ Jesse H. Kroll Profesor of Civil and Environmental Engineering Chair, Graduate Program Committee Accepted by: Signature redacted MHro MASSACHUSETTS INSTITUTE ' M PM ManuraHerson OF TECHNOLOGY co Director, MBA Program, MIT Sloan School of Management JUN 0 7 2018 LIBRARIES This page has been intentionally left blank Page | 2 Next Generation Commercial Aircraft Engine Maintenance, Repair, and Overhaul Capacity Planning and Gap Analysis by Amanda J. -
It's No American Dream: Pratt & Whitney GTF Engine Now a Reality
A D D E N D U M It’s No American Dream: Pratt & Whitney GTF Engine Now a Reality... and chosen in Time's November issue one of "The 50 Best Inventions of the Year" In the August try-tasked capabilities. 2008 issue of Gear For those who can’t Technology, we ran recall how the GTF a story (“Gearbox works, here’s a piece Speed Reducer Helps lifted from the 2008 Fan Technology for Gear Technology arti- ‘Greener” Jet Fuel cle explaining—with Efficiency’) on the help from Robert Saia, then ongoing, extreme- Pratt & Whitney vice ly challenging and pro- president, next-gener- tracted development ation products—what of Pratt & Whitney’s makes it leading edge: geared turbofan (GTF) (What’s unique) jet engine. If success- is the addition of a ful, the engine would reduction gear box— provide a 20 percent or transmission sys- reduction in carbon tem—comprised of a emissions and fuel star gear system with burn and up to 50 per- five stationary gears. cent in general noise As Saia explains, the reduction. The targeted The long-awaited Pratt & Whitney GTF (PurePower PW1000G) jet gear box decouples the market and application engine is now a reality, with customer orders now in production (cour- fan from the turbine so for the engine was the tesy Pratt & Whitney). that each component narrow-body commer- can turn at its optimum cial airline industry—until now a dormant market for P&W— speed while also allowing for a lighter, more efficient turbine to which had long demanded a total plane package that would turn at a higher speed in driving a much larger, slower-turning achieve reduced maintenance, lower emissions, better fuel burn, fan. -
The Market for Aviation Turbofan Engines
The Market for Aviation Turbofan Engines Product Code #F640 A Special Focused Market Segment Analysis by: Aviation Gas Turbine Forecast Analysis 1 The Market for Aviation Turbofan Engines 2010-2019 Table of Contents Executive Summary .................................................................................................................................................2 Introduction................................................................................................................................................................2 Trends..........................................................................................................................................................................3 Market Focus .............................................................................................................................................................3 Competitive Environment.......................................................................................................................................4 Figure 1 - The Market for Aviation Turbofan Engines Unit Production 2010 - 2019 (Bar Graph) .................................................................................6 Figure 2 - The Market for Aviation Turbofan Engines Value of Production 2010 - 2019 (Bar Graph)...........................................................................6 Manufacturers Review.............................................................................................................................................7 -
The Pratt & Whitney Purepower® Geared Turbofan™ Engine Overview
9/27/2015 The Pratt & Whitney PurePower® Geared Turbofan™ Engine Alan Epstein VP, Technology and Environment Pratt & Whitney Academie de l’Air et de l’Espace Paris, September 2015 © 2015 United Technologies Corporation This document has been publicly released 1 Overview The Development of the Geared TurbofanTM Engine • Some historical perspective • A recurrent theme - conventional wisdom vs. reality • The roles of architecture, design, and technology • Speculation on the future © 2015 United Technologies Corporation This document has been publicly released 2 1 9/27/2015 PurePower® Geared Turbofan™ Engine © 2015 United Technologies Corporation This document has been publicly released 3 Why History? “There is nothing new in the world except the history you do not know.” Harry S. Truman © 2015 United Technologies Corporation This document has been publicly released 4 2 9/27/2015 Pratt & Whitney – Dependable Engines Wasp Pic Wasp Engine Turbofan Engine 1925 2015 © 2015 United Technologies Corporation This document has been publicly released 5 Eras of Engine Architecture Single Spool Dual Spool Turbojet High Bypass Turbofan Ultra-High Bypass (1937) (1951) (1969) Geared Turbofan (2015) >10% STEPS IN EFFICIENCY OVERALL EFFICIENCY EFFICIENCY OVERALL 1940 1960 1980 2000 2020 © 2015 United Technologies Corporation This document has been publicly released 6 3 9/27/2015 Geared Turbofan Technology Demonstrators Over 50 years of interest Hamilton Standard General Electric Lycoming ALF502 4 5 Pratt & Whitney PW304, 1957 Q-Fan, 19722 QCSEE, 1977 1980 -
Aviation Week & Space Technology
$14.95 AUGUST 31-SEPTEMBER 13, 2020 X = Raider + Defi ant A DECADE OF SPEED GE, Pratt and Rolls Lower Margins, Higher Risks A Hypersonic Upgrade RICH MEDIA for U.S. ICBMs? EXCLUSIVE AI-Human Dogfight Advantage Machine Digital Edition Copyright Notice The content contained in this digital edition (“Digital Material”), as well as its selection and arrangement, is owned by Informa. and its affiliated companies, licensors, and suppliers, and is protected by their respective copyright, trademark and other proprietary rights. Upon payment of the subscription price, if applicable, you are hereby authorized to view, download, copy, and print Digital Material solely for your own personal, non-commercial use, provided that by doing any of the foregoing, you acknowledge that (i) you do not and will not acquire any ownership rights of any kind in the Digital Material or any portion thereof, (ii) you must preserve all copyright and other proprietary notices included in any downloaded Digital Material, and (iii) you must comply in all respects with the use restrictions set forth below and in the Informa Privacy Policy and the Informa Terms of Use (the “Use Restrictions”), each of which is hereby incorporated by reference. Any use not in accordance with, and any failure to comply fully with, the Use Restrictions is expressly prohibited by law, and may result in severe civil and criminal penalties. Violators will be prosecuted to the maximum possible extent. You may not modify, publish, license, transmit (including by way of email, facsimile or other electronic means), transfer, sell, reproduce (including by copying or posting on any network computer), create derivative works from, display, store, or in any way exploit, broadcast, disseminate or distribute, in any format or media of any kind, any of the Digital Material, in whole or in part, without the express prior written consent of Informa. -
Fourteenth European Rotorcraft Forum A
. ' . FOURTEENTH EUROPEAN ROTORCRAFT FORUM Paper No. 96 A HYDRODYNAMIC TURBO-FAN/SHAFT CONVERTIBLE ENGINE R. R. OSSI TEXTRON LYCOMING STRATFORD, CONNECTICUT USA 20-23 September, 1988 MILAN, ITALY ASSOCIAZIONE INDUSTRIE AEROSPAZIALI ASSOCIAZIONE ITALIANA DI AERONAUTICA ED ASTRONAUTICA ABSTRACT A HYDRODYNAMIC TURBO-FAN/SHAFT CONVERTIBLE ENGINE R. R. Ossi Textron Lycoming Stratford, Connecticut USA Advanced powered lift aircraft will require greater translational flight speed to render themselves economically competitive with other .~uture modes of transportation. Initial and operational costs of such aircraft may be reduced significantly by effective consolidation of the various propulsion schemes into a m~n~mum number of prime movers. Such is the motivation behind the concept of the "convertible" engine. The most common current perception of the convertible engine is a standard configuration turbofan which incorporates aerodynamic devices to redirect the engine's low-pressure-spool shaft-power to an appropriate power takeoff on the engine structure. The available mechanical shaft-power is directed to the VTOL aircraft lift system during the lift-off or landing operations. The use of a hydrodynamic drive on the low-pressure-spool may present certain engine design, installation, and operational advantages for future vertical lift aircraft. By this system, a compact transformation of a standard configuration turbofan engine can be designed wherein the fan component is operated by a variable geometry hydrodynamic drive unit. This device is directly driven by the two-spool turbofan engine low pressure gas turbine. Actuation of the variable geometry can provide a wide variety of ·operating modes by controlling the fan speed. As the fan speed is reduced, the gas turbine power is made available on an appropriate mechanical power takeoff for vertical powered lift operation. -
Modernization of the Czech Air Force
Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection 2001-06 Modernization of the Czech Air Force. Vlcek, Vaclav. http://hdl.handle.net/10945/10888 NAVAL POSTGRADUATE SCHOOL Monterey, California THESIS MODERNIZATION OF THE CZECH AIR FORCE by Vaclav Vlcek June 2001 Thesis Advisor: Raymond Franck Associate Advisor: Gregory Hildebrandt Approved for public release; distribution is unlimited. 20010807 033 REPORT DOCUMENTATION PAGE Form Approved OMBNo. 0704-0188 Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instruction, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302, and to the Office of Management and Budget, Paperwork Reduction Project (0704-0188) Washington DC 20503. 1. AGENCY USE ONLY (Leave blank) 2. REPORT DATE 3. REPORT TYPE AND DATES COVERED June 2001 Master's Thesis 4. TITLE AND SUBTITLE : MODERNIZATION OF THE CZECH AIR FORCE 5. FUNDING NUMBERS 6. AUTHOR(S) Vaclav VIcek 8. PERFORMING 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) ORGANIZATION REPORT Naval Postgraduate School NUMBER Monterey, CA 93943-5000 9. SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSORING / MONITORING N/A AGENCY REPORT NUMBER 11. SUPPLEMENTARY NOTES The views expressed in this thesis are those of the author and do not reflect the official policy or position of the Department of Defense or the U.S. -
On the Design of Energy Efficient Aero Engines Some Recent Innovations
THESIS FOR THE DEGREE OF DOCTOR OF PHILOSOPHY in Thermo and Fluid Dynamics On the Design of Energy Efficient Aero Engines Some Recent Innovations By Richard Avellán Department of Applied Mechanics CHALMERS UNIVERSITY OF TECHNOLOGY Göteborg, Sweden, 2011 On the Design of Energy Efficient Aero Engines: Some Recent Innovations Richard Avellán © RICHARD AVELLÁN, 2011. ISBN 978-91-7385-564-8 Doktorsavhandlingar vid Chalmers tekniska högskola Ny serie nr 3245 ISSN 0346-718X Department of Applied Mechanics Chalmers University of Technology SE-412 96 Gothenburg Sweden Telephone + 46 (0)31-772 1000 Cover: [Artist’s impression of a future energy efficient aircraft driven by counter-rotating propeller engines. Source: Volvo Aero Corporation] Printed at Chalmers Reproservice Göteborg, Sweden On the Design of Energy Efficient Aero Engines Some Recent Innovations By Richard Avellán Division of Fluid Dynamics Department of Applied Mechanics Chalmers University of Technology SE-412 96 Göteborg Abstract n the light of the energy crisis of the 1970s, the old aerospace paradigm of flying higher and I faster shifted towards the development of more energy efficient air transport solutions. Today, the aeronautical research and development community is more prone to search for innovative solutions, in particular since the improvement rate of change is decelerating somewhat in terms of energy efficiency, which still is far from any physical limits of aero engine and aircraft design. The Advisory Council for Aeronautics Research in Europe has defined a vision for the year of 2020 for aeronautical research in Europe which states a 50% reduction in CO2, 80% reduction in NOx and a 50% reduction in noise. -
MTU Aero Engines (MTX.DE) Investment Memo Date: 6/11/2020; Closing Stock Price: €154.4 (EUR)
MTU Aero Engines (MTX.DE) Investment Memo Date: 6/11/2020; Closing stock price: €154.4 (EUR) Disclaimer This report is for informational purposes only and does not constitute an offer to sell, solicitation to buy, or a recommendation for any security, or as an offer to provide advisory or other services in any jurisdiction in which such offer, solicitation, purchase or sale would be unlawful under the securities laws of such jurisdiction. Any offer to sell is done exclusively through the fund's Private Placement Memorandum. Past performance may not be indicative of any future results. No current or prospective client should assume that the past performance of any investment or investment strategy referenced directly or indirectly herein will perform in the same manner in the future. Different types of investments and investment strategies involve varying degrees of risk—all investing involves risk—and may experience positive or negative growth. Nothing herein should be construed as guaranteeing any investment performance. Investment funds advised by LRT Capital Management, LLC may maintain positions in the securities discussed within. The views presented here are subject to risk and uncertainties. The views presented herein may change without notice. For more information contact [email protected]. Overview MTU Aero Engines (“MTU”) operates in the aerospace engine market as an engine sub-system supplier and an independent provider of maintenance, repair, and overhaul services (MRO). MTU’s business is broken down into three divisions – commercial OEM business, military OEM business, and commercial MRO business. MTU’s revenues are split 40/60 between new engine manufacturing and MRO services, respectively. -
Introduction to Airbreathing Propulsion Systems
Introduction to airbreathing propulsion systems Integrated project: AIAA aircraft design competition 1er master Aerospace 2020 Koen Hillewaert, Université de Liège Design of Turbomachines, A&M [email protected] Remy Princivalle, Principal Engineer, Safran Aero Boosters [email protected] 1. Balances, thrust and performance Drag / thrust definition 1. Balances, thrust and performance Airbreathing engines: acceleration of (clean) air mass flow ● Thrust = acceleration force of engine mass flow from flight vf to jet velocity vj ● Powers – Propulsive power → airplane acceleration : – Mechanical power → fluid acceleration : – Lost power ● Propulsive efficiency: ● Increasing propulsive efficiency for constant thrust – increase mass flow, decrease jet velocity – Ingest flow at speed lower than flight speed 1. Balances, thrust and performance Airbreathing engines: Boundary Layer Ingestion ● ● 1. Balances, thrust and performance Airbreathing engines: classical performance parameters ● Thermal energy ! = mf Δhf – Fuel mass flow rate: – Fuel to air ratio: – Fuel lower heating value: ● "verall efficiency propulsive power Pp versus thermal energy ! – Propulsive efficiency: – Thermal efficiency: ● Efficiency $ Thrust specific fuel consumption (TSFC) ● Compacity $ Specific thrust 2. Jet engines Generation of high” speed "et through e#pansion over no%%le Snecma/'' (lympus 593 Afterburning ,urbo"et -./ Leap -i$il ,urbofan Snecma /88 Afterburning Turbofan 2. Jet engines Generation of high” speed "et through e#pansion over no%%le ● Ingestion of ma air at flight speed in nacelle – Ram effect: increased total T and p due to relative Mach num!er Mf ● Increase total pressure and temperature – Mechanical : fan – Thermal : gas generator " #rayton – $fter!urning ● #(pansion over e(haust noz)le to ambient pressure – %ho&ed – $dapted 2. Jet engines -ore flow: Brayton thermodynamic cycle ● Thermodynamic cycle – $dia!atic compression ' → ( : – %om!ustion ( → ) : – $dia!atic e*pansion )+, : 2. -
Avitrader Monthly MRO Magazine
March 2015 - www.avitrader.com MORE BANG FOR THE BUCK Is North America ready to bring widebody MRO home? Company Profile Rolls-Royce & Partners Finance MRO News from around the world People on the Move latest appointments ICF Analysis Editor‘s Page 2 Additive Manufacturing takes the leap 2015 is expected to be a breakthrough year for the area of additive manufacturing and they are autoclave and is prepared to continue its path im- the much talked about additive manufacturing keeping up with the current development. With its plementing new production methods. processes. MROs have been exploring the influ- newly opened innovation centre at the Lufthansa ence of an additive manufacturing integration on Technik base in Hamburg LHT says its preparing for Our cover story this month, touches on the issue future MRO processes, and many are already see- new requirements and challenges. of additive manufacturing and how far along the ing some benefits of this new technology. technology is being used in the North American However, LHT highlighted that they expect the market. We also look closely at the shifting cus- 3D printing can be used by MROs to manufacture process to still take some time until it really can tomer demand and market dynamics influencing parts with complex geometries on the spot with influence base maintenance work significantly. the heavy maintenance sector in North America. higher accuracy compared to conventional weld- Additive manufacturing is already being used at Interesting stuff! ing. Additive manufacturing is a very fascinating LHT within its innovation centre, but not yet in the potential development path for the airline industry. -
Inhaltsverzeichnis
Inhaltsverzeichnis 1 Einleitung 8 1.1 Marktsituation 8 1.2 Zukunftspotential 9 2 Konzept des Geared Turbofan 13 2.1 Erläuterung des Konzepts 13 2.2 Auswirkungen des Konzepts auf die einzelnen Triebwerksteile 14 2.2.1 Fanbereich 14 2.2.2 Niederdruckteil 14 2.2.3 Hochdruckteil 15 2.2.4 Brennkammer 15 2.2.5 Gehäuse 15 2.2.6 Getriebe 16 2.3 Zusammenfassung der Auswirkungen 18 3 Zur Historie des Geared Turbofan-Konzepts 20 3.1 Aubisque & Astafan 20 3.2 ALF502 & LF 507 20 3.3 Garrett TFE731 21 3.4 Rolls-Royce/SNECMA MS45SD-02 21 3.5 IAE V2500 SuperFan 22 3.6 Vorgänger des Pratt & Whitney PW1000G 23 3.6.1 Pratt & Whitney/Allison 578-DX 23 3.6.2 Advanced Ducted Propulsor (ADP) 23 3.6.3 Pratt & Whitney PW8000 23 3.6.4 Advanced Technology Fan Integrator (ATFI) 24 3.7 Pratt k Whitney PW1000G 24 4 Leistungssyntheserechnung 26 4.1 Programm 26 4.2 Eingabeparameter 26 4.2.1 Vorüberlegungen 26 4.2.2 Schub im Reiseflug 26 4.2.3 Nebenstromverhältnis und Massenströme 27 4.2.4 Wellendrehzahlen 29 4.2.5 Polytrope Wirkungsgrade 30 4.2.6 Brennkammerparameter 35 4.2.7 Druckverluste 35 4.2.8 Schubdüse 36 4.2.9 Luftsystem 37 4.2.10 Leistungsentnahme 37 4.2.11 Mechanische Wirkungsgrade 38 4.2.12 Druckverhältnisse 39 4.3 Ergebnisse der Leistungsrechnung im Auslegungspunkt 40 ii http://d-nb.info/1035562723 4.4 Berücksichtigung der Startforderung 42 5 Missionsanalyse 45 5.1 Definition der Flugprofile 45 5.1.1 Mittelstreckenmission 45 5.1.2 Kurzstreckenmission 46 5.2 Bestimmung des Schubs je Zustandspunkt 48 5.3 Ergebnisse der Missionsanalyse 51 5.4 Mögliche Optimierungen 55 6 Massenabschätzung des Getriebes 56 6.1 Vorstellung der empirischen Ansätze 56 6.1.1 Motivation 56 6.1.2 Ansatz nach Worobel und Mayo 56 6.1.3 Ansatz nach Plencner, Senty und Wickenheiser 57 6.1.4 Ansätze nach Grieb 57 6.1.5 Ansatz nach Tong.