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Robust Gas Turbine and Airframe System Design in Light of Uncertain
Robust Gas Turbine and Airframe System Design in Light of Uncertain Fuel and CO2 Prices Stephan Langmaak1, James Scanlan2, and András Sóbester3 University of Southampton, Southampton, SO16 7QF, United Kingdom This paper presents a study that numerically investigated which cruise speed the next generation of short-haul aircraft with 150 seats should y at and whether a con- ventional two- or three-shaft turbofan, a geared turbofan, a turboprop, or an open rotor should be employed in order to make the aircraft's direct operating cost robust to uncertain fuel and carbon (CO2) prices in the Year 2030, taking the aircraft pro- ductivity, the passenger value of time, and the modal shift into account. To answer this question, an optimization loop was set up in MATLAB consisting of nine modules covering gas turbine and airframe design and performance, ight and aircraft eet sim- ulation, operating cost, and optimization. If the passenger value of time is included, the most robust aircraft design is powered by geared turbofan engines and cruises at Mach 0.80. If the value of time is ignored, however, then a turboprop aircraft ying at Mach 0.70 is the optimum solution. This demonstrates that the most fuel-ecient option, the open rotor, is not automatically the most cost-ecient solution because of the relatively high engine and airframe costs. 1 Research Engineer, Computational Engineering and Design 2 Professor of Aerospace Design, Computational Engineering and Design, AIAA member 3 Associate Professor in Aircraft Engineering, Computational Engineering and Design, AIAA member 1 I. Introduction A. Background IT takes around 5 years to develop a gas turbine engine, which then usually remains in pro- duction for more than two decades [1, 2]. -
NPA 2018-13 Table of Contents
European Aviation Safety Agency Notice of Proposed Amendment 2018-13 Appendix I to AMC to Annex III (Part-66) Aircraft type ratings for Part-66 aircraft maintenance licences RMT.0541 (66.024) EXECUTIVE SUMMARY This Notice of Proposed Amendment (NPA) addresses a regulatory coordination issue related to aircraft type ratings. According to the AMC to Annex III (Part-66), type ratings should be endorsed on an aircraft maintenance licence (AML) in accordance with Appendix I to AMC to Part-66 ‘List of type ratings’. An NPA is issued regularly to amend this list, after assessing feedback received from the industry, and to add new aircraft types or to remove aircraft types whose type certificate (TC) has been revoked or surrendered. This NPA adds also the tables of the new Group as a consequence of the introduction of the ‘L’ licence subcategories by Commission Regulation (EU) 2018/1142. The main objective is to ensure a common standard throughout the Member States. Action area: Regular updates/review of rules Affected rules: AMC/GM to Annex III (Part-66) to Commission Regulation (EU) No 1321/2014 Affected stakeholders: Maintenance certifying staff; maintenance training organisations; maintenance organisations; competent authorities Driver: Efficiency/proportionality Rulemaking group: No Impact assessment: None Rulemaking Procedure: Standard 12.5.2009 5.12.2018 2019/Q2 TE.RPRO.00034-008 © European Aviation Safety Agency. All rights reserved. ISO 9001 certified. Proprietary document. Copies are not controlled. Confirm revision status through the EASA intranet/internet. Page 1 of 186 An agency of the European Union European Aviation Safety Agency NPA 2018-13 Table of contents Table of contents 1. -
International Aero Engines V2500-A1, V2522-A5
Federal Register / Vol. 75, No. 225 / Tuesday, November 23, 2010 / Proposed Rules 71373 under the criteria of the Regulatory (i) For TAE 125–01 engines, Operation & DEPARTMENT OF TRANSPORTATION Flexibility Act. Maintenance Manual OM–01–02, Issue 3, We prepared a regulatory evaluation Revision 13. Federal Aviation Administration of the estimated costs to comply with (ii) For TAE 125–02–99 and TAE 125–02– this proposed AD and placed it in the 114 engines, Operation & Maintenance 14 CFR Part 39 AD docket. Manual OM–02–02, Issue 1, Revision 10. [Docket No. FAA–2010–0494; Directorate List of Subjects in 14 CFR Part 39 Prohibition of FADEC Software Earlier Identifier 2010–NE–20–AD] Versions Air transportation, Aircraft, Aviation (f) Once FADEC software version 2.91 is RIN 2120–AA64 safety, Safety. installed, do not install any earlier version of Airworthiness Directives; International FADEC software. The Proposed Amendment Aero Engines V2500–A1, V2522–A5, Accordingly, under the authority FAA AD Differences V2524–A5, V2525–D5, V2527–A5, delegated to me by the Administrator, (g) EASA AD 2010–0137 permits V2527E–A5, V2527M–A5, V2528–D5, the FAA proposes to amend 14 CFR part installation of earlier FADEC software V2530–A5, and V2533–A5 Turbofan 39 as follows: versions, once version 2.91 is installed. This Engines AD does not. AGENCY: Federal Aviation PART 39—AIRWORTHINESS (h) EASA AD 2010–0137 requires Administration (FAA), DOT. DIRECTIVES compliance within 110 flight hours after the effective date of the AD or during next ACTION: Notice of proposed rulemaking 1. The authority citation for part 39 maintenance, whichever occurs first, but no (NPRM). -
ISSEK HSE) Role of Big Data Augmented Horizon Scanning in Strategic and Marketing Analytics
National Research University Higher School of Economics Institute for Statistical Studies and Economics of Knowledge Big Data Augmented Horizon Scanning: Combination of Quantitative and Qualitative Methods for Strategic and Marketing Analytics [email protected] [email protected] XIX April International Academic Conference on Economic and Social Development Moscow, 11 April 2018 Outline - Role of artificial intelligence and big data in modern analytics - System of Intelligent Foresight Analytics iFORA - Combined quantitative and qualitative analysis methodology and software solutions - Use cases - Conclusion and discussion 2 Growing interest in Artificial Intelligence, Big Data and Machine Learning International analytical reports & news feed 12000 10000 8000 Artificial Intelligence 6000 Big Data Machine Learning 4000 2000 0 2000 2001 2002 2003 2004 2005 2006 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016 Russian analytical reports & news feed 800 700 600 500 Artificial Intelligence 400 Big Data 300 Machine Learning 200 100 0 2000 2001 2002 2003 2004 2005 2006 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016 3 Source: System of Intelligent Foresight Analytics iFORA™ (ISSEK HSE) Role of Big Data Augmented Horizon Scanning in Strategic and Marketing Analytics AI-related tasks Tracking latest and challenges trends, technologies, drivers, barriers Market forecasting Trend analysis Understanding S&T modern skills and Instruments for Customers Market Intelligence competences analysis feedback knowledge discovery HR policy Vacancy Feedback mining -
An Analysis of Coast Guard HH-65 Engine Reliability: a Comparison of Malfunctions to Component Removals
Air Force Institute of Technology AFIT Scholar Theses and Dissertations Student Graduate Works 3-2004 An Analysis of Coast Guard HH-65 Engine Reliability: A Comparison of Malfunctions to Component Removals Donna L. Cottrell Follow this and additional works at: https://scholar.afit.edu/etd Part of the Applied Mathematics Commons, Aviation Commons, and the Systems Engineering Commons Recommended Citation Cottrell, Donna L., "An Analysis of Coast Guard HH-65 Engine Reliability: A Comparison of Malfunctions to Component Removals" (2004). Theses and Dissertations. 4082. https://scholar.afit.edu/etd/4082 This Thesis is brought to you for free and open access by the Student Graduate Works at AFIT Scholar. It has been accepted for inclusion in Theses and Dissertations by an authorized administrator of AFIT Scholar. For more information, please contact [email protected]. AN ANALYSIS OF COAST GUARD HH-65 ENGINE RELIABILITY: A COMPARISON OF MALFUNCTIONS TO COMPONENT REMOVALS THESIS Donna L. Cottrell, Commander, USCG AFIT/GIR/ENC/04-01 DEPARTMENT OF THE AIR FORCE AIR UNIVERSITY AIR FORCE INSTITUTE OF TECHNOLOGY Wright-Patterson Air Force Base, Ohio APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED The views expressed in this thesis are those of the author and do not reflect the official policy or position of the United States Air Force, United States Coast Guard, Department of Defense, Department of Homeland Security, or the United States Government. AFIT/GIR/ENC/04-01 AN ANALYSIS OF COAST GUARD HH-65 ENGINE RELIABILITY: A COMPARISON OF MALFUNCTIONS TO COMPONENT REMOVALS THESIS Presented to the Faculty Department of Mathematics and Statistics Graduate School of Engineering and Management Air Force Institute of Technology Air University Air Education and Training Command In Partial Fulfillment of the Requirements for the Degree of Master of Science in Information Resource Management Donna L. -
Trusted to Deliver Excellence Rolls-Royce Holdings Plc Annual
Rolls-Royce Holdings plc plc Holdings Rolls-Royce Rolls-Royce Holdings plc Annual report 2011 Trusted to deliver excellence Annual reportAnnual 2011 ® ® © Rolls-Royce plc 2012 Trusted to deliver excellence deliver to Trusted Rolls-Royce Holdings plc Registered office: 65 Buckingham Gate London SW1E 6AT T +44 (0)20 7222 9020 www.rolls-royce.com Company number 7524813 129 Glossary Contents Glossary Business review ABC Anti-bribery and corruption IFRS International Financial Reporting Standards Civil aerospace Defence aerospace 1 Introduction ABI Association of British Insurers INVENT Integrated Vehicle Energy Technology 2 Chairman’s statement 4 Chief Executive’s review ACARE Advisory Council for Aviation Research and IPTMSD Integrated Power and Thermal Management System Development 6 Our business model and strategy Innovation in Europe ISO International Standards Organisation 8 Our business segments ADR American Depositary Receipts Programme LDI Liability-driven investment 9 Market opportunities ADVENT Adaptive Versatile Engine Technology LIBOR London Inter-bank Offered Rate 10 Key performance indicators AEBS All-Employee Bonus Scheme 14 Finance Director’s review LLP Limited Liability Partnership 18 Civil aerospace AFRL US Air Force Research Lab LTSA Long-Term Service Agreement 20 Defence aerospace AGM Annual General Meeting MoD UK Ministry of Defence 22 Marine p18 p20 ANA All Nippon Airways MoU Memorandum of Understanding 24 Energy APB Auditing Practices Board 26 Excellence in technology MWh Megawatt hours APRA Annual Performance Related -
Airbus A320-232, G-EUUI
Airbus A320-232, G-EUUI AAIB Bulletin No: 11/2004 Ref: EW/C2003/11/04 Category: 1.1 INCIDENT Aircraft Type and Airbus A320-232, G-EUUI Registration: No & Type of Engines: 2 International Aero Engines (IAE) V2527-A5 turbofan engines Year of Manufacture: 2002 Date & Time (UTC): 29 November 2003 at 1955 hrs Location: Overhead Birmingham Type of Flight: Public Transport (Passenger) Persons on Board: Crew - 7 Passengers - 92 Injuries: Crew - None Passengers - None Nature of Damage: None Commander's Licence: Airline Transport Pilot's Licence Commander's Age: 39 years Commander's Flying 11,350 hours Experience: (of which 930 were on type) Last 90 days - 166 hours Last 28 days - 50 hours Information Source: AAIB Field Investigation Synopsis On a relatively clear evening, upon reaching the cruise level of Flight Level (FL) 280, the crew and passengers on a scheduled flight from London Heathrow to Edinburgh experienced momentary noise and vibration throughout the aircraft. This was repeated approximately one minute later. It was also reported that an orange flash, associated with the right engine, had been seen. The flight crew identified that No 2 engine had surged and recovered, with the engine indications returning to normal. The aircraft's Quick Reference Handbook, coupled with the training that the flight crew had received, provided them with inadequate guidance with which to fully assess the situation. Their initial intention to continue to Edinburgh was changed upon advice from the operator and the crew initiated a return to Heathrow. The engine then began to surge again and, once more, recovered, but this was followed by another series of surges. -
The Analysis of the Reference Shaft Under Torque Measurement Unit for Turboshaft Engines
THE ANALYSIS OF THE REFERENCE SHAFT UNDER TORQUE MEASUREMENT UNIT FOR TURBOSHAFT ENGINES by KEREM KILIÇ Submitted to the Graduate School of Engineering and Natural Sciences in partial fulfilment of the requirements for the degree of Master of Science Sabancı University December 2020 THE ANALYSIS OF THE REFERENCE SHAFT UNDER TORQUE MEASUREMENT UNIT FOR TURBOSHAFT ENGINES Approved by: Approval Date: December 25, 2020 KEREM KILIC 2020 © All Rights Reserved ABSTRACT THE ANALYSIS OF THE REFERENCE SHAFT UNDER TORQUE MEASUREMENT UNIT FOR TURBOSHAFT ENGINES KEREM KILIC ENERGY TECHNOLOGIES and MANAGEMENT M.Sc THESIS, DECEMBER 2020 Thesis Supervisor: Asst. Prof. BEKIR BEDIZ Keywords: Torque Measurement, Angular Twist Method, Reference Shaft, Torquemeter, Turboshaft Engine Gas turbine engines have become a dominating and convincing power source in aviation; for instance, turboshaft gas turbine engines are widespread propulsion systems for helicopters. In turboshaft engines, produced power is transmitted to the helicopter rotor group via a power output shaft. The level of power extraction depends on the transmitted torque and rotational speed of the power output shaft. The need to measure the torque from a rotating shaft leads to the development of various torque measurement units. The commonly used torque measurement unit (TMU) of compact turboshaft engines makes use of an angular twist method. The angular twist method is a multidisciplinary approach with a strong base in mechanics, electronics, and control. In this thesis, a comparison of TMU of various turboshaft engines, which use the angular twist method, is done concerning mechanical discipline. The new generic conceptual design of the reference shaft is done under TMU to be used for different turboshaft engines with minor modifications. -
What to Consider When Investing in Engines
Editor’s letter What to consider when investing in engines Engine investors need to be more reactive to changes than aircraft investors, as even a small change can impact the attractiveness of an asset. nvesting in engines is quite different to investing came into service with Lufthansa in January 2016. Iin aircraft. When investing in engines only, there How to communicate an engine issue to the is less of an emphasis on long-term contractual market as an OEM can be critical – either be open business, with power-by-the-hour contracts about the technical issues with the customers being an exception. Such contracts are risky for and accept the engine’s faults, or claim that the independent servicers, but less so for original problems have been fully addressed when they equipment manufacturers (OEMs), which can have not. The latter strategy can backfire, because control the parts supply. There are different it means that any technical issues make more customer bases to consider for engines and headlines and have more of an impact on market technical knowledge of the asset is needed to be sentiment towards the engine. able to spot opportunities. When investing in an engine, also consider the Another major difference is that lessors in aftermarket and the role the OEM has in it. OEMs the engine market often do not get a chance to are often criticised by engine investors for being order engines directly from the OEMs, but instead too involved in the aftermarket. The market is gain most of their business through sale and lucrative, but if an OEM has too much involvement leasebacks. -
Calepin International B6 2009 Version3.Indd
Calepin international des principales entreprises travaillant pour la défense Édition Mai 2009 DÉLÉGATION GÉNÉRALE POUR L’ARMEMENT Sommaire Sommaire .............................................................................................. p. 3 Carte des ensembles de sécurité en Europe ............................................ p. 4 Préface .................................................................................................. p. 5 Taux de change de l’Euro ....................................................................... p. 6 Fiches sociétés (pays de la LoI* + États-Unis) Sommaire sociétés pays de la LoI + États-Unis ....................................... p. 7 à 8 Fiches sociétés pays de la LoI + États-Unis ............................................. p. 9 à 112 Tableaux pays (LoI* + Etats-Unis) Sommaire tableaux pays de la LoI + États-Unis ...................................... p. 114 Allemagne............................................................................................. p. 116 Espagne ................................................................................................ p. 117 États-Unis d’Amérique ........................................................................... p. 118 France ................................................................................................... p. 119 Italie ..................................................................................................... p. 120 Royaume-Uni ....................................................................................... -
Vliv Vlastností Pracovní Látky Na Výkonové Parametry Letadlového Motoru
ČESKÉ VYSOKÉ UČENÍ TECHNICKÉ V PRAZE Fakulta strojní Ústav letadlové techniky VLIV VLASTNOSTÍ PRACOVNÍ LÁTKY NA VÝKONOVÉ PARAMETRY LETADLOVÉHO MOTORU Diplomová práce 2016 Jan Bernášek Prohlášení „Nemám závažný důvod proti užívání tohoto školního díla ve smyslu § 60 Zákona č. 121/2000 Sb., o právu autorském, o právech souvisejících s právem autorským a o změně některých zákonů (autorský zákon).“ „Prohlašuji, že jsem předloženou práci vypracoval samostatně a že jsem uvedl veškeré použité informační zdroje v souladu s Metodickým pokynem o etické přípravě vysokoškolských závěrečných prací.“ V Praze dne 5. 8. 2016 vlastnoruční podpis autora Poděkování Na tomto místě bych rád poděkoval panu Ing. Davidu Hlaváčkovi za vedení mé diplomové práce a za jeho velikou ochotu a vstřícnost, se kterou přistupoval k veškerým našim konzultacím. Dále bych rád poděkoval mé novomanželce za podporu při studiu a při psaní této práce, a v neposlední řadě bych rád poděkoval svým rodičům za jejich morální a materiální podporu, které se mi dostávalo po celou dobu mého studia. Obsah Seznam obrázků ......................................................................................................................... 8 Seznam tabulek .......................................................................................................................... 9 Seznam grafů ............................................................................................................................ 11 Seznam používaných symbolů ................................................................................................ -
National Air & Space Museum Technical Reference Files: Propulsion
National Air & Space Museum Technical Reference Files: Propulsion NASM Staff 2017 National Air and Space Museum Archives 14390 Air & Space Museum Parkway Chantilly, VA 20151 [email protected] https://airandspace.si.edu/archives Table of Contents Collection Overview ........................................................................................................ 1 Scope and Contents........................................................................................................ 1 Accessories...................................................................................................................... 1 Engines............................................................................................................................ 1 Propellers ........................................................................................................................ 2 Space Propulsion ............................................................................................................ 2 Container Listing ............................................................................................................. 3 Series B3: Propulsion: Accessories, by Manufacturer............................................. 3 Series B4: Propulsion: Accessories, General........................................................ 47 Series B: Propulsion: Engines, by Manufacturer.................................................... 71 Series B2: Propulsion: Engines, General............................................................