Integration of Turbofan Engines Into the Preliminary Design of a High
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Flying Outside The
ISSN 1718-7966 June 26, 2017/ VOL. 596 WEEKLY AVIATION HEADLINES Read by thousands of aviation professionals and technical decision-makers every week www.avitrader.com WORLD NEWS Ryanair launches connecting flights in Milan Ryanair, the largest airline in Italy ex- tended its connecting flights service to Milan Bergamo Airport, providing Ryanair customers with an expanded route choice, and the opportunity to book and transfer directly onto con- necting Ryanair flights. This come following the successful launch of connecting flights at Rome Fiumicino last month. In other news Ryanair (Europe) announced the purchase of 10 more Boeing 737 Max 200 “Ga- mechanger” aircraft, 5 of which will deliver in the first half of 2019, with the second 5 delivering in the first half of 2020. Airbus unveiled new innovations Nasmyth Group opens new met- in Paris. al treatment facility in California Pegasus Nasmyth Group announces Photo: Airbus the opening of a new metal surface treatments facility in the Santa Clarita Flying outside the box Valley (SCV) in Valencia, California, sig- OEMs spread their wings at Paris nificantly expanding Nasmyth TMF’s footprint and ability to deliver services This year’s Paris Air Show was rela- unit), would allow an aircraft fitted unit also sends data automatically to aerospace and defence clients in the tively upbeat in terms of orders espe- with it to taxi without using its jet into efficiency applications such as USA. The processing line will be able to cially by the big two Boeing and Air- engines or requiring airport tractors weather, flight planning, logbooks, operate 24 hours a day, seven days a bus but the common theme across or tugs. -
Airworthiness Directives; Airbus Dated September 12, 2013
Federal Register / Vol. 78, No. 220 / Thursday, November 14, 2013 / Rules and Regulations 68347 PART 39—AIRWORTHINESS in accordance with Part 2 of the (j) Related Information DIRECTIVES Accomplishment Instructions of Boeing Alert For more information about this AD, Service Bulletin 747–57A2343, dated contact Nathan Weigand, Aerospace ■ 1. The authority citation for part 39 September 12, 2013. If any cylindrical defect Engineer, Airframe Branch, ANM–120S, continues to read as follows: is found, before further flight, do the actions FAA, Seattle Aircraft Certification Office, specified in paragraph (h)(1)(i) or (h)(1)(ii) of 1601 Lind Avenue SW., Renton, WA 98057– this AD. Authority: 49 U.S.C. 106(g), 40113, 44701. 3356; phone: 425–917–6428; fax: 425–917– (i) Do a minimum thickness inspection of 6590; email: [email protected]. § 39.13 [Amended] the inboard actuator attach fitting to determine minimum wall thickness of the (k) Material Incorporated by Reference ■ 2. The FAA amends § 39.13 by adding actuator fitting assembly, in accordance with (1) The Director of the Federal Register the following new airworthiness Part 3 of the Accomplishment Instructions of approved the incorporation by reference directive (AD): Boeing Alert Service Bulletin 747–57A2343, (IBR) of the service information listed in this dated September 12, 2013. If the minimum 2013–23–03 The Boeing Company: paragraph under 5 U.S.C. 552(a) and 1 CFR thickness of the wall is less than 0.130 inch: Amendment 39–17658; Docket No. part 51. Before further flight, replace the inboard FAA–2013–0871; Directorate Identifier actuator attach fitting of the outboard flap, in (2) You must use this service information 2013–NM–187–AD. -
Airbus A320 Family Equipment Catalogue Incl
AIRBUS A320 EQUIPMENT CATALOGUE EQUIPMENT A320 AIRBUS | HYDRO AIRBUS A320 FAMILY EQUIPMENT CATALOGUE INCL. NEO 5 HYDRO | Airbus A320 Equipment 1 _INDEX 12 2_EQUIPMENT LIST 16 3 _DIMENSIONS & AREAS 23 3.1 AIRCRAFT MAINTENANCE ACCESS STAND 24 3.2 MULTI-PURPOSE PLATFORM 26 4 _LIFTING & SHORING (ATA CHAPTER 07) 29 4.1 FORTEVO TRIPOD-JACKS 30 4.2 SMARTLINE TRIPOD-JACKS 46 4.3 SHORING STANCHION 50 4.4 AXLE-JACK / STANDARD AXLE-JACK (RT) 52 4.5 AXLE-JACK / UNIVERSAL AXLE-JACK (RC) 56 4.6 AXLE-JACK / FLY-AWAY AXLE-JACK (RH) 58 4.7 AXLE-JACK / RECOVERY AXLE-JACK (RL) 60 4.8 RECOVERY AXLE-JACK BEAM 62 4.9 AXLE-JACK HOSE PRESSURE KIT 64 4.10 STEERING TEST EQUIPMENT 65 5 _TOWING AND TAXING (ATA CHAPTER 09) 66 5.1 TOW-BAR (STANDARD) 68 5.2 TOW-BAR (UNIVERSAL) 70 5.3 TOW-BAR (FLY-AWAY) 72 5.4 DEBOGGING KIT 74 6 _SERVICING (ATA CHAPTER 12) 76 6.1 NITROGEN SERVICE CART 78 6.2 OXYGEN SERVICE CART 80 6.3 AIRCRAFT WHEEL AND BRAKE CHANGE TRAILER 82 6.4 FLUID DISPENSER 84 6.5 AIRCRAFT TYRE PRESSURE GAUGES 86 6.6 AIRCRAFT TYRE INFLATION 88 6.7 OIL FILLING UNIT 90 7 _ELECTRONIC BONDING (ATA CHAPTER 20) 92 7 LOOP RESISTANCE TESTER AIRLINER SET 94 8 _EQUIPMENT / FURNISHING (ATA CHAPTER 25) 97 8 CABIN INTERIOR ACCESS STAND 98 9 _HYDRAULIC POWER (ATA CHAPTER 29) 97 9.1 HYDRAULIC POWER 104 9.2 WATER SEPARATOR SYSTEM 108 9.3 SAMPLING VALVE ADAPTER 110 HYDRO | Airbus A320 Equipment 6 9.4 TEST EQUIPMENT FOR RAM-AIR TURBINE 111 9.5 RAT SAFETY INTERFACE KIT 113 9.6 TEST EQUIPMENT FOR RAM-AIR TURBINE 114 01 _LANDING GEAR (ATA CHAPTER 32) 117 10.1 WHEEL AND BRAKE CHANGE -
Ivchenko Progress
® AdvancedAdvanced turboprop,turboprop, propfanpropfan andand turbojetturbojet bypassbypass enginesengines forfor GAGA andand lightlight airplanesairplanes S. DMYTRIYEV 23.11.09 ® HISTORY ZAPOROZHYE MACHINE-BUILDING DESIGN BUREAU PROGRESS STATE ENTERPRISE NAMED AFTER ACADEMICIAN A.G. IVCHENKO (SE IVCHENKO-PROGRESS) Foundation date: May 5, 1945 Over a whole past period, engine manufacturing plants have produced more than 80 , 000 aircraft gas turbine and piston engines, turbostarters and industrial plants. Today, the engines designed by SE IVCHENKO-PROGRESS power 57 types of flying vehicle in 109 countries. Over the years, SE IVCHENKO-PROGRESS engines logged more than 300 million flight hours. © SE Ivchenko-Progress, 2009 2 ® HISTORY D-27 propfan , ÒV3-117 VÌÀ- SBÌ1 turboprop , D-436 turbofan , AI -22 turbofan , AI -222 turbofan , AI -450 turboshaft , 4-th stage AI -450 turboprop , SPM-21 turbofan Turbofans with high power and thrust : 3- rd stage D-136, D-18Ò Turbofans : AI -25, AI -25ÒË, D-36 2-nd stage APUs: AI -9, AI -9 V Turboprops : AI -20, AI -24 1- st stage APU: AI -8 Piston engines: AI -26 , AI-14, AI-4 © SE Ivchenko-Progress, 2009 3 ® DIRECTIONS OF ACTIVITY CIVIL AVIATION: commercial aircraft and helicopters Ìè-2Ì Àí-140 Àí-14 8 STATE AVIATION : trainers and combat trainers, military transport aircraft and helicopters , multipurpose aircraft ßê-18Ò Àí-70 Ìè-26Ò ßê-130 Áe-200 Àí-124 © SE Ivchenko-Progress, 2009 4 ® THE BASIC SPHERES OF ACTIVITIES DESIGN MANUFACTURE OVERHAUL TEST AND DEVELOPMENT PUTTING IN SERIES PRODUCTION AND IMPROVEMENT OF CONSUMER'S CHARACTERISTICS © SE Ivchenko-Progress, 2009 5 INTERNATIONAL RECOGNITION OF ® CERTIFICATION AUTHORITIES Totally 60 certificates of various types European Aviation Safety Agency (Germany) Certificate No. -
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]. -
Aerospace Engine Data
AEROSPACE ENGINE DATA Data for some concrete aerospace engines and their craft ................................................................................. 1 Data on rocket-engine types and comparison with large turbofans ................................................................... 1 Data on some large airliner engines ................................................................................................................... 2 Data on other aircraft engines and manufacturers .......................................................................................... 3 In this Appendix common to Aircraft propulsion and Space propulsion, data for thrust, weight, and specific fuel consumption, are presented for some different types of engines (Table 1), with some values of specific impulse and exit speed (Table 2), a plot of Mach number and specific impulse characteristic of different engine types (Fig. 1), and detailed characteristics of some modern turbofan engines, used in large airplanes (Table 3). DATA FOR SOME CONCRETE AEROSPACE ENGINES AND THEIR CRAFT Table 1. Thrust to weight ratio (F/W), for engines and their crafts, at take-off*, specific fuel consumption (TSFC), and initial and final mass of craft (intermediate values appear in [kN] when forces, and in tonnes [t] when masses). Engine Engine TSFC Whole craft Whole craft Whole craft mass, type thrust/weight (g/s)/kN type thrust/weight mini/mfin Trent 900 350/63=5.5 15.5 A380 4×350/5600=0.25 560/330=1.8 cruise 90/63=1.4 cruise 4×90/5000=0.1 CFM56-5A 110/23=4.8 16 -
Design and Analysis of Advanced Flight: Planning Concepts
NASA Contractor Report 4063 Design and Analysis of Advanced Flight: Planning Concepts Johri A. Sorerisen CONrRACT NAS1- 17345 MARCH 1987 NASA Contractor Report 4063 Design and Analysis of Advanced Flight Planning Concepts John .A. Sorensen Analytical Mechanics Associates, Inc. Moantain View, California Prepared for Langley Research Center under Contract NAS 1- 17345 National Aeronautics and Space Administration Scientific and Technical Information Branch 1987 F'OREWORD This continuing effort for development of concepts for generating near-optimum flight profiles that minimize fuel or direct operating costs was supported under NASA Contract No. NAS1-17345, by Langley Research Center, Hampton VA. The project Technical Monitor at Langley Research Center was Dan D. Vicroy. Technical discussion with and suggestions from Mr. Vicroy, David H. Williams, and Charles E. Knox of Langley Research Center are gratefully acknowledged. The technical information concerning the Chicago-Phoenix flight plan used as an example throughout this study was provided by courtesy of United Airlines. The weather information used to exercise the experimental flight planning program EF'PLAN developed in this study was provided by courtesy of Pacific Southwest Airlines. At AMA, Inc., the project manager was John A. Sorensen. Engineering support was provided by Tsuyoshi Goka, Kioumars Najmabadi, and Mark H, Waters. Project programming support was provided by Susan Dorsky, Ann Blake, and Casimer Lesiak. iii DESIGN AND ANALYSIS OF ADVANCED FLIGHT PLANNING CONCEPTS John A. Sorensen Analytical Mechanics Associates, Inc. SUMMARY The Objectives of this continuing effort are to develop and evaluate new algorithms and advanced concepts for flight management and flight planning. This includes the minimization of fuel or direct operating costs, the integration of the airborne flight management and ground-based flight planning processes, and the enhancement of future traffic management systems design. -
Large Composite Fan Blade Development for Modern Aeroengines
Volume I: Composites Applications and Design LARGE COMPOSITE FAN BLADE DEVELOPMENT FOR MODERN AEROENGINES Keith T. Kedward University of California at Santa Barbara Department of Mechanical & Environmental Engineering Santa Barbara, California 93106-5070, USA SUMMARY: The state of maturity of contemporary PMC’s after almost 30 years of scientific and technology development has resulted in a capability that far exceeds that available in the late 1960’s, and which, in 1989, prompted General Electric to engage in the notably successful development and flight certification of large PMC fan blades for their GE90 engine. In this paper an accounting of the specific enhancements in (i) constituent (fiber and matrix) property characteristics, (ii) fabrication and processing options, and (iii) design analysis methods combined with computational capabilities will be discussed. However, an equally important aspect is the variation in the design options that has resulted from evolving high by-pass ratio engine technology, which will also be addressed. The GE90 fan blade represents one of these options, being a relatively large blade designed to operate at lower tip speeds, thereby reducing the severity of the impact threat represented by the ingestion of large birds. A comparison between various modern turbofan engine fan blades and other rotor blades serves to indicate the important parameters and the difficulty of establishing a composite threshold range for rotor blades in general. KEYWORDS: polymer matrix composite, composite fan blade, constituent properties, impact performance, textile reinforcement architectures, engine certification INTRODUCTION Since the ill-fated attempt by Rolls-Royce to develop large polymer matrix composite (PMC) fan blades for a large commercial turbofan engine in 1968, i.e., the RB211, this potential application had eluded the engine designer until the emergence of General Electric’s GE90 engine development. -
Facts & Figures & Figures
OCTOBER 2019 FACTS & FIGURES & FIGURES THE STAR ALLIANCE NETWORK RADAR The Star Alliance network was created in 1997 to better meet the needs of the frequent international traveller. MANAGEMENT INFORMATION Combined Total of the current Star Alliance member airlines: FOR ALLIANCE EXECUTIVES Total revenue: 179.04 BUSD Revenue Passenger 1,739,41 bn Km: Daily departures: More than Annual Passengers: 762,27 m 19,000 Countries served: 195 Number of employees: 431,500 Airports served: Over 1,300 Fleet: 5,013 Lounges: More than 1,000 MEMBER AIRLINES Aegean Airlines is Greece’s largest airline providing at its inception in 1999 until today, full service, premium quality short and medium haul services. In 2013, AEGEAN acquired Olympic Air and through the synergies obtained, network, fleet and passenger numbers expanded fast. The Group welcomed 14m passengers onboard its flights in 2018. The Company has been honored with the Skytrax World Airline award, as the best European regional airline in 2018. This was the 9th time AEGEAN received the relevant award. Among other distinctions, AEGEAN captured the 5th place, in the world's 20 best airlines list (outside the U.S.) in 2018 Readers' Choice Awards survey of Condé Nast Traveler. In June 2018 AEGEAN signed a Purchase Agreement with Airbus, for the order of up to 42 new generation aircraft of the 1 MAY 2019 FACTS & FIGURES A320neo family and plans to place additional orders with lessors for up to 20 new A/C of the A320neo family. For more information please visit www.aegeanair.com. Total revenue: USD 1.10 bn Revenue Passenger Km: 11.92 m Daily departures: 139 Annual Passengers: 7.19 m Countries served: 44 Number of employees: 2,498 Airports served: 134 Joined Star Alliance: June 2010 Fleet size: 49 Aircraft Types: A321 – 200, A320 – 200, A319 – 200 Hub Airport: Athens Airport bases: Thessaloniki, Heraklion, Rhodes, Kalamata, Chania, Larnaka Current as of: 14 MAY 19 Air Canada is Canada's largest domestic and international airline serving nearly 220 airports on six continents. -
Airbus A340-300 Technical Specifications
Technical Specifications Airbus A340-300 AIRCRAFT ZS-SXD (0643) TECHNICAL SPECIFICATION AIRCRAFT Aircraft Type: A340-300 Current Registration: ZS -SXD TT : 63319 As of : 2019-09-30 Serial No: 0643 Date of Manufacture: 25 November 2004 TC : 7935 ENGINE Manufacturer: CFM Model : CFM56=5C4/P International Thrust Rating Engine 1 Engine 2 Engine 3 Engine 4 Serial Number: 567278 567276 567277 567279 56000 lbs (249KN) TT: FH 57016 56317 54787 58026 FC 7134 7060 6944 7385 AS OF 2019-09-30 WEIGHTS AND FUEL Weights Pounds Kilograms Maximum Taxi Weight 608 248 lbs. 275000 kg Maximum Take-Off Weight 606 264 lbs. 275000 kg Maximum Landing Weight 423 287 lbs. 192000 kg Maximum Zero Fuel Weight 396 823 lbs. 180000 kg LANDING GEAR Nose Centre Main LH Wing Main RH Wing Part Number D23581100-20 37100-1001 201490001 201490002 Serial Number B558 DCL331/03 MDL582 MDL582 Status As Of 2019-09-30 2017-12-31 2017-12-31 2017-12-31 Next O/H Date 2024-11-22 2024-11-22 2024-11-22 2024-11-22 WHEELS Nose Centre Main LH Wing Main RH Wing Vendor Goodrich Honeywell Honeywell Honeywell Part Number 3-1596 2612201-3 2612201-3 2612201-3 BRAKES Vendor N/A N/A Honeywell Honeywell Part Number N/A N/A 2612202-4 2612202-4 TYRES Vendor Bridgestone Bridgestone Bridgestone Bridgestone Part Number APR06500 APR06911 APR06911 APR06911 APU Manufacturer: Honeywell Total Time (TT) : FH =16563 FC = 12212 Type /Model : 3800454-6 AS OF 2019-09-30 Serial number : P791 INTERIOR CONFIGURATION Passengers J/C=38 Y/C=215 Total=253 Galleys 9 Lavatories 9 Refer to the attached LOPA and Equipment -
Rolls-Royce / Itp Regulation
EUROPEAN COMMISSION DG Competition Case M.8242 - ROLLS-ROYCE / ITP Only the English text is available and authentic. REGULATION (EC) No 139/2004 MERGER PROCEDURE Article 6(1)(b) in conjunction with Art 6(2) Date: 19/04/2017 In electronic form on the EUR-Lex website under document number 32017M8242 EUROPEAN COMMISSION Brussels, 19.04.2017 C(2017) 2613 final In the published version of this decision, some information has been omitted pursuant to Article PUBLIC VERSION 17(2) of Council Regulation (EC) No 139/2004 concerning non-disclosure of business secrets and other confidential information. The omissions are shown thus […]. Where possible the information omitted has been replaced by ranges of figures or a general description. To the notifying party: Subject: Case M.8242 – Rolls-Royce / ITP Commission decision pursuant to Article 6(1)(b) in conjunction with Article 6(2) of Council Regulation No 139/20041 and Article 57 of the Agreement on the European Economic Area2 Dear Sir or Madam, (1) On 24 February 2017, the European Commission received notification of a proposed concentration pursuant to Article 4 of the Merger Regulation by which the undertaking Rolls-Royce Holdings plc ("Rolls-Royce", United Kingdom) acquires within the meaning of Article 3(1)(b) of the Merger Regulation control of the whole of the undertaking Industria de Turbo Propulsores SA ("ITP", Spain) by way of a purchase of shares (the "Transaction").3 Rolls-Royce is designated hereinafter as the "Notifying Party", and Rolls-Royce and ITP are together referred to as the "Parties". 1 OJ L 24, 29.1.2004, p. -
CRUISE FLIGHT OPTIMIZATION of a COMMERCIAL AIRCRAFT with WINDS a Thesis Presented To
CRUISE FLIGHT OPTIMIZATION OF A COMMERCIAL AIRCRAFT WITH WINDS _______________________________________ A Thesis presented to the Faculty of the Graduate School at the University of Missouri-Columbia _______________________________________________________ In Partial Fulfillment of the Requirements for the Degree Master of Science _____________________________________________________ by STEPHEN ANSBERRY Dr. Craig Kluever, Thesis Supervisor MAY 2015 The undersigned, appointed by the dean of the Graduate School, have examined the thesis entitled CRUISE FLIGHT OPTMIZATION OF A COMMERCIAL AIRCRAFT WITH WINDS presented by Stephen Ansberry, a candidate for the degree of Master of Science, and hereby certify that, in their opinion, it is worthy of acceptance. Professor Craig Kluever Professor Roger Fales Professor Carmen Chicone ACKNOWLEDGEMENTS I would like to thank Dr. Kluever for his help and guidance through this thesis. I would like to thank my other panel professors, Dr. Chicone and Dr. Fales for their support. I would also like to thank Steve Nagel for his assistance with the engine theory and Tyler Shinn for his assistance with the computer program. ii TABLE OF CONTENTS ACKNOWLEDGEMENTS………………………………...………………………………………………ii LIST OF FIGURES………………………………………………………………………………………..iv LIST OF TABLES…………………………………………………………………………………….……v SYMBOLS....................................................................................................................................................vi ABSTRACT……………………………………………………………………………………………...viii 1. INTRODUCTION.....................................................................................................................................1