CARTRIDGE STARTERS WORDS: JAMES KIGHTLY ARTWORK: IAN BOTT He Critical Elements for Six Shells Ready to Be Used
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Airport Rules and Regulations, Rev
AIRPORT RULES and REGULATIONS AVI-POL-506 – DAL Airport Rules and Regulations, Rev. 2 (10/15/17) PURPOSE: The purpose of this manual is to publish Rules and Regulations for airport- approved operating procedures, terminal, safety and security requirements at in affect at Dallas Love Field. Nothing in these Rules and Regulations shall limit or constrain the legitimate authority of the Airport Director or designee. SCOPE: Dallas Love Field is owned and operated by the City of Dallas, Texas. These Airport Rules and Regulations apply to all airport employees (including City staff), tenant organizations, airlines and governmental organizations that work at, conduct business at, lease property, or otherwise have access to Dallas Love Field. They are put in place, to ensure that employees performing their jobs contribute to the Dallas Love Field goal of providing a safe and efficient airport. Chapter 5, of the Dallas City Code contains current City of Dallas Ordinances pertaining to Aircraft and Airports. Only the pertinent portions of the Chapter are included in these Rules and Regulations. AVI-POL-506 – DAL Airport Rules and Regulations Rev 2 - 10/15/17 Page ii Rules of Interpretation and Construction Wherever these Rules and Regulations refer to “applicable law,” such term shall refer to all present and future federal, state and local statutes, ordinances and regulations and City ordinances applicable to the Person or the Airport or the use thereof and judicial or administrative interpretations thereof, as amended from time to time, including but not limited to Transportation Security Regulations and Security Directives issued from time to time by DHS or TSA, Federal Regulations and Advisory Circulars issued from time to time by the FAA, these Rules and Regulations, Notices to Airmen (“NOTAMs”) and Airport Directives issued by the Department of Aviation from time to time and directions issued by the Air Traffic Control Tower. -
Low Temperature Environment Operations of Turboengines
0 Qo B n Y n 1c AGARD 2 ADVISORY GROUP FOR AEROSPACE RESEARCH & DEVELOPMENT 3 7 RUE ANCELLE 92200 NEUILLY SUR SEINE FRANCE AGARD CONFERENCE PROCEEDINGS 480 Low Temperature Environment Operations of Turboengines (Design and User's Problems) Fonctionnement des Turborkacteurs en Environnement Basse Tempkrature (Problkmes Pos& aux Concepteurs et aux Utilisateurs) processed I /by 'IMs ..................signed-...............date .............. NOT FOR DESTRUCTION - NORTH ATLANTIC TREATY ORGANIZATION I Distribution and Availability on Back Cover AGARD-CP-480 --I- ADVISORY GROUP FOR AEROSPACE RESEARCH & DEVELOPMENT 7 RUE ANCELLE 92200 NEUILLY SUR SEINE FRANCE AGARD CONFERENCE PROCEEDINGS 480 Low Temperature Environment Operations of Turboengines (Design and User's Problems) Fonctionnement des TurborLacteurs en Environnement Basse Tempkrature (Problkmes PoSes aux Concepteurs et aux Utilisateurs) Papers presented at the Propulsion and Energetics Panel 76th Symposium held in Brussels, Belgium, 8th-12th October 1990. - North Atlantic Treaty Organization --q Organisation du Traite de I'Atlantique Nord I The Mission of AGARD According to its Chartcr, the mission of AGARD is to bring together the leading personalities of the NATO nations in the fields of science and technology relating to aerospace for the following purposes: -Recommending effective ways for the member nations to use their research and development capabilities for the common benefit of the NATO community; - Providing scientific and technical advice and assistance to the Military Committee -
The Aircraft Propulsion the Aircraft Propulsion
THE AIRCRAFT PROPULSION Aircraft propulsion Contact: Ing. Miroslav Šplíchal, Ph.D. [email protected] Office: A1/0427 Aircraft propulsion Organization of the course Topics of the lectures: 1. History of AE, basic of thermodynamic of heat engines, 2-stroke and 4-stroke cycle 2. Basic parameters of piston engines, types of piston engines 3. Design of piston engines, crank mechanism, 4. Design of piston engines - auxiliary systems of piston engines, 5. Performance characteristics increase performance, propeller. 6. Turbine engines, introduction, input system, centrifugal compressor. 7. Turbine engines - axial compressor, combustion chamber. 8. Turbine engines – turbine, nozzles. 9. Turbine engines - increasing performance, construction of gas turbine engines, 10. Turbine engines - auxiliary systems, fuel-control system. 11. Turboprop engines, gearboxes, performance. 12. Maintenance of turbine engines 13. Ramjet engines and Rocket engines Aircraft propulsion Organization of the course Topics of the seminars: 1. Basic parameters of piston engine + presentation (1-7)- 3.10.2017 2. Parameters of centrifugal flow compressor + presentation(8-14) - 17.10.2017 3. Loading of turbine blade + presentation (15-21)- 31.10.2017 4. Jet engine cycle + presentation (22-28) - 14.11.2017 5. Presentation alternative date Seminar work: Aircraft engines presentation A short PowerPoint presentation, aprox. 10 minutes long. Content of presentation: - a brief history of the engine - the main innovation introduced by engine - engine drawing / cross-section - -
AIRCRAFT SYSTEMS COURSE FILE III B. Tech II Semester
ERONAUTICAL ENGINEERING MRCET (UGC Autonomous) – – AIRCRAFT SYSTEMS COURSE FILE III B. Tech II Semester (2017-2018) Prepared By Ms. L Sushma, Assoc. Prof Department of Aeronautical Engineering MALLA REDDY COLLEGE OF ENGINEERING & TECHNOLOGY (Autonomous Institution – UGC, Govt. of India) Affiliated to JNTU, Hyderabad, Approved by AICTE - Accredited by NBA & NAAC – A Grade - ISO 9001:2015 Certified) Maisammaguda, Dhulapally (Post Via. Kompally), Secunderabad – 500100, Telangana State, India. III– II B. Tech Aircraft Systems By L SUSHMA I AERONAUTICAL ENGINEERING MRCET (UGC Autonomous) – – MRCET VISION To become a model institution in the fields of Engineering, Technology and Management. To have a perfect synchronization of the ideologies of MRCET with challenging demands of International Pioneering Organizations. MRCET MISSION To establish a pedestal for the integral innovation, team spirit, originality and competence in the students, expose them to face the global challenges and become pioneers of Indian vision of modern society. MRCET QUALITY POLICY. To pursue continual improvement of teaching learning process of Undergraduate and Post Graduate programs in Engineering & Management vigorously. To provide state of art infrastructure and expertise to impart the quality education. III– II B. Tech Aircraft Systems By L SUSHMA II AERONAUTICAL ENGINEERING MRCET (UGC Autonomous) – – PROGRAM OUTCOMES (PO’s) Engineering Graduates will be able to: 1. Engineering knowledge: Apply the knowledge of mathematics, science, engineering fundamentals, -
AEROMOTIVE Part 2
AEROMOTIVE Part 2 What is an aircraft engine? A child might answer, "an engine that's on an aeroplane." Foolish youth! If we skip the radials, rotarys, sleeve valvers, two strokes, diesels, turbines, jets, and rockets, we're left with . the four cycle, internal combustion, spark ignited, piston reciprocating, poppet valvers, in only; aircooled, liquid cooled, inline, opposed, vee, naturally aspirated, and supercharged gasoline consuming variations. These qualifications squeeze the answer into a set of characteristics that appears remarkably like an automotive engine to enthusiastic people. Back To The Basics: We can attempt to equate engine performance in a variety of ways. However, horsepower still seems to be the best method if it is qualified by an accompanying RPM (revolutions/minute). Power output in HP/CID (horsepower/cubic inch displacement) is a standard for most engine nerds but it doesn't reveal much about the drivability (torque) or personality (horsepower curve) of the engine. Torque and horsepower are intimately related even though they are often spoken of as if they were separate entities. I have taught a private engine design and building course for 21 years and it has always been a challenge to get my students to understand the relationship between torque and horsepower. This doesn't surprise me because these two parameters, ostensibly simple, are in fact tricky to relate. I am reluctant to rehash the whole horsepower/torque issue. But, based on conversations I have had with aircraft folks - and automotive folks, for that matter - I perceive the need to establish basic terms. We (“we” meaning us at Sunset Engine Development) are often asked, "what do I want, torque or horsepower?" Trying to explain such abstract concepts on the telephone cannot do the subject justice. -
Napier Sabre Engines Will Be Found on Page L75
STAITDARDIZRD DATA PAGES FOR RECIPROCATIITG EITCTI\ES Standardized data pages are used to present the specifieations of the basic aircraft engines and airhorne auxiliary units described and illustrated in the followirg section of the book. The arrangeme'nt of the data on the standardi zed" data pages is as f ollows : First, there is a concise description of the engine, its construe tion and the major accessories with which it is equipped. Then, in tabular form, there are items such as bore, stroke, displacement (swept vol- ume), compression ratio, overall dimensions, frontal areae total weight and weight per maximum horsepolyer. F'uel and lubricating oiX eonsumptions at cruising output are given in units of weight. The fuel grade and the viscosity of the lubricating oil at 210o F" (100o C) also are specified. Efficiency figures such as maximum power output per unit of dis- placement, maximum polver output per unit of piston area) maximum piston speed and maximum brake mean effective pressure have been ealculated for comparative purposes. Finally, the various horsepower ratings of the engine are given, such as; Take-off rating, or the maxinrum horsepower which it is per- missibil to ,ruJ at sea level and at low altitrdes. flrlilitary (combat) rating, or the maximum horsepower which it is perrnissib]e to use for military purposes at various alti- tudes. fVorrual rating,, or the ntaximum horsepower which the engine can deliver continuously for climh without undue stress" Cruising ratirug, or the maximum horsepo\,ver recommended for continuous operation consistent with reasonable fuel econ- omy. Ern,ergerlcy rating, or the marximum horsepower which it is permissible use a _ to for short period of time in an ernergency. -
19FFL-0023 2-Stroke Engine Options for Automotive Use: a Fundamental Comparison of Different Potential Scavenging Arrangements for Medium-Duty Truck Applications
Citation for published version: Turner, J, Head, RA, Chang, J, Engineer, N, Wijetunge, RS, Blundell, DW & Burke, P 2019, '2-Stroke Engine Options for Automotive Use: A Fundamental Comparison of Different Potential Scavenging Arrangements for Medium-Duty Truck Applications', SAE Technical Paper Series, pp. 1-21. https://doi.org/10.4271/2019-01-0071 DOI: 10.4271/2019-01-0071 Publication date: 2019 Document Version Peer reviewed version Link to publication The final publication is available at SAE Mobilus via https://doi.org/10.4271/2019-01-0071 University of Bath Alternative formats If you require this document in an alternative format, please contact: [email protected] General rights Copyright and moral rights for the publications made accessible in the public portal are retained by the authors and/or other copyright owners and it is a condition of accessing publications that users recognise and abide by the legal requirements associated with these rights. Take down policy If you believe that this document breaches copyright please contact us providing details, and we will remove access to the work immediately and investigate your claim. Download date: 27. Sep. 2021 Paper Offer 19FFL-0023 2-Stroke Engine Options for Automotive Use: A Fundamental Comparison of Different Potential Scavenging Arrangements for Medium-Duty Truck Applications Author, co-author (Do NOT enter this information. It will be pulled from participant tab in MyTechZone) Affiliation (Do NOT enter this information. It will be pulled from participant tab in MyTechZone) Abstract For the opposed-piston engine, once the port timing obtained by the optimizer had been established, a supplementary study was conducted looking at the effect of relative phasing of the crankshafts The work presented here seeks to compare different means of on performance and economy. -
Small Gas Turbines Chapter 2 Fuel Systems
Chapter 2 Fuel Systems A complex part of a typical small gas turbine is the fuel system. Small gas turbines in a similar way to much larger units make high demands on the fuel systems. A typical fuel system is required to start and accelerate the engine, govern or control the engine at one or more running speeds, maintain a given speed under load conditions and in many designs, the engine must be protected against excessive exhaust gas temperatures and compressor surging. All small gas turbines are designed to operate on Jet fuel such as Jet A, Jet A1 and JP4, these fuels are similar to Kerosene. Paraffin is a type of kerosene, as is 28 second heating oil and gas oil. Small engines will run satisfactorily on any of these fuels, tolerance of differing fuels is one of the advantages of the gas turbine engine. As the combustion process is continuous and takes place at constant pressure, there are no problems with detonation or pinking. Detonation or pinking which is associated with piston engines significantly limits their performance. Certain designs of gas turbine intended for specialist stationary applications may be operated on natural gas. Many small engines may be operated on Diesel fuel or Petrol (Gasoline), the basic performance of the engine will be unaffected but prolonged use is not recommended for a number of reasons. Diesel fuel contains sulfur that may deposit itself on components in the fuel system. Certain fuel pump components are often silver-plated which will be damaged by the sulfur content in the fuel. -
AC 00-2.13 Appendix 3
6/15/00 AC 00-2.13 Appendix 3 APPENDIX 3 NUMERICAL LIST OF ADVISORY CIRCULARS Important Notice This Advisory Circular Checklist, AC 00-2, is no longer sent automatically to addresses on free advisory circular mailing lists. Persons not now receiving AC 00-2 but who wish to receive it must specifically request to be placed on the AC 00-2 mailing list (see par. 5 for ordering information). Up to ten copies may be sent to any one address. Persons receiving this edition of AC 00-2 need not request AC 00-2 mailing list service as they have already been transferred to the new list. Q 00-7D (9/20/82) (ANN-130) General State and Regional Disaster Airlift Informs the aviation community of the (SARDA) Planning establishment and content of the United (9/15/98) (ADA-20) States (US). National Aviation Standard for Subject No. 00 Provides officials with guidance to access the Very High Frequency Omnidirectional and utilize a broad range of aviation Radio Range (VOR)/Distance Measuring 00-1.1 resources within the state, when needed to Equipment(DME)/Tactical Air Navigation Government Aircraft Operations support civil emergency operations. (TACAN) Systems. (4/19/95) (AFS -220) Provides guidance on whether particular 00-24B 00-33B government aircraft operations are public Thunderstorms Nickel-Cadmium Battery Operational, aircraft or civil aircraft operations under the (1/20/83) (AFS -400) Maintenance, and Overhaul Practices new statutory definition of “public Describes the hazards of thunderstorms to (7/9/97) (AFS -400) aircraft.” This AC contains FAA’s intended aviation and offers guidance to help prevent Provides guidelines for more reliable nickel- application of key terms in the new accidents caused by thunderstorms. -
Aircraft Propulsion C Fayette Taylor
SMITHSONIAN ANNALS OF FLIGHT AIRCRAFT PROPULSION C FAYETTE TAYLOR %L~^» ^ 0 *.». "itfnm^t.P *7 "•SI if' 9 #s$j?M | _•*• *• r " 12 H' .—• K- ZZZT "^ '! « 1 OOKfc —•II • • ~ Ifrfil K. • ««• ••arTT ' ,^IfimmP\ IS T A Review of the Evolution of Aircraft Piston Engines Volume 1, Number 4 (End of Volume) NATIONAL AIR AND SPACE MUSEUM 0/\ SMITHSONIAN INSTITUTION SMITHSONIAN INSTITUTION NATIONAL AIR AND SPACE MUSEUM SMITHSONIAN ANNALS OF FLIGHT VOLUME 1 . NUMBER 4 . (END OF VOLUME) AIRCRAFT PROPULSION A Review of the Evolution 0£ Aircraft Piston Engines C. FAYETTE TAYLOR Professor of Automotive Engineering Emeritus Massachusetts Institute of Technology SMITHSONIAN INSTITUTION PRESS CITY OF WASHINGTON • 1971 Smithsonian Annals of Flight Numbers 1-4 constitute volume one of Smithsonian Annals of Flight. Subsequent numbers will not bear a volume designation, which has been dropped. The following earlier numbers of Smithsonian Annals of Flight are available from the Superintendent of Documents as indicated below: 1. The First Nonstop Coast-to-Coast Flight and the Historic T-2 Airplane, by Louis S. Casey, 1964. 90 pages, 43 figures, appendix, bibliography. Price 60ff. 2. The First Airplane Diesel Engine: Packard Model DR-980 of 1928, by Robert B. Meyer. 1964. 48 pages, 37 figures, appendix, bibliography. Price 60^. 3. The Liberty Engine 1918-1942, by Philip S. Dickey. 1968. 110 pages, 20 figures, appendix, bibliography. Price 75jf. The following numbers are in press: 5. The Wright Brothers Engines and Their Design, by Leonard S. Hobbs. 6. Langley's Aero Engine of 1903, by Robert B. Meyer. 7. The Curtiss D-12 Aero Engine, by Hugo Byttebier. -
Aviation Rulemaking Advisory Committee
Aviation Rulemaking Advisory Committee Airman Certification System Working Group Interim Recommendation Report August 8, 2018 August 8, 2018 Yvette A. Rose Chair, Aviation Rulemaking Advisory Committee Federal Aviation Administration 800 Independence Avenue, SW Washington, DC 20591 Dear Ms. Rose, On behalf of the Airman Certification System Working Group (ACSWG), we submit the following interim recommendation report to the Aviation Rulemaking Advisory Committee (ARAC) for consideration and implementation. The FAA and the aviation industry have continued its collaborative effort to improve airman training and testing by establishing an integrated, holistic airman certification system that clearly aligns testing with the certification standards, guidance, and reference materials, and maintains that alignment. As part of its ongoing effort, the ACSWG is presenting feedback on draft standards for the Private Pilot Rotorcraft Pilot Helicopter and Instrument Rating – Powered-Lift. Additionally, we have included recommendations on the Aviation Instructor Handbook (FAA-H-8083-9B) and the Helicopter Flying Handbook (FAA-H-8083-21B). Collectively, we recommend and endorse the committee’s transmittal of the working group recommendations to the FAA for further review, incorporation, and execution. We are confident that, by doing so, the safety of aviation will continue to markedly improve. Sincerely, David Oord Susan Parson Eric Crump ARAC Vice-Chair & ACSWG Chair FAA Representative ACSWG Subgroup Lead Senior Director, Regulatory Affairs Flight Standards Service Federal Aerospace Program Director Aircraft Owners and Pilots Association Aviation Administration Polk State College Janeen Kochan, PhD, FRAeS, John “Mac” McWhinney Jackie Spanitz AMT ACS Subgroup Co-chair ACSWG Subgroup Lead ACSWG Subgroup Lead General Human Factors Scientist/Designated Pilot Examiner/ Senior Course Developer Manager Instructor Pilot King Schools, Inc. -
Napier Sabre VII
55° FLIGHT Napier Sabre VII Over 3,000 b.h.p. for Take-off tLowest Specific Weight of Any Pro- duction Piston Engine EGULAR readers of Flight may remember that a octane fuel are no longer burned to produce only hot water, detailed description of the Sabre engine was given which is immediately cooled again; by using regenerative R in the March 23rd, 1944, issue, together with a good dynamometers the power output is used to produce elec- many illustrations, including a special cut-away drawing; tricity for the factory and outside supply, and an example but the subject of that description was the Mk. II, whereas of the output is that if a Sabre is running on a Sunday the latest Sabre is the Mk. VII. (when the factory is not working) the electricity generated Series II engines were developed in three guises, the II, by a single engine is sufficient to supply the entire demand IIA and IIB, in which the boost pressures were progressively from the whole Willesden area and still leave sufficient increased and the power outputs stepped-up from 2,090 over for feeding into the national grid system. to 2,220 and then to 2,420 b.h.p. Weight had also in- creased, but not proportionally, so that specific weight Teetliing Troubles Cured went down respectively from 1.12 to 1.06 until, with the As with all engines developed at high pressure during IIB, it dropped below unity with the value of 0.981b. /b.h.p. the war, teething troubles were experienced with the Sabre.