Induction & Fuel Metering
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Type Certificate Holder Record Teledyne Continental Motors Ownership & Name Change As of April 19, 2011 (Continental Motors, Inc.)
DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E-233 Revision 18 CONTINENTAL C75-8, -8F, -8FH, -8FHJ, -8FJ, -8J C75-12, -12F, -12FH, -12FHJ, -12FJ, -12J C75-12B, -12BF, -12BFH C75-15, -15F C85-8, -8F, -8FHJ, -8FJ, -8J C85-12, -12F, -12FH, -12FHJ, -12FJ, -12J C85-14F C85-15, -15F November 1, 2011 TYPE CERTIFICATE DATA SHEET NO. E-233 Engines of models described herein conforming with this data sheet (which is part of type certificate No. 233) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Civil Air Regulations provided they are installed, operated and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. Type Certificate Holder Continental Motors Mobile, Alabama 36601 Type Certificate Holder Record Teledyne Continental Motors Ownership & name change as of April 19, 2011 (Continental Motors, Inc.) Model C75-8 C75-12, -15 C85-8 C85-12, -14, -15 Type 4H0A - - - - - - Rating, ICAO or ARDC standard atmosphere Max. continuous hp., r.p.m., full throttle 75-2275 - - 85-2575 - - at sea level pressure altitude Takeoff hp., 5 min., r.p.m. full throttle at 75-2275 - - 85-2575 - - sea level pressure altitude (87-2650 for -J, -FHJ and -FJ models only) Fuel (min. grade aviation gasoline) 73 - - - - - - Lubricating oil, ambient temperature Oil Grade Below 40°F. SAE 20 - - - - - - Above 40°F. SAE 40 - - - - - - Bore and stroke, in. 4.062 x 3.625 - - - - - - Displacement, cu. in. 188 - - - - - - Compression ratio 6.3:1 - - - - - - Weight (dry), lb. -
Spark Plug Condition Chart
Spark Plug Condition Chart Normal Mechanical Damage Oil Fouled May be caused by a foreign object that Too much oil is entering the combustion has accidentally entered the combus- Combustion deposits are slight chamber. This is often caused by piston tion chamber. When this condition is and not heavy enough to cause rings or cylinder walls that are badly discovered, check the other cylinders to any detrimental effect on engine worn. Oil may also be pulled into the prevent a recurrence, since it is possi- performance. Note the brown to chamber because of excessive clear- ble for a small object to "travel" from greyish tan color, and minimal ance in the valve stem guides. If the one cylinder to another where a large amount of electrode erosion which PCV valve is plugged or inoperative it degree of valve overlap exists. This clearly indicates the plug is in the can cause a build-up of crankcase pres- condition may also be due to improper correct heat range and has been sure which can force oil and oil vapors reach spark plugs that permit the piston operating in a "healthy" engine. past the rings and valve guides into the to touch or collide with the firing end. combustion chamber. Overheated Insulator Glazing Pre-Ignition A clean, white insulator firing tip and/or excessive electrode ero- Usually one or a combination of several sion indicates this spark plug con- Glazing appears as a yellowish, var- dition. This is often caused by over engine operating conditions are the nish-like color. This condition indicates prime causes of pre-ignition. -
Certificated Aircraft Engines
CERTIFICATED AIRCRAFT ENGINES SSP1101 DECEMBER 2013 652 Oliver Street Williamsport, PA 17701 U.S.A. Phone: Main OfficeU.S. and Canada Toll Free +1 (800) 2583279 Direct +1 (570) 3236181 Sales Department +1 (570) 3277278 Facsimile +1 (570) 3277101 Visit us on the World Wide Web at: http://www.lycoming.com ©2013 Avco Corporation All Rights Reserved. Lycoming Engines is a division of Avco Corporation. TABLE OF CONTENTS PISTON CERTIFICATED ENGINES – (4) Four Cylinder Series ....................................................................................................................................................... 1 (6) Six Cylinder Series ....................................................................................................................................................... 16 (8) Eight Cylinder Series .................................................................................................................................................... 32 PISTON ENGINE INSTALLATIONS (4) Four Cylinder Installations............................................................................................................................................ 33 (6) Six Cylinder Installations.............................................................................................................................................. 42 TURBOCHARGED .................................................................................................................................................... 46 GEARED................................................................................................................................................................... -
UAT-ARC Final Report
Unleaded AVGAS Transition Aviation Rulemaking Committee FAA UAT ARC Final Report Part I Body Unleaded AVGAS Findings & Recommendations 17 February 2012 UAT ARC Final Report – Part I Body February 17, 2012 Table of Contents List of Figures …………………………………………………………………………… 6 Executive Summary……………………………………………………………………… 8 1. Background …………………..……………………………………………………. 11 1.1. Value of General Aviation………………………………………………… 11 1.2. History of Leaded Aviation Gasoline…………………………………….. 13 1.3. Drivers for Development of Unleaded Aviation Gasoline……………… 14 2. UAT ARC Committee ……………………………………………………………… 16 2.1. FAA Charter……………………………………………………………….. 16 2.2. Membership ………………..…………………………………………….. 17 2.3. Meetings, Telecons, & Deliberations…………….……………………… 17 3. UAT ARC Assessment of Key Issues…………………………………………… 18 3.1. Summary of Key Issues Affecting Development & Transition to an Unleaded AVGAS…………………………………………………………….. 18 3.1.1. General Issues……………………………………………………… 18 3.1.2. Market & Economic Issues………………………………………… 18 3.1.3. Certification & Qualification Issues……………………………….. 18 3.1.4. Aircraft & Engine Technical Issues………………………………. 19 3.1.5. Production & Distribution Issues………………………………….. 19 3.1.6. Environment & Toxicology Issues………………………………… 19 3.2. General Issues – Will Not Be A Drop-In…………………………….……. 20 3.2.1. Drop-In vs. Transparent……………..……………………………. 20 3.2.2. Historic Efforts Focused on Drop-In…………………………….. 21 3.2.3. No Program to Support Development of AVGAS………………. 21 3.3. Market & Economic Issues…………………….. …………………………. 22 3.3.1. Market Forces……………………………………………………… 22 3.3.2. Aircraft Owner Market Perspective……………………………….. 23 3.3.3. Fleet Utilization …………..…………………………………………. 24 3.3.4. Design Approval Holder (DAH) Perspective ……………………. 25 3.4. Certification & Qualification Issues…………………………………………. 26 3.4.1. FAA Regulatory Structure…….……………………………………. 26 3.4.2. ASTM and FAA Data Requirements………………..……………. 27 3.4.3. FAA Certification Offices…………………………………………… 28 3.4.4. -
General Aviation Aircraft Propulsion: Power and Energy Requirements
UNCLASSIFIED General Aviation Aircraft Propulsion: Power and Energy Requirements • Tim Watkins • BEng MRAeS MSFTE • Instructor and Flight Test Engineer • QinetiQ – Empire Test Pilots’ School • Boscombe Down QINETIQ/EMEA/EO/CP191341 RAeS Light Aircraft Design Conference | 18 Nov 2019 | © QinetiQ UNCLASSIFIED UNCLASSIFIED Contents • Benefits of electrifying GA aircraft propulsion • A review of the underlying physics • GA Aircraft power requirements • A brief look at electrifying different GA aircraft types • Relationship between battery specific energy and range • Conclusions 2 RAeS Light Aircraft Design Conference | 18 Nov 2019 | © QinetiQ UNCLASSIFIED UNCLASSIFIED Benefits of electrifying GA aircraft propulsion • Environmental: – Greatly reduced aircraft emissions at the point of use – Reduced use of fossil fuels – Reduced noise • Cost: – Electric aircraft are forecast to be much cheaper to operate – Even with increased acquisition cost (due to batteries), whole-life cost will be reduced dramatically – Large reduction in light aircraft operating costs (e.g. for pilot training) – Potential to re-invigorate the GA sector • Opportunities: – Makes highly distributed propulsion possible – Makes hybrid propulsion possible – Key to new designs for emerging urban air mobility and eVTOL sectors 3 RAeS Light Aircraft Design Conference | 18 Nov 2019 | © QinetiQ UNCLASSIFIED UNCLASSIFIED Energy conversion efficiency Brushless electric motor and controller: • Conversion efficiency ~ 95% for motor, ~ 90% for controller • Variable pitch propeller efficiency -
Diesel and Fuel-Oil Engines
HdiiUiiat uuioTAt* VI i nPicrence moK not to do AUG 2 ^ : , CuKCH JlUili lilO L, iDi slil CS102E-42 Jf' Engines, Diese! and fuei-oil (export classifications) U. S. DEPARTMENT OF COMMERCE JESSE H. JONES, Secretary NATIONAL BUREAU OF STANDARDS LYMAN J. BRIGGS, Director DIESEL AND FUEL-OIL ENGINES (Export Classifications) COMMERCIAL STANDARD CS102E-42 Effective Date for New Production from October 30, 1942 A RECORDED VOLUNTARY STANDARD OF THE TRADE UNITED STATES GOVERNMENT PRINTING OFFICE WASHINGTON : 1942 For sale by the Superintendent of Documents, Washington, D. C. Price 10 cents . U. S. Department of Commerce National Bureau of Standard? PROMULGATION of COMMERCIAL STANDARD CS102E-42 for DIESEL AND FUEL-OIL ENGINES (Export Classifications) On January 30, 1942, at the instance of the Diesel Engine Manu- facturers’ Association, a conference of representative manufacturers adopted a recommended commercial standard for Diesel and fuel -oil engines (export classifications). Those concerned have since accepted and approved the standard as shown herein for promulgation by the U. S. Department of Commerce, through the National Bureau of Standards. The standard is effective for new production from October 30, 1942. Promulgation recommended I. J. Fairchild, Chieff Division of Trade Standards, Promulgated. Lyman J. Briggs, Director^ National Bureau of Standards, Promulgation approved. Jesse H. Jones, Secretary of Commerce. II DIESEL AND FUEL-OIL ENGINES (Export Classifications) COMMERCIAL STANDARD CS102E-42 PARTS Page 1. Nomenclature and definitions.. ' 1 2. Slow- and medium-speed stationary Diesel engines 7 3. Slow- and medium-speed marine Diesel engines 13 4. Small, medium- and high-speed stationary, marine, and portable Diesel engines 19 5. -
Water/Methanol Injection: Frequently Asked Questions
Water/Methanol Injection: Frequently Asked Questions Water/methanol injection is nothing new. It has been used as far back as World War II to help power German fighter planes. Yet it never seemed to catch on as a mainstream power adder in the hot rodding world—until recent years. Many companies are now offering easy to install water/methanol injections systems for affordable prices. Available for naturally aspirated or forced induction gasoline and diesel applications, these systems inject a roughly 50/50 mixture of methanol and water into the engine using a high-pressure pump. This magical mixture allows for more ignition timing, increases boost capability in supercharged or turbocharged applications, lowers air intake temperature, and provides an additional source of very high-octane fuel—all without increasing the chance of damaging detonation. Water injection systems are predominantly useful in forced induction (turbocharged or supercharged), internal combustion engines. Only in extreme cases such as very high compression ratios, very low octane fuel or too much ignition advance can it benefit a normally aspirated engine. The system has been around for a long time since it was already used in some World War II aircraft engines, which allowed them to produce more power and therefore fly at higher altitudes. A water injection system works similarly to a fuel injection system only it injects water instead of fuel. Water injection is not to be confused with water spraying on the intercooler's surface, water spraying is much less efficient and far less sophisticated. A turbocharger or supercharger essentially compresses the air going into the engine in order to force more air than would be possible with the atmospheric pressure. -
Installation Instructions SUPERCHARGER ‘90-’93 Mazda Miata Part# 999-000, 999-005, 999-010, 999-015
Installation Instructions SUPERCHARGER ‘90-’93 Mazda Miata Part# 999-000, 999-005, 999-010, 999-015 440 Rutherford St. P.O. Box 847 Goleta, CA 93117 1-888-888-4079 • FAX 805-692-2523 • www.jacksonracing.com INSTALLATION TIME IN AS LITTLE AS 4 HOURS regularly (every 3000 miles or so), you should FOR EXPERIENCED MECHANICS, AROUND 5 have no trouble. If in doubt, check your engine’s TO 6 HOURS FOR “OCCASIONAL” MECHAN- compression. You should have at least 135psi of ICS. compression in each cylinder with no more than a 10% variance between any two cylinders or with a TOOLS REQUIRED: 3/8” Drive Socket set w/ 10% increase in any cylinder after a tablespoon of 17mm, 14mm, 13mm, 12mm, 10mm & 8mm sock- oil is poured in. Your cooling system should be up ets; Deep sockets (14mm or 9/16”, 10mm): to par (50/50 mix of water and new coolant). Phillips and Standard screwdriver, 10mm, 12mm, Basically, if you have a good engine, it will be very and 17mm open end wrench; 5mm Allen wrench happy with this supercharger. with a 3/8” drive; paper clip; a box to store your OLD PARTS in. A 1/4” drive socket set will be use- BEFORE INSTALLING THIS SYSTEM: ful with some of the tight working areas. A timing A. Drive your fuel tank empty and refill with 92 light will be needed to set the ignition timing. Octane major brand gasoline. If you can only find 91 Octane, see step #3 under “Adjustments” at the A NOTE ON ADDING A SUPERCHARGER TO end of these instructions. -
! National Advisory Committee for Aeronautics
! . \ i NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS TECHNICAL NOTE No. 1374 EXPERIMENTAL STUDIES OF THE KNOCK - LIlvITTED BLENDIDG CHARACTERISTICS OF AVIATION FUELS II - INVESTIGATION OF LEADED PARAFFINIC FUELS IN AN AIR-COOLED CYLrnDER By Jerrold D. Wear and Newell D. Sanders Flight Propulsion Research Laboratory Cleveland, Ohio Washington July 1947 , \ I NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS TN 1374 EXPERIMENTAL STUDIES OF THE KNOCK-LIMITED BLENDING CH.~~ACTERISTICS OF AVIATION FUELS II - INVESTIGATION OF LEADED PARAFFINIC FUELS IN ~~ AIR-COOLED CYLINDER By Jerrold D. Wear and. Newell D. Sanders SUMMARY The relation between knock limit and blend composition of selected aviation fuel components individually blended with virgin base and ''lith alkylate was determined in a full-scale air-cooled aircraft-·engine cylinder. In addition the follow ing correlations were examined: (a) The knock-·limited performance of a full -scale engine at lean-mixture operation plotted against the knock-limited perform ance of the engine at rich-mixture operation for a series of fuels (b) The knock-limited performance of a full-scale engine at rich-mixture operation plotted against the knock-limited perform ance at rich-mixture operation of a small-scale engine for a series of fuels In each case the following methods of specifying the knock limi ted perfOl'IDanCe of the engine were investigated: (l) Knock·-limited indicated mean effective pressure (2) percentage of S-4 plus 4 ml T~~ per gallon in M-4 plus 4 ml TEL per gallon to give an equal knock-limited indicated mean effective pressure (3) Ratio of indicated mean effective pressure of test fuel ~o indicated mean effective pressure of clear S-4 reference fuel, all other conditions being the same . -
Water Injection on Commercial Aircraft to Reduce Airport Nitrogen Oxides
NASA/TM—2010-213179 Water Injection on Commercial Aircraft to Reduce Airport Nitrogen Oxides David L. Daggett and Lars Fucke Boeing Commercial Airplane, Seattle, Washington Robert C. Hendricks Glenn Research Center, Cleveland, Ohio David J.H. Eames Rolls-Royce Corporation, Indianapolis, Indiana March 2010 NASA STI Program . in Profile Since its founding, NASA has been dedicated to the • CONFERENCE PUBLICATION. Collected advancement of aeronautics and space science. The papers from scientific and technical NASA Scientific and Technical Information (STI) conferences, symposia, seminars, or other program plays a key part in helping NASA maintain meetings sponsored or cosponsored by NASA. this important role. • SPECIAL PUBLICATION. Scientific, The NASA STI Program operates under the auspices technical, or historical information from of the Agency Chief Information Officer. It collects, NASA programs, projects, and missions, often organizes, provides for archiving, and disseminates concerned with subjects having substantial NASA’s STI. The NASA STI program provides access public interest. to the NASA Aeronautics and Space Database and its public interface, the NASA Technical Reports • TECHNICAL TRANSLATION. English- Server, thus providing one of the largest collections language translations of foreign scientific and of aeronautical and space science STI in the world. technical material pertinent to NASA’s mission. Results are published in both non-NASA channels and by NASA in the NASA STI Report Series, which Specialized services also include creating custom includes the following report types: thesauri, building customized databases, organizing and publishing research results. TECHNICAL PUBLICATION. Reports of completed research or a major significant phase For more information about the NASA STI of research that present the results of NASA program, see the following: programs and include extensive data or theoretical analysis. -
Reduction of NO Emissions in a Turbojet Combustor by Direct Water
Reduction of NO emissions in a turbojet combustor by direct water/steam injection: numerical and experimental assessment Ernesto Benini, Sergio Pandolfo, Serena Zoppellari To cite this version: Ernesto Benini, Sergio Pandolfo, Serena Zoppellari. Reduction of NO emissions in a turbojet combus- tor by direct water/steam injection: numerical and experimental assessment. Applied Thermal Engi- neering, Elsevier, 2009, 29 (17-18), pp.3506. 10.1016/j.applthermaleng.2009.06.004. hal-00573476 HAL Id: hal-00573476 https://hal.archives-ouvertes.fr/hal-00573476 Submitted on 4 Mar 2011 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. Accepted Manuscript Reduction of NO emissions in a turbojet combustor by direct water/steam in- jection: numerical and experimental assessment Ernesto Benini, Sergio Pandolfo, Serena Zoppellari PII: S1359-4311(09)00181-1 DOI: 10.1016/j.applthermaleng.2009.06.004 Reference: ATE 2830 To appear in: Applied Thermal Engineering Received Date: 10 November 2008 Accepted Date: 2 June 2009 Please cite this article as: E. Benini, S. Pandolfo, S. Zoppellari, Reduction of NO emissions in a turbojet combustor by direct water/steam injection: numerical and experimental assessment, Applied Thermal Engineering (2009), doi: 10.1016/j.applthermaleng.2009.06.004 This is a PDF file of an unedited manuscript that has been accepted for publication. -
An Experimental Study on Performance and Emission Characteristics of a Hydrogen Fuelled Spark Ignition Engine
View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by DSpace@IZTECH Institutional Repository International Journal of Hydrogen Energy 32 (2007) 2066–2072 www.elsevier.com/locate/ijhydene An experimental study on performance and emission characteristics of a hydrogen fuelled spark ignition engine Erol Kahramana, S. Cihangir Ozcanlıb, Baris Ozerdemb,∗ aProgram of Energy Engineering, Izmir Institute of Technology, Urla, Izmir 35430, Turkey bDepartment of Mechanical Engineering, Izmir Institute of Technology, Urla, Izmir 35430, Turkey Received 2 August 2006; accepted 2 August 2006 Available online 2 October 2006 Abstract In the present paper, the performance and emission characteristics of a conventional four cylinder spark ignition (SI) engine operated on hydrogen and gasoline are investigated experimentally. The compressed hydrogen at 20 MPa has been introduced to the engine adopted to operate on gaseous hydrogen by external mixing. Two regulators have been used to drop the pressure first to 300 kPa, then to atmospheric pressure. The variations of torque, power, brake thermal efficiency, brake mean effective pressure, exhaust gas temperature, and emissions of NOx, CO, CO2, HC, and O2 versus engine speed are compared for a carbureted SI engine operating on gasoline and hydrogen. Energy analysis also has studied for comparison purpose. The test results have been demonstrated that power loss occurs at low speed hydrogen operation whereas high speed characteristics compete well with gasoline operation. Fast burning characteristics of hydrogen have permitted high speed engine operation. Less heat loss has occurred for hydrogen than gasoline. NOx emission of hydrogen fuelled engine is about 10 times lower than gasoline fuelled engine.