LP1 aircraft LS1 engine first prop run
The LP1 experimental aircraft. First prop run at zero thrust setting.
Variable Pitch Propfan circa 1981 NASA Lewis Research Center (from "Futurepath")
more at http://scitech.quickfound.net/ "The video presents material concerning Advanced turboprop programs." Public domain film from NASA, slightly cropped to remove uneven edges, with the aspect ratio corrected, and mild video noise reduction applied. The soundtrack was also processed with volume normalization, noise reduction, clipping reduction, and/or equalization (the resulting sound, though not perfect, is far less noisy than the original). http://creativecommons.org/licenses/by-sa/3.0/ http://en.wikipedia.org/wiki/turboprop A turboprop engine is a type of turbine engine which drives an aircraft propeller using a reduction gear. The gas turbine is designed specifically for this application, with almost all of its output being used to drive the propeller. The engine's Exhaust gases contain little energy compared to a jet engine and play only a minor role in the propulsion of the aircraft. The propeller is coupled to the turbine through a reduction gear that converts the high RPM, low torque output to low RPM, high torque. The propeller itself is normally a constant speed (variable pitch) type similar to that used with larger reciprocating aircraft engines. turboprop engines are generally used on small subsonic aircraft, but some aircraft outfitted with turboprops have cruising speeds in excess of 500 kt (926 km/h, 575 mph). Large military and civil aircraft, such as the Lockheed L-188 Electra and the Tupolev Tu-95, have also used turboprop power. The Airbus A400M is powered by four Europrop TP400 engines, which are the third most powerful turboprop engines ever produced, after the Kuznetsov NK-12 and Progress D-27. In its simplest form a turboprop consists of an intake, compressor, combustor, turbine, and a propelling nozzle. Air is drawn into the intake and compressed by the compressor. Fuel is then added to the compressed air in the combustor, where the fuel-air mixture then combusts. The hot combustion gases expand through the turbine. Some of the power generated by the turbine is used to drive the compressor. The rest is transmitted through the reduction gearing to the propeller. Further expansion of the gases occurs in the propelling nozzle, where the gases Exhaust to atmospheric pressure. The propelling nozzle provides a relatively small proportion of the thrust generated by a turboprop. turboprops are very efficient at flight speeds below 725 km/h (450 mph; 390 knots) because the jet velocity of the propeller (and Exhaust) is relatively low. Due to the high price of turboprop engines, they are mostly used where high-performance short-takeoff and landing (STOL) capability and efficiency at modest flight speeds are required. The most common application of turboprop engines in civilian aviation is in small commuter aircraft, where their greater reliability than reciprocating engines offsets their higher initial cost. turboprop airliners now operate at near the same speed as small turbofan-powered aircraft but burn two-thirds of the fuel per passenger. However, compared to a turbojet (which can fly at high altitude for enhanced speed and fuel efficiency) a propeller aircraft has a much lower ceiling. turboprop-powered aircraft have become popular for bush airplanes such as the Cessna Caravan and Quest Kodiak as jet fuel is easier to obtain in remote areas than is aviation-grade gasoline (avgas)... http://en.wikipedia.org/wiki/Propfan A propfan is a type of aircraft engine related in concept to both the turboprop and turbofan, but distinct from both. The engine uses a gas turbine to drive an unshielded propeller like a turboprop, but the propeller itself is designed with a large number of short, highly twisted blades, similar to a turbofan's bypass compressor. For this reason, the propfan has been variously described as an "unducted fan" or an "ultra-high-bypass (UHB) turbofan". In technical papers it is described as "a small diameter, highly loaded multiple bladed variable pitch propulsor having swept blades with thin advanced airfoil sections, integrated with a nacelle contoured to retard the airflow through the blades thereby reducing compressibility losses and designed to operate with a turbine engine and using a single stage reduction gear resulting in high performance." The design is intended to offer the speed and performance of a turbofan, with the fuel economy of a turboprop. The propfan concept was first revealed by Carl Rohrbach and Bruce Metzger of the Hamilton Standard Division of United Technologies in 1975 and was patented by Robert Cornell and Carl Rohrbach of Hamilton Standard in 1979. Later work by General Electric on similar propulsors was done under the name unducted fan, which was a modified turbofan engine, with the fan placed outside the engine nacelle on the same axis as the compressor blades...
Ravin 500 w/LS1 Corvette Engine
913RA installed with an LS1 Corvette Engine. Shot in Coleman, TX. email email@example.com for more details on performance or visit www.ravinair.com or call at 361-288-4558
Continental Motors, Continental 0 200 D light sport aircraft engine.
http://www.sportaviationmagazine.com -- Continental Motors - Dan Johnson gives us a quick look at the Continental 0-200D, light sport aircraft engine from Continental Motors during the U.S. Sport Aviation Expo, held at the Sebring Regional Airport Sebring Florida. Continental Motors Introduces the 199 Pound O200 Lightweight Engine July 6, 2009 (Mobile, AL) Teledyne Continental Motors (TCM) today introduces its O200 Lightweight Engine for sale to the Piston Aircraft market. The O200 Lightweight Engine line is the first American Made Aviation Piston engine purpose-built for the Light Sport and Kit Aircraft markets. Continental Motors is pleased to continue delivering innovation with its products said Rhett Ross, President of Teledyne Continental Motors. The O200 Lightweight Engine offers aircraft builders a certified and pedigreed engine that is lighter in weight without compromising performance, durability or service life Ross concluded. Sporting identical dimensions to the O200A, the O200 Lightweight Engine weighs in at a slim 199-pound dry weight and comes complete with starter, ignition, and fuel systems. Additional features include light weight cylinders, lightweight precision balanced crankshaft, sprocket propeller flange, weight matched connecting rods, and numerous additional features. As an added incentive to builders considering an O200 Lightweight Engine, TCM will accept any aviation engine core in the 85 - 115 horsepower range regardless of manufacturer. The engine need only be a complete and operable aviation engine. Details and limitations are available on TCMs website. Web Site:www.continentalmotors.aero/experimental eMail:firstname.lastname@example.org Address: 2039 Broad Street City: Mobile, AL 36615 USA Phone: (800) 718-3411 (251) 438-3411 http://www.sportaviationexpos.com http://youtu.be/BTOekhTjz10 Video and Audio content is Copyright © Sport Aviation Magazine. This video and audio material may not be reproduced in any form (except as an embedded video on any other website), without written permission. Related Search terms. aircraft engines,four stroke aircraft engines,experimental aircraft engines,liquid cooled aircraft engines,direct drive aircraft engines,100 HP aircraft engines,