The Renault 100 hp V-12 engine was development from an earlier 90 hp Renault V-12. The main change was the increased bore size of 96 mm instead of 90 mm in the 90 hp engine. Otherwise the general design of the engine was left relatively unchanged, and like its predecessor its general construction was derivative of the air-cooled Renault V-8 engines of the time, such as the 60 hp V-8 type.
The V-12 engine had its two rows of cylinders angled at 60 degree to each other and had a cylinder bore of 96 mm and a stroke of 140 mm. The cylinders and cylinder heads were separate cast-iron pieces with cast fins for air-cooling. The cylinder head was tightened to the cylinder with a copper-asbestos washer, and then secured by a cross-shaped clamp which was bolted to the crankcase with four long studs.[2] Airflow for cooling the cylinders was generated with a fan driven from the rear end of the crankshaft. The fan was blowing air into the sheet metal enclosed chamber between the two rows of cylinders, which then left the enclosure through the narrow spaces between the cylinders, passing through the cylinder's cooling-fins.
Renault 100 hp V-12 engine, cross section
A single camshaft was situated between the two rows of cylinders and operates the inlet and exhaust valves of both cylinder rows, with each valve operated by a separate cam on the camshaft. The inlet and exhaust valves sat vertically opposed in a lateral pocket of the cylinder head on the side of the combustion chamber, with the inlet valve situated below the exhaust valve. The inlet valve was operated directly from the camshaft via a tappet, whereas the exhaust valve was operated via a push rod and a rocker lever. The propeller was mounted directly on the camshaft, which was driven from the crankshaft via reduction gearing consisting of spur gears.
The lower part of the crankcase served as an oil reservoir. A pressurized oil lubrication system was fed by a gear pump located on the lowest point of the crankcase. The oil pump was driven over a vertical shaft from the camshaft via helical gears.[3] The crankshaft was supported by five plain intermediate bearings and two outer ball bearings. Contrary to their V-8 predecessors, the V-12 engines had master-and-slave connecting rods instead of the side-by-side placement of the connecting rods on the same crank journal.[4] This design was kept on the later Renault 80 hp V-8 and Renault 130 hp V-12 aircraft engines. The pistons were made of steel and were fitted with three cast iron rings.
A dual carburetor was fitted on one side of the crankcase, with each barrel of the carburetor feeding one cylinder row.[4] Ignition was supplied by two Bosch magnetos, with each magneto separately serving one cylinder row. The two magnetos were mounted transversely on the top of camshaft on the propeller end. The drive shafts of the magnetos were joined together and driven from the camshaft via helical gears.[3]
The engine was said to produce up to 110 hp at 1800 rpm.[4]
Angle, Glenn Dale (1921). Airplane Engine Encyclopedia: An Alphabetically Arranged Compilation Of All Available Data On The World's Airplane Engines. Otterbein Press. p. 414. OL 23525261M.
Vorreiter, Ansbert (1914). "5e Exposition Internationale de Locomotion Aerienne vom 5.-25. Dez. 1913". Zeitschrift für Flugtechnik und Motorluftschiffahrt, 5. Jahrgang, 1914 (in German). München und Berlin: R. Oldenbourg: 67–69, 82. OCLC 1606129.
"Le nouveau 100 HP Renault". L'Aérophile (in French). Paris. 1 October 1912. pp. 443-444.
Mirguet, Henri (15 September 1912). "Les enseignements de Saint-Malo". L'Aérophile (in French). Paris. pp. 418-419.
Fouqueux (1914). "Les "Renault"". L'Aviation et l'Automobilisme Militaires (in French). Paris. pp. 71-73.
Huth, Fritz (1920). Motoren für Flugzeuge und Luftschiffe. Bibliothek für Luftschiffahrt und Flugtechnik,Bd. 14 (in German) (3rd ed.). Berlin: R. C. Schmidt & co. OCLC 2116726.
External linksedit
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Renault 100 hp V-12 engine installation (Gallica - BnF)
Astra seaplane with Renault V-12 engine (Canada Aviation & Space Museum/Corbis via Getty Images)
April 09, 2024
renault, renault, aircraft, engine, from, 1912, twelve, cylinder, cooled, engine, built, french, renault, company, renault, hprenault, hptype, piston, inline, aero, enginenational, origin, francemanufacturer, renaultfirst, 1912, number, built, 35developed, fro. The Renault 100 hp or 12B aircraft engine from 1912 was a twelve cylinder air cooled 60 vee engine built by the French Renault company Renault 100 hpRenault 100 hpType Piston inline aero engineNational origin FranceManufacturer RenaultFirst run c 1912 1 Number built 35Developed from Renault 90 hpDeveloped into Renault 80 hp Renault 130 hp Contents 1 Design and development 2 Applications 3 Specifications Renault 100 hp 3 1 General characteristics 3 2 Components 3 3 Performance 4 See also 5 References 5 1 Notes 5 2 Bibliography 6 External linksDesign and development edit nbsp Renault 100 hp V 12 engine longitudinal sectionThe Renault 100 hp V 12 engine was development from an earlier 90 hp Renault V 12 The main change was the increased bore size of 96 mm instead of 90 mm in the 90 hp engine Otherwise the general design of the engine was left relatively unchanged and like its predecessor its general construction was derivative of the air cooled Renault V 8 engines of the time such as the 60 hp V 8 type The V 12 engine had its two rows of cylinders angled at 60 degree to each other and had a cylinder bore of 96 mm and a stroke of 140 mm The cylinders and cylinder heads were separate cast iron pieces with cast fins for air cooling The cylinder head was tightened to the cylinder with a copper asbestos washer and then secured by a cross shaped clamp which was bolted to the crankcase with four long studs 2 Airflow for cooling the cylinders was generated with a fan driven from the rear end of the crankshaft The fan was blowing air into the sheet metal enclosed chamber between the two rows of cylinders which then left the enclosure through the narrow spaces between the cylinders passing through the cylinder s cooling fins nbsp Renault 100 hp V 12 engine cross sectionA single camshaft was situated between the two rows of cylinders and operates the inlet and exhaust valves of both cylinder rows with each valve operated by a separate cam on the camshaft The inlet and exhaust valves sat vertically opposed in a lateral pocket of the cylinder head on the side of the combustion chamber with the inlet valve situated below the exhaust valve The inlet valve was operated directly from the camshaft via a tappet whereas the exhaust valve was operated via a push rod and a rocker lever The propeller was mounted directly on the camshaft which was driven from the crankshaft via reduction gearing consisting of spur gears The lower part of the crankcase served as an oil reservoir A pressurized oil lubrication system was fed by a gear pump located on the lowest point of the crankcase The oil pump was driven over a vertical shaft from the camshaft via helical gears 3 The crankshaft was supported by five plain intermediate bearings and two outer ball bearings Contrary to their V 8 predecessors the V 12 engines had master and slave connecting rods instead of the side by side placement of the connecting rods on the same crank journal 4 This design was kept on the later Renault 80 hp V 8 and Renault 130 hp V 12 aircraft engines The pistons were made of steel and were fitted with three cast iron rings A dual carburetor was fitted on one side of the crankcase with each barrel of the carburetor feeding one cylinder row 4 Ignition was supplied by two Bosch magnetos with each magneto separately serving one cylinder row The two magnetos were mounted transversely on the top of camshaft on the propeller end The drive shafts of the magnetos were joined together and driven from the camshaft via helical gears 3 The engine was said to produce up to 110 hp at 1800 rpm 4 Applications editAstra C M hydroplane concours de Saint Malo 1912 1 5 Sanchez Besa biplane concours de Saint Malo 1912 5 Specifications Renault 100 hp edit nbsp Renault 100 hp V 12 engine dimensioned drawingData from Angle 2 Huth 6 General characteristics Type 12 cylinder 60 degree Vee air cooled in line piston engine Bore 96 mm 3 780 in Stroke 140 mm 5 512 in Length 1 430 mm 56 3 in Width 820 mm 32 3 in Height 1 003 mm 39 5 in Dry weight 290 kg 639 lb Components Cooling system Air cooled Reduction gear 0 5 1Performance Power output 100 hp at 1 800 rpmSee also editRelated development Renault 70 hpRelated lists List of aircraft enginesReferences editNotes edit a b L Aerophile 1 October 1912 pp 443 444 a b Angle 1921 p 414 a b Vorreiter 1914 p 82 a b c L Aviation et l automobilisme militaires revue mensuelle des progres scientifiques appliques a la Defense nationale March 1914 pp 71 73 a b L Aerophile 15 September 1912 pp 418 419 Huth 1920 pp 151 153 Bibliography edit Angle Glenn Dale 1921 Airplane Engine Encyclopedia An Alphabetically Arranged Compilation Of All Available Data On The World s Airplane Engines Otterbein Press p 414 OL 23525261M Vorreiter Ansbert 1914 5e Exposition Internationale de Locomotion Aerienne vom 5 25 Dez 1913 Zeitschrift fur Flugtechnik und Motorluftschiffahrt 5 Jahrgang 1914 in German Munchen und Berlin R Oldenbourg 67 69 82 OCLC 1606129 Le nouveau 100 HP Renault L Aerophile in French Paris 1 October 1912 pp 443 444 Mirguet Henri 15 September 1912 Les enseignements de Saint Malo L Aerophile in French Paris pp 418 419 Fouqueux 1914 Les Renault L Aviation et l Automobilisme Militaires in French Paris pp 71 73 Huth Fritz 1920 Motoren fur Flugzeuge und Luftschiffe Bibliothek fur Luftschiffahrt und Flugtechnik Bd 14 in German 3rd ed Berlin R C Schmidt amp co OCLC 2116726 External links edit nbsp Wikimedia Commons has media related to Renault 100 hp Renault 100 hp V 12 engine installation Gallica BnF Astra seaplane with Renault V 12 engine Canada Aviation amp Space Museum Corbis via Getty Images Retrieved from https en wikipedia org w index php title Renault 100 hp V 12 amp oldid 1191869212, wikipedia, wiki, book, books, library,
