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V-4 Aviation Turbo Diesel Specifications:
CONFIGURATION |
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upright, inverted, or vertical 90 degree V-4, turbocharged, direct drive, two-stroke diesel with oil pump and external air-oil separator/sump |
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top profile is 3.5 inches higher at the cylinder tops than an IO-360 Lycoming, referenced from the crankshaft |
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engine width under 24 inches |
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COOLING |
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liquid cooled |
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FUEL |
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jet-A, jet-A1,JP-5, JP-8, Diesel #1, Diesel #2,
bio-diesel |
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ELECTRICAL |
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60, 100, or 200 A Alternator |
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28 Volt Starter
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POWER |
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160, 180 and 200 hp models, at 2,700 rpm |
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possible higher horsepower V-4 version |
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FUEL CONSUMPTION |
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BSFC = .39 lb/hp/hr |
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for a 1,000 nm trip in a Velocity at 65% power, it translates to:
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40.9 gal Jet A for the V-4, versus |
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57.3 gal 100LL for Lycoming IO-360 |
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WEIGHT |
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currently about 327 lbs including starter, oil pump, fuel pump, water pump, turbocharger, all internal lines and internal exhaust system |
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RELIABILITY |
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lower part count and fewer potential leakage points than the current 4-cylinder gasoline-powered aircraft engines:
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no cam shaft or valve train |
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no head gaskets to blow and no head bolts |
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fully doweled, four bolt main construction (12 studs) |
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inherently stout block and compact V-4 design |
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no ignition system |
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OTHER DESIGN CHARACTERISTICS |
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single-lever power control |
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configured for fixed or variable pitch propellers (propeller governor pad provided) |
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vacuum pump pad provided |
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limited operation at reduced power without coolant |
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limp-home capability without turbocharger, supplying approximately 100 hp with backup air |
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no electromagnetic interference at normal operating altitudes |
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provisions for cold weather starting |
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TBO of 2,000 hours (estimated) |
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