Mercedes D.IVa

The Mercedes D.IVa was a German six-cylinder, water-cooled, inline engine developed in 1917 for use in aircraft and built by Daimler Motoren Gesellschaft (DMG).[1]

D.IVa
Mercedes D.IVa at the Deutsches Museum. The prominent black piping is the inlet manifold from the carburetor
Type Inline piston engine
Manufacturer Daimler Motoren Gesellschaft (DMG)
First run 1917
Not to be confused with the Maybach Mb.IVa.

Design and development

The D.IVa replaced the failed Mercedes D.IV inline eight-cylinder engine. The D.IVa was primarily used to power bombers and large reconnaissance aircraft. Unlike most German designs, the D.IVa was relatively advanced, including four valves per cylinder powered by a SOHC valvetrain, the same "single-camshaft" arrangement that had also been used on the earlier two-valve per cylinder D.I through D.IIIa powerplants.

Designed specifically to be installed in the fuselage, the engine featured a number of design elements intended to reduce its width. For instance, the carburetor was placed behind the engine, feeding fuel to the cylinders via a long tubular intake manifold. This had the disadvantage of poor fuel distribution. Two versions of the engine were produced in mirror copies, running in opposite directions.

Applications

Engines on display
  • A Mercedes D.IVa recently restored by the Museum's Friends ASSN. is on public display at the Museo Nacional de Aeronautica (MORON-Argentina).

Specifications (D.IVa)

Data from Jane's all the World's Aircraft 1918,[2] Jane's Fighting Aircraft of World War One[3][4]

General characteristics

  • Type: 6-cylinder, inline piston engine
  • Bore: 160 mm (6.30 in)
  • Stroke: 180 mm (7.09 in)
  • Displacement: 21.72 l (1,325 cu in)
  • Length: 1,168.4 mm (46 in) approx.
  • Height: 1,968.5 mm (77.5 in)
  • Dry weight: 498.50 kg (1,099 lb)

Components

  • Valvetrain: Shaft driven SOHC operating twin exhaust and inlet valves with a half compression setting for starting
  • Fuel system: Twin jet Mercedes carburettor with automatic mixture control
  • Fuel type: Gasoline
  • Oil system: Forced feed to bearings and camshaft
  • Cooling system: Water-cooled
  • Reduction gear: Direct drive, left-hand tractor

Performance

  • Power output: 187.92 kW (252 hp) at 1,400 rpm
  • Compression ratio: 4.94:1
  • Fuel consumption: 125 pints per hour
  • Specific fuel consumption: 0.0914 kg/kW/ks (0.541 lb/hp/h) / 0.128 l/kW/ks (0.605 imp pt/hp/h)
  • Oil consumption: 0.024 l/kW/h (0.032 imp pt/hp/h)
  • Power-to-weight ratio: 0.376 kW/kg (0.229 hp/lb)
  • Bmep: 741.19 kPa (107.5 psi)

See also

Related lists

References

Notes
  1. Gunston 1989, p.101.
  2. Grey, C.G., ed. (1968). Jane's all the World's Aircraft 1918 (facsimile ed.). New York Pages=46d-56d: Arno Press Inc.CS1 maint: location (link)
  3. Jane's 1993, p. 299
  4. Figures were derived from a British bench test of a captured engine.

Bibliography
  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
  • Jane's Fighting Aircraft of World War I. London. Studio Editions Ltd, 1993. ISBN 1-85170-347-0
This article is issued from Wikipedia. The text is licensed under Creative Commons - Attribution - Sharealike. Additional terms may apply for the media files.