Zoche aero-diesel

The Zoche aero-diesels are a trio of radical German prototype diesel radial aero-engines intended for light aircraft.[1]

Zoche ZO series
Type Radial aero engine
National origin Germany
Manufacturer Zoche

Zoche engines are modular and are all direct-drive, air-cooled, radial two-stroke diesels with up to four cylinders per row. They all feature direct fuel-injection, two-stage charging (turbocharger and supercharger), and intercooling.

The testing and gestation period of the Zoche engines has already lasted over 20 years; and whether or when production may eventually start is unknown.

Design and development

The range comprises three radial engines, namely: a "cross-4"; a twin-row "cross-8"; and a V-twin.[2]

The AOPA website explains the "cross-4" ZO 01A as follows: "The radial design was chosen for its ability to be effectively air-cooled and 100% balanced at all rpm with a simple counterweight system. All four connecting rods are attached to a single crankshaft throw. This prevents any crankshaft twisting, which is hard to balance out in opposed-configuration engines. Zoche engines use a pneumatic starting system that does away with the need for a heavy-duty starter and battery system".[3] Propeller rotation is clockwise (viewed from the cockpit). Engine mountings are attached to the cylinder heads. Engines are to be certified to JAR-E and FAR 33, and a TBO of 2,000 hours is anticipated.

The founder of the project is Michael Zoche, who claims that the ZO engines will have the following advantages:

  • they will be lightweight, compact (with low frontal area) and very smooth;
  • low fuel consumption; high power-to-weight ratio;
  • the lubrication system will allow aerobatics;
  • diesel fuel injection, so no carburetor icing;
  • direct-driven generator, so no drive belts;
  • good reliability through a low part count and absence of poppet valves;
  • pneumatic starting obviates both electric starter motor and heavy starter battery;
  • complete absence of rubber hoses; cheaper parts through modularity;
  • reduced fire risk compared to avgas;[4]
  • good power output, even at altitudes up to 9,000 feet (3,000 m).[2]
  • the engines will also have a "classic radial" appearance that is appropriate for some aircraft types.

A Zoche engine has run effectively in wind tunnel tests,[5] but Zoche seem barely any closer to production than they were a decade ago. Experimental engine manufacturers seem to experience difficulties in proceeding beyond the prototype stage. The cited engine weights include: starter-generator, hydraulic propeller-governor, turbocharger and supercharger, and oil- and fuel-filters.

Zoche engine variants
ZO 01A
Single-row cross-4, 2,660 cc (162 cu in), (max) 150 hp (112 kW) @ 2500 rpm, 84 kg (185 lb)), fuel consumption 21 litres/h @ 75% power.[2]
ZO 02A
Double-row cross-8, 5,330 cc (325 cu in), (max) 300 hp (224 kW) @ 2500 rpm, 123 kg (271 lb)), fuel consumption 42 litres/h @ 75% power.[2]
ZO 03A
V-twin, 1,330 cc (81 cu in), (max) 70 hp (52 kW) @ 2500 rpm, 55 kg (121 lb)), fuel consumption 10 litres/h @ 75% power.[2]
ZO 04A
A 2,000 hp (1,500 kW) compound diesel engine for use in the Sentinel 5000 airship on vectoring mounts.[6]

Lambert Mission

The Lambert Mission 212,[7] a kit-built 4-seat aircraft from Belgium, was initially designed around the Zoche ZO1A engine; but, with the non-appearance of the Zoche, Lambert were obliged to select other engines, the DeltaHawk® DH200A4 (or DH180A4), or the XP-360 engine.[7] In May 2010 the second M212 Mission (and first kit-built example) was successfully flown.

gollark: I just bought 100 generic cheao pens off Amazon some years back.
gollark: I should really learn more TeX, on that note.
gollark: Typing is far superior.
gollark: I try to avoid writing things by hand.
gollark: Meh.

See also

Comparable engines

Related lists

References
  1. http://www.zoche.de
  2. http://www.zoche.de/zoche_brochure.pdf
  3. "Horsepower of a Different Color". Archived from the original on January 8, 2007. Retrieved July 31, 2012.
  4. Brochure claim: "High inflight reliability – no carburetor-icing, no magneto or spark- plug problems, no vapor lock. Turbine inlet temperature is so low that it needs no monitoring. Even cylinder head temperatures are not critical.
  5. Wideo of wind tunnel test
  6. Gunston, Bill (2006). World encyclopedia of aero engines : from the pioneers to the present day (5th ed.). Stroud: Sutton. p. 254. ISBN 9780750944793.
  7. http://www.lambert-aircraft.com/eng/indexEN.htm

Patents:

  • DE 4020826
  • EP 0231223
  • US 4781028
  • US 5197416
  • Japan 63-500818
This article is issued from Wikipedia. The text is licensed under Creative Commons - Attribution - Sharealike. Additional terms may apply for the media files.