Zoche aero-diesel
| Zoche ZO series | |
|---|---|
| Type | Radial aero engine |
| National origin | Germany |
| Manufacturer | Zoche |
The Zoche aero-diesels are a trio of radical German prototype diesel radial aero-engines intended for light aircraft.[1]
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-build 4-seat aircraft from Belgium was initially designed around the Zoche ZO1A motor; 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.
See also
Comparable engines
- Thielert Centurion
- Wilksch Airmotive — WAM 100 (100 hp), WAM 120 (120 hp) and WAM 160 (160 hp)
- Diesel Air — 100 hp (75 kW) twin-cylinder two-stroke opposed-piston engine
- Continental O-300
- Continental O-360
- ULPower UL260i
- MidWest AE series
Related lists
References
- ^ http://www.zoche.de
- ^ a b c d e http://www.zoche.de/zoche_brochure.pdf
- ^ "Horsepower of a Different Color". Archived from the original on January 8, 2007. Retrieved July 31, 2012.
{{cite web}}: Unknown parameter|deadurl=ignored (|url-status=suggested) (help) - ^ 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.
- ^ Wideo of wind tunnel test [1]
- ^ Gunston, Bill (2006). World encyclopedia of aero engines : from the pioneers to the present day (5th ed.). Stroud: Sutton. p. 254. ISBN 9780750944793.
- ^ a b http://www.lambert-aircraft.com/eng/indexEN.htm
External links
- www.zoche.de — Zoche site
Patents: