LOM M 332
The LOM M 332 is an air-cooled four-cylinder - four stroke - aircraft engine of the Czech manufacturer Avia . It is an in- line engine with suspended cylinders , the crankshaft is in the normal position above. The oil is supplied through a dry sump .
development
The M 332 engine was developed in 1958 by Walter von Bohumil Simunek based on the Walter Minor 4 III . In contrast to the initial type, an OHC valve drive was used and the engine was equipped with a switchable compressor and intake manifold injection . Compared to the original type, this required extensive changes to the cylinder head and the piston. The six-cylinder version was named Avia M 337 . Avia took over the production from Walter and so the engines were manufactured by Avia until 1989. Then LOM took over the manufacture and repair of the engines.
In 1992 production of the improved M 332A began. Compared to the original type, the crankshaft housing has been reinforced and the seal on the camshaft housing has been changed. This type M 332A was registered in November 1992. Another variant is the M 332AK with a modified oil supply, which is approved for unlimited inverted flight. It was approved in October 1994.
Starting in 1993, various improvements were made to improve performance. So there were changes to the crankshaft, the installation of a more powerful oil pump and the use of ultra-fine oil filters. This led to the variants 332B with increased speed and 332C with increased speed and increased compression.
In 2003, an improved engine control came into production, which allows the engine power to be regulated with just one lever, even with controllable pitch propellers.
variants
- A - Standard design for fixed or variable pitch propellers. Approval for simple aerobatics . Inverted flight is limited to 5 seconds.
- AK - Changed oil supply so that unlimited inverted flight is allowed.
- AR - Changed version for the drive of the pusher propeller.
- AK.1 - version with a three-phase alternator.
- B - Increased performance, permissible speed 3000 / min, 118 kW
- BK - like B, but modified oil supply so that unlimited inverted flight is permitted.
- C - Increased performance, permissible speed 3000 / min, higher compression 124 kW
Technical specifications
- Take-off power: 103 kW at 2700 rpm
- Continuous power: 88 kW at 2400 rpm
- Consumption at continuous output: 34.55 l / h
- Cylinder: 4 rows hanging
- Frontal area: 0.195 m²
- Bore: 104.9 mm
- Stroke: 115.06 mm
- Displacement: 3979 cm³
- Compression: 6.3: 1
- MTBO: 2000 h
- Dry weight: 124 kg
- Permissible acceleration: +6 g / −3.5 g
- Length: 1143 mm
- Width: 432 mm
- Height: 635 mm
literature
- Heinz A. F. Schmidt: Aircraft engines of socialist countries . In: Flieger-Jahrbuch 1971 . Transpress, Berlin 1970, p. 103 .