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Walter M601

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1960s Czech turboprop aircraft engine

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M601
Partially sectioned M601E
Type	Turboprop
National origin	Czech Republic
Manufacturer	Walter Aircraft Engines
First run	1967
Major applications	Let L-410 Turbolet PAC FU-24 Fletcher PZL-130 Orlik
Developed into	GE Aerospace Czech H80

An M601 mounted on an L-410 UVP in the Kbely museum, Prague

TheWalter M601 is aturboprop aircraft engine produced byWalter Aircraft Engines of theCzech Republic. The company's first turboprop, the M601 is used in business, agricultural and military training aircraft.^[1]

Development

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The turboprop was designed for use on theLet L-410 and the M601 first ran in 1967. It was not suitable for the prototype L-410 and the company developed an upgraded version, the M601A, with a slightly wider diameter.

Variants

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M601A: Initial production variant for early version of the Let L410.
M601B: Production variant for the Let L410UVP.
M601D: Developed for the Let L410UVP.
M601D-1: Agricultural variant for high-cycle operation, used on the PZL Kruk and Ayres Thrush.
M601D-2: Special variant for paradrop aircraft, used on the Do 28 and some Finist conversions.
M601D-11: Agricultural and paradrop variant with a higher Time Between Overhaul of up to 1800 hours.
M601D-11NZ: Downrated variant for use in the FU-24 Fletcher.
M601E: Developed for the Let L410UVP-E.
M601E-11: General use engine with sub-variants of differing TBO.
M601E-11A: Variant of the 11 for use at higher operating altitudes and modified with a low pressure bleed air system for pressurised aircraft.
M601E-21: Variant for the L410-UVP-E used for hot and high operations.
M601F: Variant intended for use on the L420.
M601FS
M601F-11
M601F-22
M601F-32
M601FS
M601T: Aerobatic variant for use on the PZL Orlik.
M601H-80: now theGE Aerospace Czech H80
M601Z: Agricultural variant for use on the Z-37T.

Applications

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Specification (M601D-1)

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Data fromWalter Engines^[2]

General characteristics

Type:Turboprop
Length: 1,675 mm
Diameter: 590 mm
Dry weight: 197 kg

Components

Compressor: 2-stageaxial compressor and 1-stagecentrifugal compressor
Combustors: annular
Turbine: 1-stage high-pressure and 1-stage free

Performance

Maximum power output: 544 kW, 490 kW continuous (740 hp, 657 hp continuous)
Turbine inlet temperature: 690°C
Specific fuel consumption: 377 g/kW·h (.62 lb/hp-h)
Power-to-weight ratio: 2.76:1 (kW:kg)

References

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^"M601 Turbo Prop Engine Description".www.walterengines.com. Archived fromthe original on 2007-02-19. Retrieved2025-09-13.
^"Specifications of various M601 models".www.walterengines.com. Archived fromthe original on 2007-04-30. Retrieved2025-09-13.

External links

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Wikimedia Commons has media related toWalter M601.

v t e Walter aircraft engines
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Opposed engines	Atom M202 M208
Inline engines	M 332 M 337 Junior Major 4 Major 6 Mikron Minor 4 Minor 6
V-12 engines	Sagitta Minor 12
Radial engines	NZ 40 NZ 60 NZ 85 NZ 90 NZ 95 NZ 120 Atlas Bora Castor Gemma Mars I Polaris Pollux Regulus Scolar Super Castor Vega Venus
Turbojets	M05 M06 M701
Turboprops	H80 M601 M602