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The Klimov M-103 is a V-12 liquid-cooled piston aircraft engine used by Soviet aircraft during World War II. It was a further development of the Klimov M-100 engine that was itself a licensed copy of the French Hispano-Suiza 12Ybrs. It differed from both engines in a number of aspects such as increased compression ratio, increased supercharger ratio, increased rpm's, strengthened cylinder blocks, a new crankshaft, and flat bottomed cylinders. Developed in 1936 it was ready for testing in October of 1936. The first two models failed testing due to cracked cylinder blocks and the engine was resubmitted for testing in 1937. After passing its trials it was cleared for production in 1938 and 11,681 were produced until 1942 at its factory in Rybinsk. The M-103 was followed by the M-105.
[edit] Models
- M-103A
- M-103P - 148mm rather than 150mm bore cylinders. A ShVAK cannon fitted to fire through the engine vee.
- M-103SP - A proposed version with two engines married to a common crankshaft.
- M-103G - With Glycol rather than water cooling.
- M-103A -TK - With an experimental Turbo-Supercharger
- M-103U - Improved service life variant.
- M-104 - Basically a M-103A with a two speed single stage supercharger for increased performance. 232 built.
[edit] Specifications (Klimov M-103A)
General characteristics
- Type: 12 cylinder liquid cooled in-line vee engine
- Bore: 150mm (5.91 in)
- Stroke: 170mm (6.69 in)
- Displacement: 36.03 Liters(2,198 cu in)
- Dry weight: 495kg (1,091 lb)
Components
- Supercharger: Single speed single stage geared centrifugal
- Fuel system: Carburetor
- Fuel type: 100 Octane
- Cooling system: Liquid
Performance
[edit] Applications
[edit] References
- Kotelnikov, Vladimir (2005). Russian Piston Aero Engines. Crowood Press Ltd., p.137-138.
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