Design and Development
Arkadiy Shvetsov re-engineered the Wright Cyclone design, through the OKB-19 design bureau he headed, for Russian aviation engine manufacturing practices and metric dimensions and fasteners, reducing the stroke, dimensions and weight. This allowed the engine to be used in light aircraft, where an American-design Twin Cyclone, of some 930 kg (2,045 lb) weight in "dry" condition could not be installed. It entered production in 1940 and saw service in a number of Soviet aircraft. It powered the Tupolev Tu-2 and Pe-8 bombers and the inline engine-powered LaGG-3 was adapted for the ASh-82 producing the famous Lavochkin La-5 fighter and its development, Lavochkin La-7, additionally the Lavochkin La-9 with its Lavochkin La-11 escort variant and Ilyushin Il-14 airliner were created around the engine. Over 70,000 ASh-82s were built. They were built in the 1950s to 1960s era under licence, both in Czechoslovakia (as the M-82) by the Walter (Motorlet) factory in Prague-Jinonice and in the German Democratic Republic by the VEB Industriewerke Karl-Marx-Stadt. Variants

• ASh-82-111 (M-82-111) - First mass-produced ASh-82, with carburettors and one two-speed supercharger. Engine had lubrication and carburettor problems in harsh winter conditions.
• ASh-82-112 (M-82-112) - Improved M-82-111 with longer Time between overhaul (TBO) and better reliability. Redesigned carburettors, oil pumps, gear, turbocharger and reinforced pushrods.
• ASh-82F (M-82F) - Identical to ASh-82 except for longer Time between overhaul and improved cooling and lubrication system.
• ASh-82FNV (M-82FNV) - Improved M-82F with direct fuel injection, power output increased to 1,380 kW (1,850 hp) compared to the 1,268 kW (1,700 hp) of the M-82 and M-82F.
• ASh-82FN (M-82FN) - Series production M-82FNV,[2] used by Pe-8 long-range bombers and Lavochkin La-5FN and La-7 fighters.
• ASh-21 (M-21) - Single-row 7-cylinder version of ASh-82 for Yakovlev Yak-11 trainer, entered production in 1946, used also to power e.g. the Mil Mi-1 helicopter.
• ASh-82T (M-82T) - New version of the ASh-82FNV developed in the early fifties for civilian aircraft. Previous version twin superchargers were replaced with a large single-speed compressor attached to an after-cooler (the critical altitude was 2,000 m, 6,561 ft). New alloys were used and some components were upgraded, thus reducing maintenance operations. Special care was put into reducing the engine noise level and an optional exhaust double silencer was available. The engine had a new fuel injection system and improved specific fuel consumption. A four-blade high efficiency propeller, the Typ AV-50m, was developed for the 82T version. Take-off power was 1,900 hp (1,417 kW) at 2,600 RPM, with 95 octane Avgas. Maximum continuous power was 1,630 hp (1,215 kW). At 85 octane Avgas and minor modifications, power output was rated at 1,700 hp (1,268 kW).
• ASh-82V (M-82V) - Helicopter version of the ASh-82T developed in 1952, with axial-flow fan mounted in the fuselage's front. The engine was connected to a R-5 two-stage planetary primary gearbox with the help of a shaft (which was between the pilots seats). This engine was used in the Mi-4 and Yak-24 helicopters.
• ASh-2TK and ASh-2K (ASh-4K) – Four-row versions of the ASh-82, developed in the late '40s. The ASh-2TK had a two-stage two-speed supercharging system with intercooler (similar to the ASh-73) that compromised the engine's long TBO. Finally the ASh-2TK was discarded and a new version was developed, the ASh-4K, with an experimental variable-speed turbocharger and after-cooler, which allowed a cruising altitude of 11,000 m (36,089 ft). The engine had 82.4 litres (5,030 cu in) and 4,000 HP (2,985 kW) at 2,600 RPM (dry). The Ash-2K (ASh-4K) version had 4,700 HP (3,507 kW) wet, with a water-methanol system. For political reasons, these engines were prematurely installed in Tupolev Tu-4LL testbeds at the end of 1950, when the prototypes' initial tests had barely begun. The engines had various teething and overheating problems, and required a long testing period. Most of the flaws were fixed in the mid-fifties, but the production was cancelled: in those days, the priority for the Soviet Air Force were the turboprop and jet engines.
• Dongan HS-7 A Chinese license built copy of the ASh-82V, and the chosen engine for powering modern 21st century reproductions of the Focke-Wulf Fw 190A built in Germany.
• Dongan HS-8 A modified version of the Dongan HS-7 which "combined the main body and supercharger of the HS-7 with the reduction gear and propeller drive of the Shvetsov ASh-82T". Built by Dongan Engine Manufacturing Company (aka Harbin Engine Factory).

• Type: 14-cylinder two-row radial engine
• Bore: 155.5 mm (6.122 in)
• Stroke: 155 mm (6.102 in)
• Displacement: 41.2107 L (2,514.83 cu in)
• Length: 2,100 mm (82.677 in)
• Diameter: 1,260 mm (49.606 in)
• Dry weight:
• M-82-112: 860 kg (1,900 lb)
• M-82FN: 890 kg (1,960 lb)
• M-82FNV: 900 kg (2,000 lb)
• M-82T: 1,020 kg (2,250 lb)

• Valvetrain: Pushrod, two valves per cylinder with sodium-cooled exhaust valve.
• Supercharger:
• M-82FN andM-82FN: Single-stage, One TK-2 two-speed centrifugal type supercharger on early production. Two TK-3 two-speed exhaust gas-driven forced-induction compressor.
• M-82T: Single-speed centrifugal supercharger with after-cooler. The gear ratio was 7.27:1 and 10.2:1. Critical altitude: 2,000 m (6,600 ft). Optionally, the M-82T had a two speed supercharger with after-cooler; Critical altitude: 4,000 m (13,000 ft). Manifold pressure limit:1.64 atm (49 inHg) for takeoff and 1.34 atm (40 inHg) at second speed.
• Fuel system: Carburettors (early production), direct fuel injection with automatic mixture control. Petrol pump: BNK-10KT.
• Fuel type: 90 octane (minimum grade allowed), 92 octane, 95 octane or 100 octane
• Oil system: Two pumps: geared rotation pump MSH-6SV (rear) and swarm pump PMN-T (front). Normal oil temp: 40 to 90°C. Limit temp: 115°C. Minimum oil pressure at low power: 2.94 bar (42.7 psi). Minimum oil pressure at cruise: 4.5 kg/cm2 (64 psi) (front pump), 5.5 kg/cm2 (78 psi) (rear pump)
• Cooling system: Air-cooled. Minimum permissible cylinders temp for operation: 120°C. Maximum permissible cylinders temp: 250°C. Maximum permissible at cruise: 225°C. Normal cylinders temp at cruise: 160 to 180°C
• Reduction gear: 11:16 (prototypes & M-82-111), 9:16 (M-82-211 and later models)

• Power output:
• M-82-111 with carburettors:
• 1,570 hp (1,170 kW) at 2,400 RPM for take-off (Dry), boost rated at 1.55 atm (46 inHg)
• 1,540 hp (1,148 kW) at 2,400 RPM at 2,000 m (6,600 ft)
• 1,330 hp (992 kW) at 2,400 RPM at 5,500 m (18,000 ft)), boost rated at 1.29 atm (39 inHg)
• 820 hp (612 kW) at 2,400 RPM at 8,500 m (27,900 ft)
• M-82F with carburettors:
• 1,650 hp (1,230 kW) at 2,400 RPM for take-off (Dry), boost rated at 1.55 atm (46 inHg)
• 1,430 hp (1,067 kW) at 2,400 RPM at 5,000 m (16,000 ft)
• 800 hp (597 kW) at 2,400 RPM at 10,000 m (33,000 ft)
• M-82FNV and M-82FN with direct fuel injection:
• 1,850 hp (1,380 kW) at 2,500 RPM for take-off (Dry), boost rated at 1.6 atm (48 inHg)
• 1,650 hp (1,230 kW) at 2,400 RPM at 1,650 m (5,410 ft), boost rated at 1.36 Atm (40.7")
• 1,450 hp (1,082 kW) at 2,400 RPM at 4,650 m (15,260 ft), boost rated at 1.36 Atm (40.7")
• 810 hp (604 kW) at 2,400 RPM at 10,500 m (34,400 ft)
• M-82T with two speed supercharger:
• 1,900 hp (1,416 kW) at 2,600 RPM for take-off, boost rated at 1.64 atm (49 inHg)
• 1,630 hp (1,215 kW) at 2,400 RPM at 2,000 m (6,600 ft), boost rated at 1.34 atm (40 inHg)
• 1,530 hp (1,082 kW) at 2,400 RPM at 4,000 m (13,000 ft), boost rated at 1.34 atm (40 inHg)
721 hp (537 kW) at 2,400 RPM at 9,500 m (31,200 ft)
• Specific power:
• M-82F: 29.84 kW/L (0.656 hp/cu in)
• M-82FNV: 33.48 kW/L (0.736 hp/cu in)
• Compression ratio: 7.05:1 (M-82T: 6.90:1)
• Specific fuel consumption:
• M-82F:
• Take-off:0.47 kg/kW/h (0.78 lb/hp/h)
Nominal:0.43 kg/kW/h (0.7 lb/hp/h)
• M-82FNV:
• Take-off:0.48 kg/kW/h (0.79 lb/hp/h)
• Nominal:0.43 kg/kW/h (0.71 lb/hp/h)
• M-82T:
• Take-off:0.46–0.43 kg/kW/h (0.76–0.71 lb/hp/h)
• Cruise:0.346–0.372 kg/kW/h (0.568–0.611 lb/hp/h)
• Power-to-weight ratio: 1.46 kW/kg (0.89 hp/lb)