The Info List - Shvetsov ASh-82

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The Shvetsov
ASh-82 (M-82) is a Soviet 14-cylinder, two-row, air-cooled radial aircraft engine developed from the Shvetsov
M-62. The M-62 was the result of development of the M-25, which was a licensed version of the Wright R-1820 Cyclone.


1 Design and development 2 Variants 3 Applications 4 Specifications (ASh-82)

4.1 General characteristics 4.2 Components 4.3 Performance

5 See also 6 References

6.1 Notes

7 External links

Design and development[edit] 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.[1] It entered production in 1940 and saw service in a number of Soviet aircraft. It powered the Tupolev Tu-2
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
Lavochkin La-5
fighter and its development, Lavochkin La-7, additionally the Lavochkin La-9
Lavochkin La-9
with its Lavochkin La-11
Lavochkin La-11
escort variant and Ilyushin Il-14
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[edit]

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.[2] 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 aircraft engine. The black metal plates mid-engine are baffles that re-direct airflow from the front of the engine (on the left in this image) over the heads of the cylinders.

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).[3] 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[4] 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.[5] 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.[citation needed] 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".[citation needed] Built by Dongan Engine Manufacturing Company (aka Harbin Engine Factory)


Family tree of Shvetsov

Amtorg KM-2 (Improved PBY Catalina, built under Consolidated license) Douglas TS-82 Gudkov Gu-82 (Prototype) Ilyushin Il-2
Ilyushin Il-2
(prototype) Ilyushin Il-12 Ilyushin Il-14 Kocherigin OPB-5 (prototype) Lisunov Li-2 Lavochkin La-5 Lavochkin La-7 Lavochkin La-9 Lavochkin La-11 MiG-5 MiG-9 I-210 (1941 Prototype) Mikoyan-Gurevich I-211
Mikoyan-Gurevich I-211
prototype Mil Mi-4 Petlyakov Pe-2 Petlyakov Pe-8 Polikarpov I-185
Polikarpov I-185
(Prototype) Sukhoi Su-2 Sukhoi Su-7 Sukhoi Su-12 Tupolev Tu-2 Yakovlev Yak-24

Specifications (ASh-82)[edit] Data from [3] [6] General characteristics

Type: 14-cylinder two-row radial engine Bore: 155.5 mm (6.122 in) Stroke: 155.0 mm (6.102 in) Displacement: 41.2107 L (2,515.3 cu in) Length: 2.01 m (6ft 7.1 in) Diameter: 1.26 m (49.6 in) Dry weight: M-82-112 model: 860 kg (1,894 Ib), M-82FN model: 890 kg (1,962 Ib), M-82FNV model: 900 kg (1,984 lb), M-82T model: 1,020 kg (2,246 lb)


Valvetrain: Pushrod, two valves per cylinder with sodium-cooled exhaust valve. Supercharger: Single-stage, One TK-2 two-speed centrifugal type supercharger on early production. Two TK-3 two-speed exhaust gas-driven forced-induction compressor on FN and FNV models. For the M-82T: Single-speed centrifugal supercharger with after-cooler. The gear ratio was 7.27:1. Critical altitude: 2,000 m (6,561 ft). Optionally, the M-82T had a two speed supercharger with after-cooler; the second speed gear ratio was 10,2:1. Critical altitude: 4,000 m (13,123 ft). Manifold pressure limit: 1.64 Atm (49.2") for takeoff and 1.34 Atm (40.15") 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, 95 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 gas: 3 kg/cm2 (42.7 PSI). Minimum oil pressure at cruise: 4.5 kg/cm2 (front pump), 5.5 kg/cm2 (rear pump) (64 PSI front and 78.2 PSI rear) 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-82-112 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 (46.3") 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 (38.6") 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 (46.3") 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 1.60 Atm (47.88") 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 (49.2") 1,630 hp (1,215 kW) at 2,400 RPM at 2,000 m (6,600 ft), boost rated at 1.34 Atm (40.1") 1,530 hp (1,082 kW) at 2,400 RPM at 4,000 m (13,000 ft), boost rated at 1.34 Atm (40.1") 721 hp (537 kW) at 2,400 RPM at 9,500 m (31,200 ft) Specific power: M-82F: 29.84 kW/L (0.655 hp/in³), M-82FNV: 33.48 kW/L (0.735 hp/in³) Compression ratio: 7.05:1 (6.90:1 for M-82T) Specific fuel consumption: M-82F: 355 g/hp•h (0.78 Ib/hp•hr) for take-off, 320 g/hp•hr (0.70 Ib/hp•hr) at nominal power M-82FNV: 360 g/hp•h (0.79 Ib/hp•hr) for take-off, 325 g/hp•hr (0.71 Ib/hp•hr) at nominal power M-82T: 350 to 325 g/hp•h (0.76 to 0.71 Ib/hp•hr) for take-off, 260 to 280 g/hp•hr (0.568 to 0.611 Ib/hp•hr) at cruise power Power-to-weight ratio: 1.46 kW/kg (0.89 hp/lb)

See also[edit]

Comparable engines

BMW 801 Bristol Hercules Fiat A.74 Gnome-Rhône 14N Mitsubishi Kinsei Nakajima Mamoru Nakajima Sakae Pratt & Whitney R-1830 Wright R-2600

Related lists

List of aircraft engines

References[edit] Notes[edit]

^ Witold Liss (1967). The Lavochkin La 5 & 7, number 149. Profile publications Ltd., P.O. Box, 1a North Street, Leatherhead, Surrey, UK. p. 3 ^ a b Gordon, Yefim; Khazanov, Dmitri (1998). Soviet Combat Aircraft of the Second World War Vol. 1. Midland Publishing limited. p. 44. ISBN 1857800834.  ^ a b ORDER. Chief of Civil Air Fleet. The Council of Ministers of the USSR. Number 508. August 5, 1963, Moscow. On enactment of the "Guide to Flight operation and piloting of the IL-14 with two engines AL-82T " ^ http://www.avid.ru/eng/pr/news/514/ ^ Yefim Gordon, Vladimir Rigmant (2002). Tupolev Tu-4, Soviet Superfortress (Red Star, Vol.7). Midland Publishing ISBN 1-85780-142-3. pp. 54–59.  ^ Liss, Witold (1967). The Lavochkin La 5 & 7, number 149. Profile publications Ltd., P.O. Box, 1a North Street, Leatherhead, Surrey, UK. pp. 3, 5–6, 8–9. 

External links[edit]

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