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Wright R-1820 Cyclone / Cyclone 9
Curtiss-Wright R-1820 Cyclone
Hispano-Suiza 9V
Shvetsov M-25


Wright-R1820
Curtiss-Wright R-1820 Cyclone

 

In 1932, the R-1750 was developed to a capacity of 1823 cu in. This was the F model Cyclone, designated R-1820 Cyclone 9. This engine introduced a forged aluminium crankcase and was developed through the 1930s to reach 890 hp. It used a General Electric supercharger, and Wright concluded that this feature limited the potential power output of the engine. For the next development, the G-Series of 1937, Wright developed its own single-speed supercharger. The G-series was developed to deliver 1200 hp at 2500 rpm and made up the bulk of R-1820 Cyclone production during World War 2. It was installed in the Boeing B-17 Flying Fortress. The final phase of development of the single row radial design was the H-Series at 1350 hp.

The engine remained in production well into the 1950s.

The R-1820 was built under license by Lycoming, Pratt & Whitney Canada, and also, during World War II, by the Studebaker Corporation. The Soviet Union had purchased a license for the design, and the Shvetsov OKB was formed to produce the engine as the M-25. In Spain the R-1820 was license-built as the Hispano-Suiza 9V or Hispano-Wright 9V.

 

The Shvetsov M-25 was a licensed production variant of the Wright R-1820-F3. The first M-25s were produced from kits imported from the United States; the main difference between the later M-25 and the R-1820-F3 was the use of metric components. 13,888 M-25s were produced in the USSR at factories in Perm and Kazan. There were a number of sub-variants which differed from the original M-25 in that they had reduction gears, rather than direct drive. Performance was similar to the equivalent Wright engines. The M-25 was later developed into the ASh-62.

 

Shn-M25
Shvetsov M-25

 

The R-1820 was at the heart of many famous aircraft including the early Douglas airliners (prototype DC-1, the DC-2, earliest civilian versions of the DC-3, and the limited-production DC-5), B-17 Flying Fortress, and SBD Dauntless bombers, the early versions of the Polikarpov I-16 fighter (as M-25), and the Piasecki H-21 helicopter.

 

TC9J2, a Turbocompounded R-1820 Offered in the Early 1950s.

 

The R-1820 also found limited use in armored vehicles in two forms. The G-200 was a nine-cylinder gas-burning radial that developed 900 hp (670 kW) @ 2,300 rpm and powered the M6 Heavy Tank. The Wright RD-1820 was converted to a diesel by Caterpillar Inc. as the D-200 and produced 450 hp (340 kW) @ 2,000 rpm in the M4A6 Sherman.

 

Variants:
Unit numbers ending in/with W indicate engines fitted with water-methanol emergency power boost system.

R-1820-04
700 hp (522 kW)

R-1820-1
575 hp (429 kW)

R-1820-4
770 hp (574 kW)

R-1820-19
675 hp (503 kW)

R-1820-22
950 hp (708 kW)

R-1820-25
675 hp (503 kW), 750 hp (559 kW), 775 hp (578 kW)

R-1820-32
1,000 hp (750 kW)

XR-1820-32
800 hp (596 kW)

R-1820-33
775 hp (578 kW)

R-1820-34
940 hp (701 kW), 950 hp (708 kW)

R-1820-34A
1,200 hp (895 kW)

R-1820-40
1,100 hp (820 kW), 1,200 hp (895 kW)

R-1820-41
850 hp (634 kW)

R-1820-45
800 hp (596 kW), 930 hp (694 kW)

R-1820-50
850 hp (634 kW)

R-1820-52
1,000 hp (750 kW)

R-1820-53
930 hp (694 kW), 1,000 hp (750 kW)

R-1820-56
1,200 hp (895 kW), 1,350 hp (1,007 kW)

R-1820-57
1,060 hp (790 kW)

R-1820-60
1,200 hp (895 kW)

R-1820-62
1,350 hp (1,007 kW)

R-1820-66
1,200 hp (895 kW), 1,350 hp (1,007 kW)

R-1820-72W
1,350 hp (1,007 kW), 1,425 hp (1,063 kW)

R-1820-74W
1,500 hp (1,118 kW)

R-1820-76A, B, C, D
1,425 hp (1,063 kW)

R-1820-78
700 hp (522 kW)

R-1820-80
700 hp (522 kW), 1,535 hp (1,145 kW)

R-1820-82WA
1,525 hp (1,137 kW)

R-1820-86
1,425 hp (1,063 kW)

R-1820-97
1,200 hp (895 kW), Fitted with turbosupercharger

R-1820-103
1,425 hp (1,063 kW)

SGR-1820-F3
710 hp (529 kW), 720 hp (537 kW)

SGR-1820-F2
720 hp (537 kW)

R-1820-F53
770 hp (574 kW)

R-1820-F56
790 hp (589 kW)

GR-1820-G2
1,000 hp (750 kW)

R-1820-G3
840 hp (626 kW)

R-1820-G5
950 hp (708 kW)

R-1820-G101
1,100 hp (820 kW)

R-1820-G102
775 hp (578 kW)

GR-1820-G102A
1,100 hp (820 kW)

R-1820-G102A
1,100 hp (820 kW)

R-1820-G102A
1,100 hp (820 kW)

R-1820-G202A
1,200 hp (895 kW)

R-1820-G103
1,000 hp (750 kW)

R-1820-G105
1,000 hp (750 kW)

R-1820-G205A
1,200 hp (895 kW)

Hispano-Suiza 9V
Licence built R-1820

Hispano-Suiza 9Vbr
Hispano-Suiza 9Vbs
Hispano-Suiza 9Vd

Shvetsov M-25

 

Applications
Boeing B-17 Flying Fortress
Boeing 307
Brewster F2A
Curtiss AT-32-A Condor
Curtiss SBC-4 Helldiver
Curtiss P-36 Mohawk
Curtiss SC Seahawk
Curtiss-Wright CW-21
Douglas A-33
Douglas B-18
Douglas DC-2
Douglas DC-3 (DST, G-102 and G-202)
Douglas Super DC-3, R4D-8 / C-117
Douglas DC-5
Douglas SBD Dauntless
FMA AeMB.2 Bombi
General Motors FM-2 Wildcat
Grumman TF-1 / C-1 Trader
Grumman FF-1
Grumman F3F
Grumman HU-16 Albatross
Grumman J2F Duck
Grumman S-2 Tracker
Lockheed 14
Lockheed Lodestar
Lockheed Hudson
Martin B-10
North American NA-44
North American O-47
North American P-64
North American T-28B/C/D Trojan
Northrop YC-125 Raider
Piasecki H-21
Polikarpov I-16
Ryan FR Fireball
Sikorsky S-58/HUS/HSS/H-34

Vehicles:
M4A6 tank
M6 heavy tank

 

Shvetsov M-25 Applications:
Neman R-10
Polikarpov I-14
Polikarpov I-15bis
Polikarpov I-153
Polikarpov I-16

 

Specifications:

GR-1820-G2
Type: Nine-cylinder single-row supercharged air-cooled radial engine
Bore: 6 1⁄8 in (155.6 mm)
Stroke: 6 7⁄8 in (174.6 mm)
Displacement: 1,823 in³ (29.88 L)
Length: 47.76 in (1,213 mm)
Diameter: 54.25 in (1,378 mm)
Dry weight: 1,184 lb (537 kg)
Valvetrain: Two overhead valves per cylinder with sodium-filled exhaust valve
Supercharger: Single-speed General Electric centrifugal type supercharger, blower ratio 7.134:1
Fuel system: Stromberg PD12K10 downdraft carburetor with automatic mixture control
Fuel type: 87 octane rating gasoline
Oil system: Dry sump with one pressure and one scavenging pump
Cooling system: Air-cooled
Power output: 1,000 hp (746 kW) at 2,200 rpm for takeoff
Specific power: 0.46 hp/in³ (20.88 kW/L)
Compression ratio: 6.45:1
Specific fuel consumption: 0.6 lb/(hp•h) (362 g/(kW•h))
Oil consumption: 0.35-0.39 oz/(hp•h) (13-15 g/(kW•h))
Power-to-weight ratio: 0.84 hp/lb (1.39 kW/kg)

 

Shvetsov M-25
Type: 9-cylinder, air-cooled, radial engine
Bore: 6.125 in (155.6 mm)
Stroke: 6.875 in (174 mm)
Displacement: 1,823.1 in³ (29.876 L)
Dry weight: 499kg (999lb)
Supercharger: Single speed, single stage, geared centrifugal supercharger
Fuel system: 1 K-25 (Solex) Carburetor
Power output: 700-800hp depending on model
Compression ratio: 6.4:1

 

 

 

 

 


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