| A-1020 / T-1020 | |
|---|---|
| |
| A T-1020 variant on display | |
| Type | Diesel radial engine |
| National origin | United States |
| Manufacturer | Guiberson Diesel Engine Company |
| Designer | Fred A. Thaheld[1] |
| First run | January 1940[2] |
| Major applications | Stinson Reliant |
The Guiberson A-1020 is a four-stroke diesel radial engine developed for use in aircraft and tanks.
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Design and development
Development of the Guiberson diesel engine started in the 1930s with the A-918 and A-980 which was first flown in 1931. It is a single-row direct drive nine-cylinder four-cycle engine.[2]
Operational history
Production A-1020s and T-1020s were designed and sold by Guiberson and produced by Buda Engine Co.[2][3]
Variants
- Guiberson A-918
- Rated at 185 hp (138 kW) - one of the initial development models for use on aircraft.[4][5]
- Guiberson A-980
- Rated at 210 hp (160 kW) - one of the initial development models for use on aircraft.[2][4]
- Guiberson A-1020
- Rated at 310 hp (230 kW) - production engines for aircraft use.[2][5]
- Guiberson T-1020
- Rated at 250 hp (190 kW) - for use in light tanks such as the M-3 Stuart[2][6][5]
Applications
Surviving engines
- There is a T-1020 on display at the New England Air Museum, Bradley International Airport, Windsor Locks, CT.[7]
Specifications (A-1020)
Data from Aircraft Diesels: Chapter 3 - The Guiberson Diesel[2][5]
General characteristics
- Type: 9-cylinder air-cooled radial diesel piston engine
- Bore: 5.125 in (130.18 mm)
- Stroke: 5.5 in (139.70 mm)
- Displacement: 1,021 cu in (16.73 L)
- Length: 38.6 in (980 mm) including starter
- Diameter: 47.125 in (1,197.0 mm)
- Dry weight: 653 lb (296 kg)
- Designer: F. A. Thaheld
Components
- Valvetrain: two pushrod operated valves per cylinder, with de-compression device for hand-turning or free-wheeling.
- Fuel system: Guiberson system fuel injection
- Fuel type: Diesel Index No.50
- Cooling system: Air-cooled
- Reduction gear: Direct-drive
- Eclipse inertia starter or Coffman cartridge starter
Performance
- Power output: 310 hp (230 kW), continuous at 2,150 rpm at sea level
- Compression ratio: 15:1
- Specific fuel consumption: 0.42 lb/(hp⋅h) (0.26 kg/kWh) at 2,150 rpm; 0.382 lb/(hp⋅h) (0.232 kg/kWh) at cruising speed
- Oil consumption: 0.02 lb/(hp⋅h) (0.012 kg/kWh) at 2,150 rpm
- Power-to-weight ratio: 0.475 hp/lb (0.781 kW/kg)
- BMEP 113 psi (780 kPa) at rated output
See also
References
Wikimedia Commons has media related to Guiberson A-1020.
- ^ "Lightplane Diesel". Flying. July 1946.
- ^ a b c d e f g h i j Wilkinson, Paul H. "Aircraft Diesels: Chapter 3 - The Guiberson Diesel" (PDF). Aircraft Engine Historical Society. Retrieved 14 March 2018.
- ^ The Aeroplane, Volume 59.
- ^ a b Grey, C.G.; Bridgman, Leonard, eds. (1938). Jane's all the World's Aircraft 1938. London: Sampson Low, Marston & company, ltd. p. 86d.
- ^ a b c d Bridgman, Leonard, ed. (1947). Jane's all the World's Aircraft 1947. London: Sampson Low, Marston & Co. p. 67d.
- ^ Arthur William Judge. Aircraft engines, Volume 2.[page needed]
- ^ Guiberson T-1020 Diesel Engine, New England Air Museum
Further reading
- "The Guiberson Aero Diesel", Flight, p. 9, 2 January 1941
- TM9-1727 T-1020 Ordinance Maintenance Manual
This page was last edited on 2 March 2023, at 16:15