Rolls-Royce AE 2100
| AE 2100 | |
|---|---|
| Type | Turboprop |
| National origin | United States |
| Manufacturer | Allison Engine Company Rolls-Royce plc |
| Major applications | C-130J Hercules C-27J Spartan ShinMaywa US-2 |
The Rolls-Royce AE 2100 is a turboprop developed by Allison Engine Company, now part of Rolls-Royce North America. A derivative of the Allison AE 1107C-Liberty (Rolls-Royce T406) turboshaft engine, it shares the same high-pressure core as the engine, as does the Rolls-Royce AE 3007. The engine is a two-shaft design and is the first to use dual FADECs (full authority digital engine control) to control both engine and propeller.
There are two versions of the engine. The civil AE2100A and the AE2100D3 military variant.
The engine uses new six-bladed Dowty propellers for use on the 50-seat Saab 2000 and the Lockheed C-130J Hercules military transport. Each engine develops 4,591 shaft horsepower, an increase of about 300 shp over the engines in the 'H' model C-130.[citation needed]
Applications
- AE2100A
- AE2100D3
Specifications (AE 2100)
General characteristics
- Type: Turboprop
- Length: 108 inches including gearbox
- Diameter: ~29 inches
- Dry weight: 1,610 to 1,925 lbs
Components
- Compressor: 14 stages axial
- Turbine: 2HP and 2PT
Performance
- Maximum power output: 4,150 plus shp (~3,100 kW)
- Power-to-weight ratio: 2.7 shp/lbs
See also
Related development
Related lists
References
- Leyes II, Richard A. (1999). The History of North American Small Gas Turbine Aircraft Engines. Washington, DC: Smithsonian Institution. ISBN 1-56347-332-1.
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External links
- AE 2100 product page at rolls-royce.com
- Rolls-Royce - http://www.rolls-royce.com/defence_aerospace/downloads/transport/ae2100.pdf
- Lockheed Martin C-130J specification booklet - http://www.c-130j.ca/document/Spec_Book.pdf
- Canadian C-130J site - http://www.c-130j.ca/index.php?page=capabilities&lang_id=1&page_id=33
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