Rolls-Royce AE 2100
| AE 2100 | |
|---|---|
| |
| The Rolls-Royce AE 2100 D2A of a C-27J | |
| Type | Turboprop |
| National origin | United States |
| Manufacturer | Allison Engine Company Rolls-Royce plc |
| Major applications | Lockheed Martin C-130J Hercules Alenia 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, the AE 2100 shares the same high-pressure core as that engine, as does the Rolls-Royce AE 3007 turbofan. The engine is a two-shaft design, and was 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 Martin C-130J Super Hercules military transport. Each engine develops 4,591 shaft horsepower.
Applications
- AE2100A
- Saab 2000
- Indonesian Aerospace N-250 - Prototype only
- AE2100D2A
- AE2100J
- AE2100D3
Specifications (AE 2100D2)
Data from Rolls-Royce product data sheet.[2]
General characteristics
- Type: Turboprop
- Length: 118 in (3.0 m)
- Diameter: 28.7 in (0.73 m)
- Dry weight: 1,727 lb (783 kg)
Components
- Compressor: 14-stage axial
- Turbine: 2-stage HP, 2-stage PT
Performance
- Maximum power output: 4,637 shp (3,458 kW)
- Overall pressure ratio: 16.6:1
- Power-to-weight ratio: 2.7 shp/lb (4.53 kW/kg)
See also
Related development
Related lists
References
- ^ AE 2100 Description
- ^ Rolls-Royce AE 2100 turboprop Retrieved: 14 January 2013
- Leyes II, Richard A.; William A. Fleming (1999). The History of North American Small Gas Turbine Aircraft Engines. Washington, DC: Smithsonian Institution. ISBN 1-56347-332-1.
External links
