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The Allison Model 250, now known as the Rolls-Royce M250, (US military designations T63 and T703) is a highly successful turboshaft engine family, originally developed by the Allison Engine Company in the early 1960s. The Model 250 has been produced by Rolls-Royce since it acquired Allison in 1995.
Data from Rolls-Royce General characteristics Type: Twin-spool turboshaft/turboprop Length: 37.6 inches (96 cm) Diameter: 21.5 inches (55 cm) Dry weight: 201 pounds (91 kg) Components Compressor: Single-stage centrifugal Turbine: 2 stage GP, 2 stage PT Performance Maximum power output: 240–300 shaft horsepower (180–220 kW) Overall pressure ratio: 6.2 Power-to-weight ratio: 0.67 pounds per ...
Pages in category "Rolls-Royce aircraft gas turbine engines" The following 53 pages are in this category, out of 53 total. This list may not reflect recent changes .
Over the years a family of engines based on the T56 configuration was developed, culminating in the T406/Allison AE1107 turboshaft for the V-22 Osprey, the Allison AE2100 turboprop, used on newer models of the C-130 and the Allison/Rolls-Royce AE 3007 turbofan which propels many regional airline aircraft, such as the Embraer ERJ 135, ERJ 140 ...
Data from International Directory of Civil Aircraft and Technical specifications General characteristics Crew: 1–2 Capacity: 1–3 passengers Length: 31 ft 2 in (9.50 m) overall Height: 11 ft 0 in (3.35 m) Empty weight: 1,210 lb (549 kg) Gross weight: 2,460 lb (1,116 kg) Max takeoff weight: 2,550 lb (1,157 kg) Powerplant: 1 × Rolls-Royce M250-C20W turboshaft engine, 235 shp (175 kW) Main ...
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. This core is capable of powering turboprops of up to 10,000 shp (7,500 kW). [ 15 ]
It is produced by the LHTEC (Light Helicopter Turbine Engine Company), a joint venture between Rolls-Royce and Honeywell. The commercial and export version is the CTS800 . The engine was primarily developed for the United States Army 's cancelled RAH-66 Comanche armed reconnaissance helicopter, but has found use in other applications.
A T56 on a mobile test unit at MCAS Futenma, 1982 T56-A-1 (Series I) A 1,600 lb weight (730 kg) engine delivering 3,460 shp (2,580 kW) and 725 lbf (329 kgf; 3.22 kN) residual jet thrust, which is equal to 3,750 equivalent shp (2,800 kW); single-shaft 14-stage axial flow compressor, cannular combustion chamber with 6-cylindrical through-flow combustion liners, 4-stage axial flow turbine; 13,800 ...
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