Rolls-Royce RB.183 Tay
|A Tay 650-15 installed on an Air Bagan Fokker 100|
|Major applications||Fokker 70
The Rolls-Royce RB.183 Tay is a turbofan engine, developed from the RB.163 Spey, using scaled down low-pressure components from the RB.211 to produce versions with a bypass ratio of 3.1:1 or greater. The engine was first run in August 1984. The Tay family is used on a number of airliners and larger business jets, including the Gulfstream IV family, Fokker 70 and Fokker 100, with a later version being used to re-engine Boeing 727-100s.
|This section does not cite any references or sources. (January 2011)|
Originally designated 610-8, all but one training engine have now been converted to 611-8 standard. The newest variant is the 611-8C which has a modified high pressure nozzle box, cast HP1 turbine blades, larger fan from the 650-15, structural by-pass duct and FADEC.
All Tays consists of a twenty-two blade titanium fan, 3 stage Intermediate pressure compressor (Same spool as the fan.), 12 stage High pressure compressor, 2 stage high pressure turbine, 3 stage low pressure turbine.
The 620-15 is internally identical to the 611-8 and externally similar to the 650-15.
Thrust: 15,100 lbf (67 kN) Aircraft: Originally designed to re-engine the BAC One-Eleven (650-14, only two made, both have since been converted to 650-15 standard.), the 650-15 entered service on the Fokker 100 in 1989.
The 651-54 is internally identical to the 650-15. The thrust increase comes solely from an adjustment to the Fuel Flow Meter.
Thrust: 15,400 lbf (69 kN) Aircraft: Boeing 727-100 from 1992. Conversion from three JT8D-7 to three Tay 651-54 was done by the now defunct Dee Howard Aircraft Maintenance Company in San Antonio Texas for the United Parcel Service but all aircraft are currently grounded. Only one private 727 was converted.
Specifications (Tay 620-15)
- Type: Twin-spool high bypass turbofan
- Length: 94.7 in (2,405.4 mm)
- Diameter: 44 in (1,117.6 mm) (fan diameter)
- Dry weight: 3,310 lb (1,501.4 kg)
- Compressor: Single-stage fan plus 3-stage LP compressor and 12-stage HP compressor
- Combustors: 10 cannular combustion chambers
- Turbine: 2 stage HP turbine, 3 stage LP turbine
- Maximum thrust: 13,850 lbf (62.82 kN)
- Bypass ratio: 3.04:1
- Turbine inlet temperature: 735 degrees C (maximum continuous)
- Thrust-to-weight ratio: 4.2:1
- Comparable engines
- Related lists
- Gunston 1989, p.153.
- Rolls-Royce data sheet
- FAA Type Certificate Data Sheet
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