The Market for Aviation Turboshaft Engines - Forecast International

Aviation Gas Turbine Forecast Page 3
Rolls-Royce Model 250/RR300 (Turboshaft)
Goodrich Engine Control Systems http://www.goodrich.com, Charter Oak Blvd, PO Box 330651, West Hartford, CT 06133
United States, Tel: + 1 (860) 236-0651, Fax: + 1 (860) 236-1062 (Main Fuel Pump
MFP-262-64)
Honeywell Aerospace http://www.honeywell.com/sites/aero/, 717 N Bendix Dr, South Bend, IN 46620 United
States, Tel: + 1 (574) 231-2000, Fax: + 1 (574) 231-3335 (Power Turbine Governor)
Howmet Castings, Corporate
Machining
http://www.alcoa.com, 145 Price Rd, Winsted Industrial Park, Winsted, CT 06098 United
States, Tel: + 1 (860) 379-3314, Fax: + 1 (860) 379-4239 (Integral Turbine Components)
Timken Super Precision (MPB) http://www.timken.com, 7 Optical Ave, PO Box 547, Keene, NH 03431-0547 United
States, Tel: + 1 (602) 352-0310, Fax: + 1 (602) 355-4554 (Main Shaft & Accessory Ball &
Roller Bearings)
Comprehensive information on Contractors can be found in Forecast International’s “International Contractors” series. For a detailed description,
go to www.forecastinternational.com (see Products & Samples/Governments & Industries) or call + 1 (203) 426-0800.
Contractors are invited to submit updated information to Editor, International Contractors, Forecast International, 22 Commerce Road, Newtown,
CT 06470, USA; rich.pettibone@forecast1.com
Design Features
Intake. Front annular steel intake with five struts.
Compressor. All models prior to the 250-C28 had one
centrifugal and six axial compressor stages. Beginning
with the 250-C28, a single titanium centrifugal
compressor was employed. The 250-C30 has an
improved centrifugal unit, allowing for a greater mass
flow and higher pressure ratio. The 250-C28 pressure
ratio is 8.4:1; 250-C30 is 8.5:1. Air mass flow is
4.5 lb/sec (2.04 kg/sec) and 5.6 lb/sec (2.54 kg/sec),
respectively.
Combustor. Single aft-mounted cannular combustor of
short length, with a single duplex fuel nozzle mounted
Technical Data
on the aft face. It is ignited by a capacitor discharge
with a low-tension exciter, utilizing a single plug. The
ignition units are produced by Unison Industries.
Series II engines have twin igniters.
Turbine. Both the gas generator and power turbines are
composed of two-stage units. The power turbine drives
the forward-mounted gearbox via the inner coaxial
shaft. The cooled first-stage turbine was introduced
with the 250-C28 and subsequent models, resulting in
higher turbine inlet temperatures. Nickel-base alloy
blades are employed.
Dimensions. The approximate dimensions and weights of the Model 250 turboshaft series are as follows:
Metric Units English Units
Series II
Length 1,035-1,037 mm 40.756-40.81 in
Width 477-527 mm 18.784-20.76 in
Height 574-589 mm 22.596-23.20 in
Weight, dry 71.6-73.5 kg 158-162 lb
Series IV
Length 1,097 mm 43.198 in
Width 559 mm 21.996 in
Height 632-660 mm 24.88-25.99 in
Weight, dry 111.1-114.7 kg 245-280 lb
Performance. According to data in U.S. FAA Type Certificate Data Sheet E4CE, Revision 39, June 11, 2001, and
Type Certificate Data Sheet E1GL, Revision 21, June 9, 2003, the Model 250 aviation turboshaft series of engines
have the following performance parameters (first figure is shp, second figure is kW):
30-Min.
Max. Cont. T-O 5-Min. 30-Min. OEI 2.5-Min. OEI Intermediate
at S/L at S/L at S/L at S/L at S/L
250-C28 478 (356) 500 (372) 500 (372) n/a n/a
250-C28B/C 500 (372) 500 (372) 500 (372) 550 (410) n/a
©2011 February 2011