Pratt & Whitney Canada PW300

Maximum Takeoff Thrust

23.24 kN

Bypass Ratio

4.5

Diameter

970.3 mm

Length

2062 mm

Dry Weight

450 kg

Thrust To Weight

5.26

Specific Fuel Consumption

11.528 g/(kN·s)

Architecture

Fan	Fan Stages —	Fan Blades —	Fan Technology —	Fan Pressure Ratio —
Gearbox	Geared Fan No	Gear —	Reduction Ratio —
LP compressor	Low-Pressure Compressor Stages —	Low-Pressure Compressor Technology —	BP Compressor Pressure Ratio —
IP compressor	Intermediary-Pressure Compressor Stages —	Intermediary-Pressure Compressor Technology —	IP Compressor Pressure Ratio —
HP compressor	High-Pressure Compressor Stages —	High-Pressure Compressor Technology —	HP Compressor Pressure Ratio —
Combustor	Combustion Chamber Annular
HP turbine	High Pressure Compressor Stages —	High-Pressure Turbine Technology —
IP turbine	Intermediary-Pressure Turbine Stages —	Intermediary-Pressure Turbine Technology —
LP turbine	Low-Pressure Turbine Stages —	Low-Pressure Turbine Technology —
Whole engine	Streams 2	Bypass Ratio 4.5	Overall Pressure Ratio —	Afterburner No

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Name	Aircraft Engine	Number of Engines	Length (m)	Flat Wing Span (m)	Max Seating
Cessna Citation Sovereign	Pratt & Whitney Canada PW300	2	19.35	22.04	12
Gulfstream G200	Pratt & Whitney Canada PW300	2	18.97	17.7
Hawker 4000	Pratt & Whitney Canada PW300	2	21.08	18.82	8

Name	Aircraft Engine Manufacturer	Maximum Takeoff Thrust (kN)	Bypass Ratio
Rolls-Royce RB401	Rolls-Royce	24.7	4.2	Compare
General Electric J97	General Electric Company	23.4		Compare
Rolls-Royce RB.162	Rolls-Royce	23		Compare
CFE CFE738	General Electric Company	26.3	5.3	Compare
Garrett ATF3	Garrett	24.2	2.8	Compare
Klimov VK-1	Klimov	26.5		Compare

All data (18 fields)

Name: Pratt & Whitney Canada PW300
Aircraft Engine Manufacturer: Pratt & Whitney Canada
Aircraft Engine Type: Turbofan
Dry Weight (kg): 450
Diameter (mm): 970.3
Length (mm): 2062
Wikipedia Article (URL): en.wikipedia.org/wiki/Pratt_%26_Whitney_Canada_PW300
Fuel: Aviation Kerosene such as JET A, JET A-1, JP-4, JP-5 or CPW-204
Geared Fan: No
Combustion Chamber: Annular
Afterburner: No
Streams: 2
Bypass Ratio: 4.5
Maximum Takeoff Thrust (kN): 23.24
Thrust To Weight: 5.26
Specific Fuel Consumption (g/(kN·s)): 11.528
Compressor Description: 1-stage fan, 4-stage axial with 1-stage centrifugal high pressure compressor
Turbine Description: 2 stage high pressure, 3 stage low pressure turbines.