Pratt & Whitney TF30

Bypass Ratio

0.878

Diameter

1305.56 mm

Length

5981.7 mm

Dry Weight

1928.221 kg

Thrust To Weight

5.26

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 can-annular ("cannular")
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 0.878	Overall Pressure Ratio —	Afterburner No

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Name	Aircraft Engine	Number of Engines	Length (m)	Flat Wing Span (m)
Dassault Mirage F2	Pratt & Whitney TF30	1	17.6	10.5
Douglas F6D Missileer	Pratt & Whitney TF30	2	16.1544	21.336
General Dynamics–Grumman F-111B	Pratt & Whitney TF30	2	20.98
Lockheed CL-1200 Lancer	Pratt & Whitney TF30	1	17.45	8.89

All data (15 fields)

Name: Pratt & Whitney TF30
Aircraft Engine Manufacturer: Pratt & Whitney
Aircraft Engine Type: Turbofan
Dry Weight (kg): 1928.221
Diameter (mm): 1305.56
Length (mm): 5981.7
Wikipedia Article (URL): en.wikipedia.org/wiki/Pratt_%26_Whitney_TF30
Geared Fan: No
Combustion Chamber: can-annular ("cannular")
Afterburner: No
Streams: 2
Bypass Ratio: 0.878
Thrust To Weight: 5.26
Compressor Description: 2 spool axial: 3 fan and 6 low pressure stages, 7 high pressure stages
Turbine Description: 1 stage high pressure turbine, 3 stage low pressure turbine